diff --git a/stol/solve.txt b/stol/solve.txt index 14d0dbe..58476d9 100644 --- a/stol/solve.txt +++ b/stol/solve.txt @@ -1,69 +1,69 @@ Cost ---- - 1424 [kg] + 1426 [kg] Free Variables -------------- | Mission - Vs : 35.81 [kt] power off stall speed - W_{cent} : 3141 [lbf] center aircraft weight + Vs : 35.79 [kt] power off stall speed + W_{cent} : 3145 [lbf] center aircraft weight | Mission/Aircraft - m : 1424 [kg] aircraft mass + m : 1426 [kg] aircraft mass | Mission/Aircraft/Battery - E_capacity : 545.1 [Wh] energy capacity - m : 85.82 [kg] total mass + E_capacity : 546.7 [Wh] energy capacity + m : 86.02 [kg] total mass | Mission/Aircraft/BlownWing - m : 262.6 [kg] mass + m : 263.2 [kg] mass | Mission/Aircraft/BlownWing/Powertrain - Pmax : 47.76 [kW] maximum power - m : 9.355 [kg] powertrain mass - m_m : 5.307 [kg] motor mass - m_mc : 4.048 [kg] motor controller mass - r : 0.4324 [m] propeller radius + Pmax : 47.9 [kW] maximum power + m : 9.381 [kg] powertrain mass + m_m : 5.322 [kg] motor mass + m_mc : 4.059 [kg] motor controller mass + r : 0.4326 [m] propeller radius | Mission/Aircraft/BlownWing/Wing - W : 372.8 [lbf] wing weight + W : 373.6 [lbf] wing weight | Mission/Aircraft/BlownWing/Wing/CapSpar - W : 21.43 [lbf] spar weight - I : [ 9.64e-06 7.88e-06 6.48e-06 5.24e-06 ... ] [m**4] spar x moment of inertia - Sy : [ 5.53e-05 4.62e-05 3.81e-05 3.08e-05 ... ] [m**3] section modulus - dm : [ 0.501 0.48 0.461 0.443 ... ] [kg] segment spar mass - hin : [ 13 11.7 10.6 9.57 ... ] [in] height between caps - t : [ 0.376 0.376 0.376 0.376 ... ] [in] spar cap thickness + W : 21.49 [lbf] spar weight + I : [ 9.68e-06 7.91e-06 6.51e-06 5.26e-06 ... ] [m**4] spar x moment of inertia + Sy : [ 5.54e-05 4.63e-05 3.82e-05 3.09e-05 ... ] [m**3] section modulus + dm : [ 0.502 0.481 0.463 0.444 ... ] [kg] segment spar mass + hin : [ 13 11.7 10.7 9.58 ... ] [in] height between caps + t : [ 0.377 0.377 0.377 0.377 ... ] [in] spar cap thickness tshear : [ 0.012 0.012 0.012 0.012 ... ] [in] shear web thickness - w : [ 0.753 0.753 0.753 0.753 ... ] [in] spar width + w : [ 0.754 0.754 0.754 0.754 ... ] [in] spar width | Mission/Aircraft/BlownWing/Wing/Planform - AR : 5.442 aspect ratio - S : 289.4 [ft**2] surface area - b : 39.69 [ft] span - cmac : 7.563 [ft] mean aerodynamic chord - croot : 9.724 [ft] root chord - cave : [ 9.54 9.16 8.79 8.42 ... ] [ft] mid section chord + AR : 5.443 aspect ratio + S : 290.1 [ft**2] surface area + b : 39.74 [ft] span + cmac : 7.571 [ft] mean aerodynamic chord + croot : 9.735 [ft] root chord + cave : [ 9.55 9.17 8.8 8.42 ... ] [ft] mid section chord | Mission/Aircraft/BlownWing/Wing/WingSkin - W : 289.2 [lbf] wing skin weight + W : 289.9 [lbf] wing skin weight t : 0.06 [in] wing skin thickness | Mission/Aircraft/Fuselage f : 2.333 fineness ratio - m : 406.5 [kg] mass of fuselage + m : 407.2 [kg] mass of fuselage | Mission/Aircraft/GenAndIC - P_g_cont : 1.444e+05 [W] genandic cont. power - P_g_sp_cont : 4330 [W/kg] genandic spec power (cont) - P_gc_cont : 1.3e+05 [W] genandic controller cont. power - P_ic_cont : 1.474e+05 [W] piston continous power - m : 96.99 [kg] total mass - m_g : 33.35 [kg] genandic mass - m_gc : 11.01 [kg] genandic controller mass - m_ic : 52.63 [kg] piston mass + P_g_cont : 1.445e+05 [W] genandic cont. power + P_g_sp_cont : 4331 [W/kg] genandic spec power (cont) + P_gc_cont : 1.301e+05 [W] genandic controller cont. power + P_ic_cont : 1.475e+05 [W] piston continous power + m : 97.08 [kg] total mass + m_g : 33.37 [kg] genandic mass + m_gc : 11.02 [kg] genandic controller mass + m_ic : 52.68 [kg] piston mass | Mission/Aircraft/HorizontalTail W : 7.217 [lbf] wing weight @@ -84,17 +84,17 @@ Free Variables t : 0.012 [in] wing skin thickness | Mission/Aircraft/PoweredWheel - RPMmax : 6842 [rpm] maximum RPM of motor - gear_ratio : 7.251 gear ratio of powered wheel - m : 6.702 [kg] mass of powered wheel motor - tau_max : 102.8 [N*m] torque of the + RPMmax : 6840 [rpm] maximum RPM of motor + gear_ratio : 7.252 gear ratio of powered wheel + m : 6.707 [kg] mass of powered wheel motor + tau_max : 102.9 [N*m] torque of the | Mission/Aircraft/Tank - E : 6.528e+05 [Wh] fuel energy - V_fuel : 18.05 [gal] fuel volume - m : 130.9 [lb] total mass - m_fuel : 120.9 [lb] mass of fuel - m_tank : 4.503 [kg] fuel tank mass + E : 6.536e+05 [Wh] fuel energy + V_fuel : 18.07 [gal] fuel volume + m : 131 [lb] total mass + m_fuel : 121.1 [lb] mass of fuel + m_tank : 4.509 [kg] fuel tank mass | Mission/Aircraft/VerticalTail W : 7.217 [lbf] wing weight @@ -115,8 +115,8 @@ Free Variables t : 0.012 [in] wing skin thickness | Mission/AircraftLoading/SparLoading - W : 3141 [lbf] loading weight - Mr : [ 9.4e+04 7.85e+04 6.47e+04 5.24e+04 ... ] [N*m] wing section root moment + W : 3145 [lbf] loading weight + Mr : [ 9.42e+04 7.87e+04 6.49e+04 5.25e+04 ... ] [N*m] wing section root moment | Mission/AircraftLoading/SparLoading/Beam \bar{EI} : [ 1.03 0.845 0.695 0.562 ... ] normalized YM and moment of inertia @@ -127,47 +127,47 @@ Free Variables dx : [ 0.0769 0.0769 0.0769 0.0769 ... ] normalized length of element | Mission/Climb - Sclimb : 41.74 [ft] distance covered in climb - W : 1.396e+04 [N] aircraft weight + Sclimb : 41.73 [ft] distance covered in climb + W : 1.399e+04 [N] aircraft weight h_dot : 27.8 [m/s] climb rate h_gain : 50 [ft] height gained in climb - t : 0.5483 [s] time of climb + t : 0.5482 [s] time of climb | Mission/Climb.1 Sclimb : 5.28e+04 [ft] distance covered in climb - W : 1.396e+04 [N] aircraft weight + W : 1.399e+04 [N] aircraft weight h_dot : 2.224 [m/s] climb rate h_gain : 1950 [ft] height gained in climb t : 267.2 [s] time of climb | Mission/Climb.1/AircraftP.2 - CD : 0.02486 total CD, referenced to wing area - P : 120 [kW] total power draw - P_charge : 7.343 [kW] battery charging power + CD : 0.02483 total CD, referenced to wing area + P : 120.1 [kW] total power draw + P_charge : 7.365 [kW] battery charging power | Mission/Climb.1/AircraftP.2/BatteryP.2 P : 1e-07 [kW] battery power draw | Mission/Climb.1/AircraftP.2/BlownWingP.2 - A_disk : 5.873 [m**2] area of prop disk + A_disk : 5.88 [m**2] area of prop disk C_D : 0.01216 total drag coefficient C_Di : 0.003993 induced drag coefficient - C_Dp : 0.008171 profile drag - C_E : 0.3463 energy momentum coefficient - C_J : 0.6563 jet momentum coefficient + C_Dp : 0.008169 profile drag + C_E : 0.3461 energy momentum coefficient + C_J : 0.656 jet momentum coefficient C_L : 0.2337 total lift coefficient C_LC : 0.95 lift coefficient due to circulation - C_Q : 0.3109 mass momentum coefficient - C_T : 0.02486 thrust coefficient + C_Q : 0.3108 mass momentum coefficient + C_T : 0.02483 thrust coefficient C_f : 0.003297 friction coefficient E_prime : 1.068e+05 [J/m/s] energy flow per unit span - J_prime : 3361 [kg/s**2] momentum flow per unit span - P : 119.8 [kW] power draw - RPMmax : 7196 [rpm] maximum rpm of propeller - Re : 9.167e+06 Reynolds number - T : 1485 [N] propeller thrust - h : 0.6792 [m] Wake height - m_dotprime : 52.88 [kg/m/s] jet mass flow per unit span + J_prime : 3362 [kg/s**2] momentum flow per unit span + P : 119.9 [kW] power draw + RPMmax : 7193 [rpm] maximum rpm of propeller + Re : 9.176e+06 Reynolds number + T : 1486 [N] propeller thrust + h : 0.6795 [m] Wake height + m_dotprime : 52.9 [kg/m/s] jet mass flow per unit span u_j : 123.5 [kt] velocity in jet flow | Mission/Climb.1/AircraftP.2/FuselageP.2 @@ -185,100 +185,102 @@ Free Variables Re : 2.545e+06 Reynolds number | Mission/Climb.1/AircraftP.2/genandicP.2 - P_fuel : 575.6 [kW] power coming in from fuel flow - P_g : 144.4 [kW] generator power - P_gc : 130 [kW] generator controller power - P_ic : 147.4 [kW] internal combustion power - P_out : 127.4 [kW] output from generator controller after efficiency + P_fuel : 576.2 [kW] power coming in from fuel flow + P_g : 144.5 [kW] generator power + P_gc : 130.1 [kW] generator controller power + P_ic : 147.5 [kW] internal combustion power + P_out : 127.5 [kW] output from generator controller after efficiency | Mission/Climb.1/FlightState.2 V : 117.1 [kt] speed + qne : 4964 [kg/m/s**2] never exceed dynamic pressure | Mission/Climb/AircraftP.1 CD : 0.2063 total CD, referenced to wing area - P : 487.8 [kW] total power draw + P : 488.8 [kW] total power draw | Mission/Climb/AircraftP.1/BatteryP.1 - P : 360.4 [kW] battery power draw + P : 361.3 [kW] battery power draw | Mission/Climb/AircraftP.1/BlownWingP.1 - A_disk : 5.873 [m**2] area of prop disk - C_D : 0.1909 total drag coefficient - C_Di : 0.181 induced drag coefficient - C_Dp : 0.009888 profile drag - C_E : 4.101 energy momentum coefficient - C_J : 3.41 jet momentum coefficient + A_disk : 5.88 [m**2] area of prop disk + C_D : 0.191 total drag coefficient + C_Di : 0.1811 induced drag coefficient + C_Dp : 0.009886 profile drag + C_E : 4.107 energy momentum coefficient + C_J : 3.413 jet momentum coefficient C_L : 1.574 total lift coefficient C_LC : 1.05 lift coefficient due to circulation - C_Q : 0.7087 mass momentum coefficient + C_Q : 0.7088 mass momentum coefficient C_T : 1.046 thrust coefficient C_f : 0.00399 friction coefficient - E_prime : 7.238e+04 [J/m/s] energy flow per unit span - J_prime : 2593 [kg/s**2] momentum flow per unit span - P : 477.6 [kW] power draw - RPMmax : 7196 [rpm] maximum rpm of propeller - Re : 3.533e+06 Reynolds number - T : 9275 [N] propeller thrust - h : 0.6792 [m] Wake height - m_dotprime : 46.45 [kg/m/s] jet mass flow per unit span - u_j : 108.5 [kt] velocity in jet flow + E_prime : 7.254e+04 [J/m/s] energy flow per unit span + J_prime : 2597 [kg/s**2] momentum flow per unit span + P : 479 [kW] power draw + RPMmax : 7193 [rpm] maximum rpm of propeller + Re : 3.536e+06 Reynolds number + T : 9297 [N] propeller thrust + h : 0.6795 [m] Wake height + m_dotprime : 46.5 [kg/m/s] jet mass flow per unit span + u_j : 108.6 [kt] velocity in jet flow | Mission/Climb/AircraftP.1/FuselageP.1 - C_f : 0.003632 friction coefficient + C_f : 0.003633 friction coefficient Cd : 0.02081 drag coefficient FF : 5.729 form factor - Re : 5.651e+06 Reynolds number + Re : 5.65e+06 Reynolds number | Mission/Climb/AircraftP.1/TailAero.2 Cd : 0.004061 drag coefficient - Re : 9.808e+05 Reynolds number + Re : 9.807e+05 Reynolds number | Mission/Climb/AircraftP.1/TailAero.3 Cd : 0.004061 drag coefficient - Re : 9.808e+05 Reynolds number + Re : 9.807e+05 Reynolds number | Mission/Climb/AircraftP.1/genandicP.1 - P_fuel : 575.6 [kW] power coming in from fuel flow - P_g : 144.4 [kW] generator power - P_gc : 130 [kW] generator controller power - P_ic : 147.4 [kW] internal combustion power - P_out : 127.4 [kW] output from generator controller after efficiency + P_fuel : 576.2 [kW] power coming in from fuel flow + P_g : 144.5 [kW] generator power + P_gc : 130.1 [kW] generator controller power + P_ic : 147.5 [kW] internal combustion power + P_out : 127.5 [kW] output from generator controller after efficiency | Mission/Climb/FlightState.1 V : 45.11 [kt] speed + qne : 4964 [kg/m/s**2] never exceed dynamic pressure | Mission/Cruise R : 100 [nmi] Range flown in flight segment t : 50 [min] Time to fly flight segment | Mission/Cruise/AircraftP.3 - CD : 0.02438 total CD, referenced to wing area - P : 126.7 [kW] total power draw - P_charge : 0.6541 [kW] battery charging power + CD : 0.02435 total CD, referenced to wing area + P : 126.8 [kW] total power draw + P_charge : 0.6561 [kW] battery charging power | Mission/Cruise/AircraftP.3/BatteryP.3 P : 1e-07 [kW] battery power draw | Mission/Cruise/AircraftP.3/BlownWingP.3 - A_disk : 5.873 [m**2] area of prop disk - C_D : 0.01175 total drag coefficient - C_Di : 0.003616 induced drag coefficient - C_Dp : 0.008131 profile drag - C_E : 0.3453 energy momentum coefficient - C_J : 0.655 jet momentum coefficient + A_disk : 5.88 [m**2] area of prop disk + C_D : 0.01174 total drag coefficient + C_Di : 0.003615 induced drag coefficient + C_Dp : 0.008129 profile drag + C_E : 0.3451 energy momentum coefficient + C_J : 0.6547 jet momentum coefficient C_L : 0.2224 total lift coefficient C_LC : 0.8 lift coefficient due to circulation - C_Q : 0.3106 mass momentum coefficient - C_T : 0.02438 thrust coefficient - C_f : 0.003281 friction coefficient - E_prime : 1.147e+05 [J/m/s] energy flow per unit span - J_prime : 3525 [kg/s**2] momentum flow per unit span - P : 126.5 [kW] power draw - RPMmax : 7196 [rpm] maximum rpm of propeller - Re : 9.397e+06 Reynolds number - T : 1530 [N] propeller thrust - h : 0.6792 [m] Wake height - m_dotprime : 54.15 [kg/m/s] jet mass flow per unit span + C_Q : 0.3105 mass momentum coefficient + C_T : 0.02435 thrust coefficient + C_f : 0.00328 friction coefficient + E_prime : 1.148e+05 [J/m/s] energy flow per unit span + J_prime : 3527 [kg/s**2] momentum flow per unit span + P : 126.6 [kW] power draw + RPMmax : 7193 [rpm] maximum rpm of propeller + Re : 9.407e+06 Reynolds number + T : 1532 [N] propeller thrust + h : 0.6795 [m] Wake height + m_dotprime : 54.18 [kg/m/s] jet mass flow per unit span u_j : 126.5 [kt] velocity in jet flow | Mission/Cruise/AircraftP.3/FuselageP.3 @@ -296,212 +298,217 @@ Free Variables Re : 2.609e+06 Reynolds number | Mission/Cruise/AircraftP.3/genandicP.3 - P_fuel : 575.6 [kW] power coming in from fuel flow - P_g : 144.4 [kW] generator power - P_gc : 130 [kW] generator controller power - P_ic : 147.4 [kW] internal combustion power - P_out : 127.4 [kW] output from generator controller after efficiency + P_fuel : 576.2 [kW] power coming in from fuel flow + P_g : 144.5 [kW] generator power + P_gc : 130.1 [kW] generator controller power + P_ic : 147.5 [kW] internal combustion power + P_out : 127.5 [kW] output from generator controller after efficiency | Mission/Cruise/FlightState.3 V : 120 [kt] speed + qne : 4964 [kg/m/s**2] never exceed dynamic pressure + + | Mission/FlightState.6 + qne : 4964 [kg/m/s**2] never exceed dynamic pressure | Mission/Landing - Sgr : 27.33 [ft] landing distance + Sgr : 27.32 [ft] landing distance Vs : 17.1 [kt] stall velocity - W : 1.397e+04 [N] aircraft weight - Xgr : 27.33 [ft] landing ground roll - Xla : 27.33 [ft] total landing distance - t : 3.157 [s] time of landing maneuver + W : 1.399e+04 [N] aircraft weight + Xgr : 27.32 [ft] landing ground roll + Xla : 27.32 [ft] total landing distance + t : 3.156 [s] time of landing maneuver | Mission/Landing/AircraftP.5 - CD : 8.805 total CD, referenced to wing area - P : 728.1 [kW] total power draw + CD : 8.808 total CD, referenced to wing area + P : 729.7 [kW] total power draw | Mission/Landing/AircraftP.5/BatteryP.5 - P : 600.7 [kW] battery power draw + P : 602.2 [kW] battery power draw | Mission/Landing/AircraftP.5/BlownWingP.5 - A_disk : 5.873 [m**2] area of prop disk - C_D : 8.787 total drag coefficient - C_Di : 8.775 induced drag coefficient - C_Dp : 0.01201 profile drag - C_E : 78.24 energy momentum coefficient - C_J : 24.34 jet momentum coefficient - C_L : 10.95 total lift coefficient + A_disk : 5.88 [m**2] area of prop disk + C_D : 8.789 total drag coefficient + C_Di : 8.777 induced drag coefficient + C_Dp : 0.012 profile drag + C_E : 78.36 energy momentum coefficient + C_J : 24.37 jet momentum coefficient + C_L : 10.96 total lift coefficient C_LC : 6.78 lift coefficient due to circulation C_Q : 1.894 mass momentum coefficient - C_T : 8.805 thrust coefficient - C_f : 0.004845 friction coefficient - E_prime : 7.517e+04 [J/m/s] energy flow per unit span - J_prime : 2659 [kg/s**2] momentum flow per unit span - P : 477.6 [kW] power draw - RPMmax : 7196 [rpm] maximum rpm of propeller - Re : 1.339e+06 Reynolds number - T : 1.122e+04 [N] propeller thrust - h : 0.6792 [m] Wake height - m_dotprime : 47.04 [kg/m/s] jet mass flow per unit span - u_j : 109.9 [kt] velocity in jet flow + C_T : 8.808 thrust coefficient + C_f : 0.004844 friction coefficient + E_prime : 7.535e+04 [J/m/s] energy flow per unit span + J_prime : 2664 [kg/s**2] momentum flow per unit span + P : 479 [kW] power draw + RPMmax : 7193 [rpm] maximum rpm of propeller + Re : 1.34e+06 Reynolds number + T : 1.125e+04 [N] propeller thrust + h : 0.6795 [m] Wake height + m_dotprime : 47.09 [kg/m/s] jet mass flow per unit span + u_j : 110 [kt] velocity in jet flow | Mission/Landing/AircraftP.5/FuselageP.5 C_f : 0.00441 friction coefficient - Cd : 0.02527 drag coefficient - FF : 5.729 form factor - Re : 2.142e+06 Reynolds number + Cd : 0.02528 drag coefficient + FF : 5.732 form factor + Re : 2.141e+06 Reynolds number | Mission/Landing/AircraftP.5/TailAero.10 - Cd : 0.006251 drag coefficient + Cd : 0.006324 drag coefficient Re : 3.717e+05 Reynolds number | Mission/Landing/AircraftP.5/TailAero.11 - Cd : 0.006251 drag coefficient + Cd : 0.006324 drag coefficient Re : 3.717e+05 Reynolds