karoliina-salminens-imac:zyggerdesigner karoliina$ ./zyggerdesigner Zyggerdesigner aircraft initial sizing program This program is intended for preliminary design phase in conceptual design method. (C) 2008 Karoliina Salminen, All rights reserved. karoliina.t.salminen at gmail.com http://karoliinasalminen.wordpress.com, http://designaplane.blogspot.com This program is licensed under GPL version 3 or any later version of the license. Type help for list of commands D/q not set, Cd0 not recalculated, using set Cd0 value. Iterating for stall speed (Vs known, W/S not known) D/q not set, Cd0 not recalculated, using set Cd0 value. AR = 14 ARtail = 5 ratio B = 38.8791 ft B_m = 11.8503 m Btail = 5.82939 ft Btail_m = 1.7768 m Cd0 = 0.025 Clcruise = 0.450054 Clmax = 2 D = -1.42543e-214 lbs D/q = -9.25124e-216 D< = 200.138 lbs Emax = 17.2302 K = 0.0336836 L/Dmax = 17.2302 Loadtot = 962.28 lbs RCmax = 19.0013 ft/s RCmax_ftmin = 1140.08 ft/min RCmax_single_ftmin = 252.74 ft/min RCmax_singleengine = 4.21233 ft/s S = 107.97 sqft SFC = 0.458 S_m2 = 10.0308 m^2 Sv = 6.79635 sqft Sv_m2 = 0.631401 m^2 T = 200.138 lbs TavailTO = 630.063 lbs TavailTO_kg = 286.392 kg TavailTO_single = 315.032 lbs TavailTO_single_kg = 143.196 kg V = 170 kts VRCmax = 157.782 ft/s VRCmax_kts = 93.3621 kts V_ms = 87.569 m/s Vapproach = 70.2 kts Vapproach_km/h = 129.87 km/h Vapproach_ms = 36.1609 m/s Vbestglide = 98.1606 kts Vfeet = 287.3 ft/s Vr = 129.179 Vs = 54 kts Vs_ms = 27.816 m/s Vv = 0.034 W/P = 13.9462 lbs/hp W/S = 19.8055 lbs/sqft We = 1176.12 lbs We_kg = 534.6 kg Wfuel = 427.68 lbs Wg = 2138.4 lbs Wg_kg = 972 kg Wseat = 178.2 lbs airframetoweight = 0.55 ratio alpha = 0.0818609 altitude = 25000 ft areatemp = 12.8834 bhpcruise = 99.6659 hp chord = 2.77708 ft chord_m = 0.846453 m chordtail = 1.16588 ft chordtail_m = 0.355359 m climbangle = 6.05762 degrees consumption = 29.2234 l/h cruise% = 0.65 cruisestallratio = 2.83948 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 9.36929 h flatplatedrag = 2.69925 sqft fuelflow = 45.647 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 3.83724e+07 SL Re hpavail = 153.332 hp hpavailsingle = 76.6661 hp hpperengine = 76.6661 hp lengthfuselage = 21.0002 ft lv = 21.0002 ft lv_is_unset = 1 flag lv_m = 6.40085 nengines = 2 pcs nmpg = 22.1056 nm/gal nseats = 3 pcs propeff = 0.75 q = 15.408 radclimbangle = 0.105725 rad range = 1592.78 nm rho = 0.0010663 seatw = 81 kg tail_Re_Vapproach = 879705 SL Re tail_Re_Vcruise = 2.13034e+06 SL Re tail_Re_Vs = 676696 SL Re thpreq = 74.7494 hp tothp = 153.332 hp usefulload = 534.6 lbs usefulload_kg = 243 kg usefulloadratio = 0.25 wing_Re_Vapproach = 2.09543e+06 wing_Re_Vcruise = 5.07439e+06 SL Re wing_Re_Vs = 1.61187e+06 warning: this program uses gets(), which is unsafe. > nseats nseats = 3 pcs {nseats} [pcs] (default = 3 ) = 2 nseats = 2 pcs > seatw seatw = 81 kg {seatw} [kg] (default = 81 ) = 100 seatw = 100 kg > airframetoweight airframetoweight = 0.55 ratio {airframetoweight} [ratio] (default = 0.55 ) = 0.60 airframetoweight = 0.6 ratio > weights reiterating weights > V V = 170 kts {V} [kts] (default = 170 ) = 145 V = 145 kts > altitude altitude = 25000 ft {altitude} [ft] (default = 25000 ) = 100 altitude = 100 ft > D/q D/q = -9.25124e-216 {D/q} [] (default = -9.25124e-216 ) = 2.2 D/q = 2.2 AR = 14 ARtail = 5 ratio