number | Mission/Landing/AircraftP.5/genandicP.5 - P_fuel : 575.6 [kW] power coming in from fuel flow - P_g : 144.4 [kW] generator power - P_gc : 130 [kW] generator controller power - P_ic : 147.4 [kW] internal combustion power - P_out : 127.4 [kW] output from generator controller after efficiency + P_fuel : 576.2 [kW] power coming in from fuel flow + P_g : 144.5 [kW] generator power + P_gc : 130.1 [kW] generator controller power + P_ic : 147.5 [kW] internal combustion power + P_out : 127.5 [kW] output from generator controller after efficiency | Mission/Landing/FlightState.5 V : 17.1 [kt] speed qne : 4964 [kg/m/s**2] never exceed dynamic pressure | Mission/Reserve/AircraftP.4 - CD : 0.07551 total CD, referenced to wing area - P : 56.18 [kW] total power draw - P_charge : 1.09 [kW] battery charging power + CD : 0.07539 total CD, referenced to wing area + P : 56.28 [kW] total power draw + P_charge : 1.093 [kW] battery charging power | Mission/Reserve/AircraftP.4/BatteryP.4 P : 1e-07 [kW] battery power draw | Mission/Reserve/AircraftP.4/BlownWingP.4 - A_disk : 5.873 [m**2] area of prop disk - C_D : 0.06108 total drag coefficient - C_Di : 0.05179 induced drag coefficient - C_Dp : 0.009288 profile drag - C_E : 0.4599 energy momentum coefficient - C_J : 0.7929 jet momentum coefficient - C_L : 0.8416 total lift coefficient + A_disk : 5.88 [m**2] area of prop disk + C_D : 0.061 total drag coefficient + C_Di : 0.05171 induced drag coefficient + C_Dp : 0.009286 profile drag + C_E : 0.4596 energy momentum coefficient + C_J : 0.7925 jet momentum coefficient + C_L : 0.8411 total lift coefficient C_LC : 0.8 lift coefficient due to circulation - C_Q : 0.3418 mass momentum coefficient - C_T : 0.07551 thrust coefficient - C_f : 0.003748 friction coefficient - E_prime : 2.075e+04 [J/m/s] energy flow per unit span - J_prime : 1127 [kg/s**2] momentum flow per unit span - P : 55.93 [kW] power draw - RPMmax : 7196 [rpm] maximum rpm of propeller - Re : 4.83e+06 Reynolds number - T : 1252 [N] propeller thrust - h : 0.6792 [m] Wake height - m_dotprime : 30.63 [kg/m/s] jet mass flow per unit span - u_j : 71.56 [kt] velocity in jet flow + C_Q : 0.3416 mass momentum coefficient + C_T : 0.07539 thrust coefficient + C_f : 0.003747 friction coefficient + E_prime : 2.078e+04 [J/m/s] energy flow per unit span + J_prime : 1129 [kg/s**2] momentum flow per unit span + P : 56.03 [kW] power draw + RPMmax : 7193 [rpm] maximum rpm of propeller + Re : 4.837e+06 Reynolds number + T : 1254 [N] propeller thrust + h : 0.6795 [m] Wake height + m_dotprime : 30.65 [kg/m/s] jet mass flow per unit span + u_j : 71.58 [kt] velocity in jet flow | Mission/Reserve/AircraftP.4/FuselageP.4 C_f : 0.003412 friction coefficient Cd : 0.01955 drag coefficient FF : 5.729 form factor - Re : 7.727e+06 Reynolds number + Re : 7.729e+06 Reynolds number | Mission/Reserve/AircraftP.4/TailAero.8 Cd : 0.003836 drag coefficient - Re : 1.341e+06 Reynolds number + Re : 1.342e+06 Reynolds number | Mission/Reserve/AircraftP.4/TailAero.9 Cd : 0.003836 drag coefficient - Re : 1.341e+06 Reynolds number + Re : 1.342e+06 Reynolds number | Mission/Reserve/AircraftP.4/genandicP.4 - P_fuel : 258.8 [kW] power coming in from fuel flow - P_g : 64.94 [kW] generator power - P_gc : 58.44 [kW] generator controller power - P_ic : 66.26 [kW] internal combustion power - P_out : 57.27 [kW] output from generator controller after efficiency + P_fuel : 259.3 [kW] power coming in from fuel flow + P_g : 65.05 [kW] generator power + P_gc : 58.54 [kW] generator controller power + P_ic : 66.37 [kW] internal combustion power + P_out : 57.37 [kW] output from generator controller after efficiency | Mission/Reserve/FlightState.4 - V : 61.68 [kt] speed + V : 61.7 [kt] speed + qne : 4964 [kg/m/s**2] never exceed dynamic pressure | Mission/TakeOff A : 14.44 [m/s**2] log fit equation helper 1 B : 0.01151 [1/m] log fit equation helper 2 - CDg : 0.9941 drag ground coefficient - Sto : 53.26 [ft] take off distance - T : 2.09e+04 [N] take off thrust - W : 1.396e+04 [N] aircraft weight - t : 2.738 [s] time of takeoff maneuver - zsto : 0.3736 take off distance helper variable + CDg : 0.9946 drag ground coefficient + Sto : 53.27 [ft] take off distance + T : 2.094e+04 [N] take off thrust + W : 1.399e+04 [N] aircraft weight + t : 2.739 [s] time of takeoff maneuver + zsto : 0.3739 take off distance helper variable | Mission/TakeOff/AircraftP - CD : 1.512 total CD, referenced to wing area - P : 728.1 [kW] total power draw + CD : 1.513 total CD, referenced to wing area + P : 729.7 [kW] total power draw | Mission/TakeOff/AircraftP/BatteryP - P : 600.7 [kW] battery power draw + P : 602.2 [kW] battery power draw | Mission/TakeOff/AircraftP/BlownWingP - A_disk : 5.873 [m**2] area of prop disk - C_D : 0.9941 total drag coefficient - C_Di : 0.9839 induced drag coefficient + A_disk : 5.88 [m**2] area of prop disk + C_D : 0.9946 total drag coefficient + C_Di : 0.9844 induced drag coefficient C_Dp : 0.01021 profile drag - C_E : 6.571 energy momentum coefficient - C_J : 4.669 jet momentum coefficient - C_L : 3.668 total lift coefficient + C_E : 6.582 energy momentum coefficient + C_J : 4.673 jet momentum coefficient + C_L : 3.67 total lift coefficient C_LC : 2.18 lift coefficient due to circulation - C_Q : 0.8293 mass momentum coefficient - C_T : 1.512 thrust coefficient - C_f : 0.004121 friction coefficient - E_prime : 7.158e+04 [J/m/s] energy flow per unit span - J_prime : 2574 [kg/s**2] momentum flow per unit span - P : 477.6 [kW] power draw - RPMmax : 7196 [rpm] maximum rpm of propeller - Re : 3.008e+06 