B = 38.8791 ft B_m = 11.8503 m Btail = 5.82939 ft Btail_m = 1.7768 m Cd0 = 0.020376 Clcruise = 0.450054 Clmax = 2 D = -1.42543e-214 lbs D/q = 2.2 D< = 200.138 lbs Emax = 17.2302 K = 0.0336836 L/Dmax = 17.2302 Loadtot = 962.28 lbs RCmax = 19.0013 ft/s RCmax_ftmin = 1140.08 ft/min RCmax_single_ftmin = 252.74 ft/min RCmax_singleengine = 4.21233 ft/s S = 107.97 sqft SFC = 0.458 S_m2 = 10.0308 m^2 Sv = 6.79635 sqft Sv_m2 = 0.631401 m^2 T = 200.138 lbs TavailTO = 630.063 lbs TavailTO_kg = 286.392 kg TavailTO_single = 315.032 lbs TavailTO_single_kg = 143.196 kg V = 145 kts VRCmax = 157.782 ft/s VRCmax_kts = 93.3621 kts V_ms = 87.569 m/s Vapproach = 70.2 kts Vapproach_km/h = 129.87 km/h Vapproach_ms = 36.1609 m/s Vbestglide = 98.1606 kts Vfeet = 287.3 ft/s Vr = 129.179 Vs = 54 kts Vs_ms = 27.816 m/s Vv = 0.034 W/P = 13.9462 lbs/hp W/S = 19.8055 lbs/sqft We = 1320 lbs We_kg = 600 kg Wfuel = 427.68 lbs Wg = 2200 lbs Wg_kg = 1000 kg Wseat = 220 lbs airframetoweight = 0.6 ratio alpha = 0.0818609 altitude = 100 ft areatemp = 12.8834 bhpcruise = 99.6659 hp chord = 2.77708 ft chord_m = 0.846453 m chordtail = 1.16588 ft chordtail_m = 0.355359 m climbangle = 6.05762 degrees consumption = 29.2234 l/h cruise% = 0.65 cruisestallratio = 2.83948 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 9.36929 h flatplatedrag = 2.69925 sqft fuelflow = 45.647 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 3.83724e+07 SL Re hpavail = 153.332 hp hpavailsingle = 76.6661 hp hpperengine = 76.6661 hp lengthfuselage = 21.0002 ft lv = 21.0002 ft lv_is_unset = 1 flag lv_m = 6.40085 nengines = 2 pcs nmpg = 22.1056 nm/gal nseats = 2 pcs propeff = 0.75 q = 15.408 radclimbangle = 0.105725 rad range = 1592.78 nm rho = 0.0010663 seatw = 100 kg tail_Re_Vapproach = 879705 SL Re tail_Re_Vcruise = 2.13034e+06 SL Re tail_Re_Vs = 676696 SL Re thpreq = 74.7494 hp tothp = 153.332 hp usefulload = 440 lbs usefulload_kg = 200 kg usefulloadratio = 0.2 wing_Re_Vapproach = 2.09543e+06 wing_Re_Vcruise = 5.07439e+06 SL Re wing_Re_Vs = 1.61187e+06 > V V = 145 kts {V} [kts] (default = 145 ) = 130 V = 130 kts > iter W/S Iterating for wing loading (W/S known, Vs not known) AR = 14 ARtail = 5 ratio B = 39.4351 ft B_m = 12.0198 m Btail = 5.93546 ft Btail_m = 1.80913 m Cd0 = 0.020376 Clcruise = 0.497964 Clmax = 2 D = 30.6363 lbs D/q = 2.2 D< = 164.611 lbs Emax = 19.0854 K = 0.0336836 L/Dmax = 19.0854 Loadtot = 880 lbs RCmax = 9.99892 ft/s RCmax_ftmin = 599.935 ft/min RCmax_single_ftmin = 57.4599 ft/min RCmax_singleengine = 0.957665 ft/s S = 111.08 sqft SFC = 0.458 S_m2 = 10.3197 m^2 Sv = 7.04595 sqft Sv_m2 = 0.65459 m^2 T = 164.611 lbs TavailTO = 396.285 lbs TavailTO_kg = 180.13 kg TavailTO_single = 198.143 lbs TavailTO_single_kg = 90.0649 kg V = 130 kts VRCmax = 133.574 ft/s VRCmax_kts = 79.0382 kts V_ms = 66.9646 m/s Vapproach = 70.2 kts Vapproach_km/h = 129.87 km/h Vapproach_ms = 36.1609 m/s Vbestglide = 75.064 kts Vfeet = 219.7 ft/s Vr = 98.7842 Vs = 54 kts Vs_ms = 27.816 m/s Vv = 0.034 W/P = 22.8121 lbs/hp W/S = 19.8055 lbs/sqft We = 1320 lbs We_kg = 600 kg Wfuel = 440 lbs Wg = 2200 lbs Wg_kg = 1000 kg Wseat = 220 lbs airframetoweight = 0.6 ratio alpha = 0.0905753 altitude = 100 ft areatemp = 13.0059 bhpcruise = 62.686 hp chord = 2.81679 ft chord_m = 0.858558 m chordtail = 1.18709 ft chordtail_m = 0.361826 