Reynolds number - T : 9724 [N] propeller thrust - h : 0.6792 [m] Wake height - m_dotprime : 46.28 [kg/m/s] jet mass flow per unit span - u_j : 108.1 [kt] velocity in jet flow + C_Q : 0.8295 mass momentum coefficient + C_T : 1.513 thrust coefficient + C_f : 0.00412 friction coefficient + E_prime : 7.174e+04 [J/m/s] energy flow per unit span + J_prime : 2578 [kg/s**2] momentum flow per unit span + P : 479 [kW] power draw + RPMmax : 7193 [rpm] maximum rpm of propeller + Re : 3.01e+06 Reynolds number + T : 9748 [N] propeller thrust + h : 0.6795 [m] Wake height + m_dotprime : 46.33 [kg/m/s] jet mass flow per unit span + u_j : 108.2 [kt] velocity in jet flow | Mission/TakeOff/AircraftP/FuselageP C_f : 0.003751 friction coefficient - Cd : 0.1116 drag coefficient - FF : 29.74 form factor - Re : 4.811e+06 Reynolds number + Cd : 0.1118 drag coefficient + FF : 29.8 form factor + Re : 4.81e+06 Reynolds number | Mission/TakeOff/AircraftP/TailAero - Cd : 0.5161 drag coefficient - Re : 8.351e+05 Reynolds number + Cd : 0.5191 drag coefficient + Re : 8.35e+05 Reynolds number | Mission/TakeOff/AircraftP/TailAero.1 - Cd : 0.5161 drag coefficient - Re : 8.351e+05 Reynolds number + Cd : 0.5191 drag coefficient + Re : 8.35e+05 Reynolds number | Mission/TakeOff/AircraftP/genandicP - P_fuel : 575.6 [kW] power coming in from fuel flow - P_g : 144.4 [kW] generator power - P_gc : 130 [kW] generator controller power - P_ic : 147.4 [kW] internal combustion power - P_out : 127.4 [kW] output from generator controller after efficiency + P_fuel : 576.2 [kW] power coming in from fuel flow + P_g : 144.5 [kW] generator power + P_gc : 130.1 [kW] generator controller power + P_ic : 147.5 [kW] internal combustion power + P_out : 127.5 [kW] output from generator controller after efficiency | Mission/TakeOff/FlightState - V : 38.41 [kt] speed + V : 38.4 [kt] speed qne : 4964 [kg/m/s**2] never exceed dynamic pressure | Mission/TakeOff/PoweredWheelP - P : 83.48 [kW] power draw of powered wheel - RPM : 6842 [rpm] rpm of powered wheel - T : 3726 [N] thrust from powered wheel - tau : 102.8 [N*m] torque of powered wheel + P : 83.56 [kW] power draw of powered wheel + RPM : 6840 [rpm] rpm of powered wheel + T : 3731 [N] thrust from powered wheel + tau : 102.9 [N*m] torque of powered wheel | Mission/TakeOff/PoweredWheelP.1 - P : 83.48 [kW] power draw of powered wheel - RPM : 6842 [rpm] rpm of powered wheel - T : 3726 [N] thrust from powered wheel - tau : 102.8 [N*m] torque of powered wheel + P : 83.56 [kW] power draw of powered wheel + RPM : 6840 [rpm] rpm of powered wheel + T : 3731 [N] thrust from powered wheel + tau : 102.9 [N*m] torque of powered wheel | Mission/TakeOff/PoweredWheelP.2 - P : 83.48 [kW] power draw of powered wheel - RPM : 6842 [rpm] rpm of powered wheel - T : 3726 [N] thrust from powered wheel - tau : 102.8 [N*m] torque of powered wheel + P : 83.56 [kW] power draw of powered wheel + RPM : 6840 [rpm] rpm of powered wheel + T : 3731 [N] thrust from powered wheel + tau : 102.9 [N*m] torque of powered wheel Constants --------- @@ -716,7 +723,8 @@ Constants eta_wiring : 0.98 efficiency of electrical connections (wiring loss) | Mission/Climb.1/FlightState.2 - g : 9.8 [m/s**2] acceleration due to gravity + Vne : 175 [kt] never exceed speed + g : 9.81 [m/s**2] acceleration due to gravity mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density @@ -755,7 +763,8 @@ Constants eta_wiring : 0.98 efficiency of electrical connections (wiring loss) | Mission/Climb/FlightState.1 - g : 9.8 [m/s**2] acceleration due to gravity + Vne : 175 [kt] never exceed speed + g : 9.81 [m/s**2] acceleration due to gravity mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density @@ -798,11 +807,15 @@ Constants eta_wiring : 0.98 efficiency of electrical connections (wiring loss) | Mission/Cruise/FlightState.3 - g : 9.8 [m/s**2] acceleration due to gravity + Vne : 175 [kt] never exceed speed + g : 9.81 [m/s**2] acceleration due to gravity mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density | Mission/FlightState.6 + Vne : 175 [kt] never exceed speed + g : 9.81 [m/s**2] acceleration due to gravity + mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density | Mission/Landing @@ -852,7 +865,7 @@ Constants | Mission/Landing/FlightState.5 Vne : 175 [kt] never exceed speed - g : 9.8 [m/s**2] acceleration due to gravity + g : 9.81 [m/s**2] acceleration due to gravity mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density @@ -895,7 +908,8 @@ Constants eta_wiring : 0.98 efficiency of electrical connections (wiring loss) | Mission/Reserve/FlightState.4 - g : 9.8 [m/s**2] acceleration due to gravity + Vne : 175 [kt] never exceed speed + g : 9.81 [m/s**2] acceleration due to gravity mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density @@ -946,7 +960,7 @@ Constants | Mission/TakeOff/FlightState Vne : 175 [kt] never exceed speed - g : 9.8 [m/s**2] acceleration due to gravity + g : 9.81 [m/s**2] acceleration due to gravity mu : 1.789e-05 [N*s/m**2] air viscosity rho : 1.225 [kg/m**3] air density @@ -967,9 +981,9 @@ Sensitivities g : +0.023 earth surface gravitational acceleration | CFRPFabric - rho : +0.41 density of CFRP - tmin : +0.41 minimum gauge thickness - tau : -2.6e-13 torsional stress limit + rho : +0.42 density of CFRP + tmin : +0.42 minimum gauge thickness + tau : -3.1e-12 torsional stress limit | CFRPUD rho : +0.02 density of CFRP @@ -985,17 +999,18 @@ Sensitivities h_obstacle : +0.19 R : +0.11 mission range Scruiseclimb : +0.0096 - mrunway : +1.1e-11 runway margin - h_cruise : +3.8e-12 - Sto : -8.2e-12 takeoff field length - Vstall : -4.5e-12 power off stall requirement - Sland : -2.5e-12 landing field length - CLstall : -2.3e-12 power off stall CL + mrunway : +1.3e-10 runway margin + h_cruise : +4.6e-11 + Sto : -9.9e-11 takeoff field length + Vstall : -5.4e-11 power off stall requirement + Sland : -3e-11 landing field length + CLstall : -2.7e-11 power off stall CL | Mission/Aircraft Npax : +0.055 number of passengers mbaggage : +0.055 mass of baggage croot : +0.05 + w_fuse : +5.1e-11 bh : +0 bv : +0 lh : +0 @@ -1004,8 +1019,8 @@ Sensitivities | Mission/Aircraft/Battery P_max_burst : -0.22 burst power output - P_max_cont : -1.2e-10 continuous power output - Estar : -7.8e-13 specific energy + P_max_cont : -1.5e-09 continuous power output + Estar : -9.4e-12 specific energy | Mission/Aircraft/BlownWing n_prop : +0.057 number of props @@ -1020,20 +1035,20 @@ Sensitivities | Mission/Aircraft/BlownWing/Wing/CapSpar mfac : -0.023 curvature knockdown factor - wlim : -1.5e-12 spar width to chord ratio + wlim : -1.8e-11 spar width to chord ratio | Mission/Aircraft/BlownWing/Wing/Planform cbarmac : +0.19 non-dim MAC - deta : [ +0.0069 +0.0069 +0.0069 +0.0069 ... ] \Delta (2y/b) + deta : [ +0.007 +0.007 +0.0069 +0.0069 ... ] \Delta (2y/b) cbar : [ +0.19 + - + - + - ... ] non-dim chord at nodes tau : -0.02 airfoil thickness ratio - cbave : [ -0.02 -8.2e-11 -4.2e-11 -2.7e-11 ... ] non-dim mid section chord + cbave : [ -0.02 -9.9e-10 -5.1e-10 -3.3e-10 ... ] non-dim mid section chord | Mission/Aircraft/BlownWing/Wing/WingSkin - Vne : +5.2e-13 never exceed vehicle speed - Cmw : +2.6e-13 negative wing moment coeff - rhosl : +2.6e-13 sea level air density - Jtbar : -2.6e-13 torsional moment of inertia + Vne : +6.3e-12 never exceed vehicle speed + Cmw : +3.1e-12 negative wing moment coeff + rhosl : +3.1e-12 sea level air density + Jtbar : -3.1e-12 torsional moment of inertia | Mission/Aircraft/Cabin m : +0.2 total mass @@ -1046,9 +1061,9 @@ Sensitivities | Mission/Aircraft/GenAndIC P_ic_sp_cont : -0.13 specific cont power of IC (2.8 if turboshaft) - m_ref : -0.11 reference mass, for meeting units constraints + Pstar_ref : -0.068 reference specific power, for meeting units constraints P_gc_sp_cont : -0.028 genandic controller cont power - Pstar_ref : -0.004 reference specific power, for meeting units constraints + m_ref : +0.016 reference mass, for meeting units constraints | Mission/Aircraft/HorizontalTail mfac : +0.0083 wing weight margin factor @@ -1071,11 +1086,13 @@ Sensitivities rhosl : +0 sea level air density | Mission/Aircraft/PoweredWheel + d : -0.059 c : -0.042 - b : +0.033 + e : +0.026 + b : +0.01 a : -0.0011 - r : +1.5e-12 tire radius - gear_ratio_max : -2.4e-12 max gear ratio of powered wheel + r : +1.8e-11 tire radius + gear_ratio_max : -2.9e-11 max gear ratio of powered wheel | Mission/Aircraft/Tank Estar_fuel : -0.15 fuel specific energy @@ -1109,25 +1126,28 @@ Sensitivities | Mission/AircraftLoading/SparLoading/Beam \bar{q} : [ +8.3e-05 +0.00032 +0.00063 +0.00092 ... ] normalized loading - \bar{M}_{tip} : +1.7e-11 Tip moment - \bar{S}_{tip} : +9.1e-12 Tip loading - \theta_{root} : +4.5e-12 Base angle -\bar{\delta}_{root} : +3.7e-12 Base deflection + \bar{M}_{tip} : +3.6e-11 Tip moment + \bar{S}_{tip} : +2.5e-11 Tip loading + \theta_{root} : +1.7e-11 Base angle +\bar{\delta}_{root} : +1.2e-11 Base deflection | Mission/Climb.1/AircraftP.2 P_avionics : +9.2e-06 avionics continuous power draw - P_draw_batt : +1.1e-13 + P_draw_batt : +1.3e-12 | Mission/Climb.1/AircraftP.2/BlownWingP.2 a : +0.024 Mlim : -0.02 tip limit a : -0.02 speed of sound at sea level - b : -0.0046 + eta_prop : -0.0086 prop efficiency loss after blade disk actuator + eta_m : -0.0086 motor efficiency + eta_mc : -0.0086 motor controller efficiency + b : -0.0047 Kf : +0.0015 form factor mfac : +0.0015 profile drag margin factor e : -0.00073 span efficiency c : +0.00039 - rho_j : -1.4e-13 density in jet flow + rho_j : -1.7e-12 density in jet flow | Mission/Climb.1/AircraftP.2/FuselageP.2 mfac : +0.0022 friction margin @@ -1145,20 +1165,24 @@ Sensitivities eta_shaft : -0.0047 shaft losses (two 99% efficient bearings) | Mission/Climb.1/FlightState.2 - rho : +0.0023 air density + rho : +0.0022 air density g : +0.0015 acceleration due to gravity mu : +0.00076 air viscosity + Vne : +0 never exceed speed | Mission/Climb/AircraftP.1 - P_avionics : +9.7e-13 avionics continuous power draw + P_avionics : +1.2e-11 avionics continuous power draw | Mission/Climb/AircraftP.1/BlownWingP.1 + eta_mc : -0.24 motor controller efficiency + eta_m : -0.24 motor efficiency + eta_prop : -0.24 prop efficiency loss after blade disk actuator a : +0.024 Mlim : -0.02 tip limit a : -0.02 speed of sound at sea level - e : -0.0093 span efficiency + e : -0.0094 span efficiency rho_j : -0.0086 density in jet flow - b : -0.0046 + b : -0.0047 Kf : +0.00098 form factor mfac : +0.00098 profile drag margin factor c : +0.00039 @@ -1173,15 +1197,16 @@ Sensitivities m_{fac--fit} : +2.3e-05 RMS error of fit | Mission/Climb/AircraftP.1/genandicP.1 - eta_g : -4.2e-11 generator efficiency - eta_gc : -4.2e-11 efficiency of generator controller - eta_ic : -4.2e-11 internal combustion engine efficiency - eta_shaft : -4.2e-11 shaft losses (two 99% efficient bearings) + eta_g : -5.3e-10 generator efficiency + eta_gc : -5.3e-10 efficiency of generator controller + eta_ic : -5.3e-10 internal combustion engine efficiency + eta_shaft : -5.3e-10 shaft losses (two 99% efficient bearings) | Mission/Climb/FlightState.1 g : +0.25 acceleration due to gravity - rho : -0.026 air density + rho : -0.074 air density mu : +0.0005 air viscosity + Vne : +0 never exceed speed | Mission/Cruise Vmin : +0.55 minimum flight speed @@ -1191,15 +1216,18 @@ Sensitivities P_draw_batt : +0 | Mission/Cruise/AircraftP.3/BlownWingP.3 - mfac : +0.1 profile drag margin factor + eta_mc : -0.58 motor controller efficiency + eta_prop : -0.58 prop efficiency loss after blade disk actuator + eta_m : -0.58 motor efficiency Kf : +0.1 form factor + mfac : +0.1 profile drag margin factor e : -0.045 span efficiency - a : +0.024 + c : +0.024 Mlim : -0.02 tip limit a : -0.02 speed of sound at sea level - b : -0.0046 - c : +0.00039 - rho_j : -1.5e-13 density in jet flow + b : -0.0047 + a : +0.00039 + rho_j : -1.9e-12 density in jet flow | Mission/Cruise/AircraftP.3/FuselageP.3 mfac : +0.15 friction margin @@ -1217,12 +1245,14 @@ Sensitivities eta_ic : -0.14 internal combustion engine efficiency | Mission/Cruise/FlightState.3 - rho : +0.16 air density - g : +0.09 acceleration due to gravity + rho : +0.15 air density + g : +0.091 acceleration due to gravity mu : +0.052 air viscosity + Vne : +0 never exceed speed | Mission/FlightState.6 - rho : -2.3e-12 air density + Vne : +0 never exceed speed + rho : -2.7e-11 air density | Mission/Landing mstall : +0.00023 stall @@ -1230,18 +1260,21 @@ Sensitivities mu_b : -0.00012 braking friction coefficient | Mission/Landing/AircraftP.5 - P_avionics : +4.6e-13 avionics continuous power draw + P_avionics : +5.5e-12 avionics continuous power draw | Mission/Landing/AircraftP.5/BlownWingP.5 - a : +0.024 + c : +0.024 Mlim : -0.02 tip limit a : -0.02 speed of sound at sea level - b : -0.0046 - c : +0.00039 + b : -0.0047 + a : +0.00039 e : -6.2e-05 span efficiency - Kf : +8.4e-08 form factor + eta_mc : -5e-05 motor controller efficiency + eta_m : -5e-05 motor efficiency + eta_prop : -5e-05 prop efficiency loss after blade disk actuator mfac : +8.4e-08 profile drag margin factor - rho_j : -1.8e-12 density in jet flow + Kf : +8.4e-08 form factor + rho_j : -2.2e-11 density in jet flow | Mission/Landing/AircraftP.5/FuselageP.5 mfac : +1.3e-07 friction margin @@ -1255,12 +1288,12 @@ Sensitivities | Mission/Landing/AircraftP.5/genandicP.5 eta_ic : +0.068 internal combustion engine efficiency eta_shaft : +0.068 shaft losses (two 99% efficient bearings) - eta_g : -1.3e-12 generator efficiency - eta_gc : -1.3e-12 efficiency of generator controller + eta_g : -1.5e-11 generator efficiency + eta_gc : -1.5e-11 efficiency of generator controller | Mission/Landing/FlightState.5 g : +0.00012 acceleration due to gravity - rho : -6.2e-05 air density + rho : -8e-05 air density mu : +4.5e-08 air viscosity Vne : +0 never exceed speed @@ -1272,15 +1305,18 @@ Sensitivities P_draw_batt : +0 | Mission/Reserve/AircraftP.4/BlownWingP.4 - c : +0.024 + eta_m : -0.054 motor efficiency + eta_mc : -0.054 motor controller efficiency + eta_prop : -0.054 prop efficiency loss after blade disk actuator + a : +0.024 e : -0.021 span efficiency Mlim : -0.02 tip limit a : -0.02 speed of sound at sea level - b : -0.0046 + b : -0.0047 Kf : +0.0038 form factor mfac : +0.0038 profile drag margin factor - a : +0.00039 - rho_j : -4.3e-12 density in jet flow + c : +0.00039 + rho_j : -5.1e-11 density in jet flow | Mission/Reserve/AircraftP.4/FuselageP.4 mfac : +0.0058 friction margin @@ -1299,38 +1335,42 @@ Sensitivities | Mission/Reserve/FlightState.4 g : +0.043 acceleration due to gravity - rho : -0.014 air density + rho : -0.016 air density mu : +0.002 air viscosity + Vne : +0 never exceed speed | Mission/TakeOff - g : -0.27 gravitational constant + g : -0.28 gravitational constant m_{fac--fit} : +0.24 fit factor a : +0.035 mu_friction : -0.035 traction limit for powered wheels mu : +0.005 coefficient of rolling resistance | Mission/TakeOff/AircraftP - P_avionics : +4.6e-13 avionics continuous power draw + P_avionics : +5.5e-12 avionics continuous power draw | Mission/TakeOff/AircraftP/BlownWingP + eta_m : -0.3 motor efficiency + eta_mc : -0.3 motor controller efficiency + eta_prop : -0.3 prop efficiency loss after blade disk actuator rho_j : -0.18 density in jet flow e : +0.12 span efficiency - a : +0.024 + c : +0.024 Mlim : -0.02 tip limit a : -0.02 speed of sound at sea level - b : -0.0046 + b : -0.0047 Kf : +0.0006 form factor mfac : +0.0006 profile drag margin factor - c : +0.00039 + a : +0.00039 | Mission/TakeOff/AircraftP/FuselageP - mfac : +3.1e-12 friction margin + mfac : +3.7e-11 friction margin | Mission/TakeOff/AircraftP/TailAero - m_{fac--fit} : +2.4e-12 RMS error of fit + m_{fac--fit} : +2.9e-11 RMS error of fit | Mission/TakeOff/AircraftP/TailAero.1 - m_{fac--fit} : +2.4e-12 RMS error of fit + m_{fac--fit} : +2.9e-11 RMS error of fit | Mission/TakeOff/AircraftP/genandicP eta_g : -0.046 generator efficiency @@ -1339,8 +1379,8 @@ Sensitivities eta_shaft : -0.046 shaft losses (two 99% efficient bearings) | Mission/TakeOff/FlightState - g : +0.79 acceleration due to gravity - rho : -0.16 air density + g : +0.8 acceleration due to gravity + rho : -0.23 air density mu : +0.00012 air viscosity Vne : +0 never exceed speed diff --git a/stol/stol.py b/stol/stol.py index fea83a9..a94f391 100644 --- a/stol/stol.py +++ b/stol/stol.py @@ -43,7 +43,7 @@ def setup(self,poweredwheels=False,n_wheels=3,hybrid=False): # self.htail.substitutions[self.htail.Vh] = 0.4 self.components = [self.cabin,self.bw,self.battery,self.fuselage] - + if hybrid: self.tank = Tank() self.genandic = GenAndIC() @@ -143,7 +143,7 @@ class Fuselage(Model): w 50 [in] width h 60 [in] height f [-] fineness ratio - Swet 29833.67 [in^2] wetted area of fuselage + Swet 29833.67 [in^2] wetted area of fuselage """ def setup(self): exec parse_variables(Fuselage.__doc__) @@ -188,7 +188,7 @@ class Powertrain(Model): def setup(self): exec parse_variables(Powertrain.__doc__) - + with gpkit.SignomialsEnabled(): constraints = [#P_m_sp_cont/Pstar_ref <= -0.228*(m_m/m_ref)**2+45.7*(m_m/m_ref)+3060, m >= m_m+m_mc, @@ -257,7 +257,7 @@ class GenAndIC(Model): P_g_cont [W] genandic cont. power P_gc_cont [W] genandic controller cont. power P_gc_sp_cont 11.8 [kW/kg] genandic controller cont power - P_ic_cont [W] piston continous power + P_ic_cont [W] piston continous power m [kg] total mass m_ref 1 [kg] reference mass, for meeting units constraints Pstar_ref 1 [W/kg] reference specific power, for meeting units constraints @@ -299,7 +299,7 @@ def setup(self,gen,state): P_fuel*eta_ic == P_ic, P_ic*eta_shaft == P_g, P_g*eta_g == P_gc, - P_gc*eta_gc == P_out + P_gc*eta_gc == P_out ] return constraints @@ -367,12 +367,15 @@ class Wing(Model): W [lbf] wing weight mfac 1.2 [-] wing weight margin factor n_plies 5 [-] number of plies on skin + Upper Unbounded --------------- - W + W, planform.tau + Lower Unbounded --------------- b, Sy + LaTex Strings ------------- mfac m_{\\mathrm{fac}} @@ -467,8 +470,8 @@ class BlownWingP(Model): a 343 [m/s] speed of sound at sea level k_t 0.2 [-] propeller torque coefficient RPMmax [rpm] maximum rpm of propeller - Kf 1.180 [-] form factor - C_f [-] friction coefficient + Kf 1.180 [-] form factor + C_f [-] friction coefficient """ def setup(self,bw,state): #bw is a BlownWing object @@ -565,7 +568,7 @@ def setup(self, aircraft,poweredwheels,n_wheels,hybrid=False): CDg >= perf.bw_perf.C_D, V >= mstall*(2*W/rho/S/perf.bw_perf.C_L)**0.5, - FitCS(fd, zsto, [A/g, B*V**2/g]), #fit constraint set, pass in fit data, zsto is the + FitCS(fd, zsto, [A/g, B*V**2/g]), #fit constraint set, pass in fit data, zsto is the # y variable, then arr of independent (input) vars, watch the units Sto >= 1.0/2.0/B*zsto, t >= Sto/(0.3*V)] @@ -576,7 +579,7 @@ def setup(self, aircraft,poweredwheels,n_wheels,hybrid=False): with gpkit.SignomialsEnabled(): constraints += [T <= perf.bw_perf.T + sum(model.T for model in wheel_models), perf.P >= perf.bw_perf.P + sum(model.P for model in wheel_models) - + ] for model in wheel_models: constraints += [model.T <= (aircraft.mass*g*mu_friction)/Variable("a",len(wheel_models),"-")] @@ -598,7 +601,7 @@ class Climb(Model): t [s] time of climb h_dot [m/s] climb rate W [N] aircraft weight - + LaTex Strings ------------- Sclimb S_{\\mathrm{climb}} @@ -624,7 +627,7 @@ def setup(self,aircraft,hybrid=False,powermode="batt-dischrg"): h_gain <= h_dot*t, Sclimb == V*t, #sketchy constraint, is wrong with cos(climb angle) ] - return constraints, perf + return constraints, perf, self.flightstate class Cruise(Model): """ @@ -644,7 +647,7 @@ def setup(self,aircraft,hybrid=False): self.flightstate["V"] >= Vmin, self.perf.bw_perf.C_LC == 0.8] - return constraints, self.perf + return constraints, self.perf, self.flightstate class Reserve(Model): """ @@ -661,8 +664,8 @@ def setup(self,aircraft,hybrid=False): self.perf = aircraft.dynamic(self.flightstate,hybrid,powermode="batt-chrg",t_charge=t) constraints = [self.perf.bw_perf.C_LC == 0.8] - return constraints, self.perf - + return constraints, self.perf, self.flightstate + class Landing(Model): """ landing model @@ -684,7 +687,7 @@ class Landing(Model): r [ft] radius of roundout maneuver Vs [kts] stall velocity nz 1.25 [-] load factor - Xla [ft] total landing distance + Xla [ft] total landing distance mu_b 0.8 [-] braking friction coefficient Sgr [ft] landing distance mstall 1.3 [-] stall @@ -716,7 +719,7 @@ def setup(self, aircraft,hybrid=False): t >= Sgr/(0.3*V) ] - return constraints, fs,perf + return constraints, fs,perf @@ -745,7 +748,7 @@ def setup(self,poweredwheels=False,n_wheels=3,hybrid=False): self.cruise = Cruise(self.aircraft,hybrid) self.reserve = Reserve(self.aircraft,hybrid) self.landing = Landing(self.aircraft,hybrid) - + Wcent = Variable("W_{cent}","lbf","center aircraft weight") loading = self.aircraft.loading(self.cruise.flightstate,Wcent) @@ -777,7 +780,7 @@ def setup(self,poweredwheels=False,n_wheels=3,hybrid=False): constraints += [self.aircraft.battery.E_capacity*0.8 >= sum(s.t*s.perf.batt_perf.P for s in self.fs)] with gpkit.SignomialsEnabled(): constraints += [R <= self.cruise.R] - return constraints,self.aircraft,self.fs, loading + return constraints,self.aircraft,self.fs, loading, state def writeSol(sol): with open('solve.txt', 'wb') as output: @@ -813,7 +816,7 @@ def CLCurves(): # # M.substitutions.update({M.aircraft.bw.CLmax:CLmax}) # sol = M.solve("mosek") # print sol(M.aircraft.mass) - + plt.grid() # plt.xlim([0,300]) # plt.ylim([0,1600]) @@ -898,7 +901,7 @@ def ElectricVsHybrid(): M.cost = M.aircraft.mass sol = M.localsolve("mosek") print sol.summary() - + plt.plot(sol(M.Srunway),sol(M.aircraft.mass),label='electric') M = Mission(poweredwheels=True,n_wheels=3,hybrid=True) @@ -924,7 +927,7 @@ def ICVsTurboshaft(): M.cost = M.aircraft.mass sol = M.localsolve("mosek") print sol.summary() - + plt.plot(sol(M.Srunway),sol(M.aircraft.mass),label='Powered wheels') M = Mission(poweredwheels=False,n_wheels=3,hybrid=True) @@ -957,11 +960,11 @@ def Runway(): plt.xlabel("Runway length [ft]") plt.ylabel("Takeoff mass [kg]") plt.grid() - plt.show() + plt.show() # CLCurves() # RangeRunway() # RangeSpeed() # SpeedSweep() # ElectricVsHybrid() # ICVsTurboshaft() -# Runway() \ No newline at end of file +# Runway()