m climbangle = 4.21254 degrees consumption = 18.3804 l/h cruise% = 0.65 cruisestallratio = 1.78593 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 15.3256 h flatplatedrag = 2.26337 sqft fuelflow = 28.7102 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 2.95359e+07 SL Re hpavail = 96.44 hp hpavailsingle = 48.22 hp hpperengine = 48.22 hp lengthfuselage = 21.1378 ft lv = 21.1378 ft lv_is_unset = 1 flag lv_m = 6.4428 nengines = 2 pcs nmpg = 26.8764 nm/gal nseats = 2 pcs propeff = 0.75 q = 13.9256 radclimbangle = 0.0735228 rad range = 1992.32 nm rho = 0.001648 seatw = 100 kg tail_Re_Vapproach = 895713 SL Re tail_Re_Vcruise = 1.65873e+06 SL Re tail_Re_Vs = 689010 SL Re thpreq = 47.0145 hp tothp = 96.44 hp usefulload = 440 lbs usefulload_kg = 200 kg usefulloadratio = 0.2 wing_Re_Vapproach = 2.12539e+06 wing_Re_Vcruise = 3.93591e+06 SL Re wing_Re_Vs = 1.63492e+06 > V V = 130 kts {V} [kts] (default = 130 ) = 145 V = 145 kts > W/S W/S = 19.8055 lbs/sqft {W/S} [lbs/sqft] (default = 19.8055 ) = 16 W/S = 16 lbs/sqft > iter W/S Iterating for wing loading (W/S known, Vs not known) AR = 14 ARtail = 5 ratio B = 43.8748 ft B_m = 13.373 m Btail = 6.96552 ft Btail_m = 2.12309 m Cd0 = 0.0198055 Clcruise = 0.323358 Clmax = 2 D = 38.1141 lbs D/q = 2.2 D< = 213.595 lbs Emax = 19.3583 K = 0.0336836 L/Dmax = 19.3583 Loadtot = 880 lbs RCmax = 18.9565 ft/s RCmax_ftmin = 1137.39 ft/min RCmax_single_ftmin = 352.269 ft/min RCmax_singleengine = 5.87115 ft/s S = 137.5 sqft SFC = 0.458 S_m2 = 12.7742 m^2 Sv = 9.7037 sqft Sv_m2 = 0.901503 m^2 T = 213.595 lbs TavailTO = 638.113 lbs TavailTO_kg = 290.051 kg TavailTO_single = 319.056 lbs TavailTO_single_kg = 145.026 kg V = 145 kts VRCmax = 120.913 ft/s VRCmax_kts = 71.5464 kts V_ms = 74.6912 m/s Vapproach = 63.0964 kts Vapproach_km/h = 116.728 km/h Vapproach_ms = 32.5017 m/s Vbestglide = 83.7252 kts Vfeet = 245.05 ft/s Vr = 110.182 Vs = 48.5357 kts Vs_ms = 25.0013 m/s Vv = 0.034 W/P = 15.7619 lbs/hp W/S = 16 lbs/sqft We = 1320 lbs We_kg = 600 kg Wfuel = 440 lbs Wg = 2200 lbs Wg_kg = 1000 kg Wseat = 220 lbs airframetoweight = 0.6 ratio alpha = 0.058816 altitude = 100 ft areatemp = 13.0059 bhpcruise = 90.7251 hp chord = 3.13392 ft chord_m = 0.955218 m chordtail = 1.3931 ft chordtail_m = 0.424618 m climbangle = 8.32325 degrees consumption = 26.6018 l/h cruise% = 0.65 cruisestallratio = 2.87576 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 10.5891 h flatplatedrag = 2.72325 sqft fuelflow = 41.5521 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 3.29439e+07 SL Re hpavail = 139.577 hp hpavailsingle = 69.7885 hp hpperengine = 69.7885 hp lengthfuselage = 21.1378 ft lv = 21.1378 ft lv_is_unset = 1 flag lv_m = 6.4428 nengines = 2 pcs nmpg = 20.7128 nm/gal nseats = 2 pcs propeff = 0.75 q = 17.3246 radclimbangle = 0.145268 rad range = 1535.42 nm rho = 0.001648 seatw = 100 kg tail_Re_Vapproach = 944790 SL Re tail_Re_Vcruise = 2.17119e+06 SL Re tail_Re_Vs = 726762 SL Re thpreq = 68.0438 hp tothp = 139.577 hp usefulload = 440 lbs usefulload_kg = 200 kg usefulloadratio = 0.2 wing_Re_Vapproach = 2.12539e+06 wing_Re_Vcruise = 4.8843e+06 SL Re wing_Re_Vs = 1.63492e+06 > V V = 145 kts {V} [kts] (default = 145 ) = 140 V = 140 kts > iter W/S Iterating for wing loading (W/S known, Vs not known) AR = 14 ARtail = 5 ratio B = 43.8748 ft B_m = 13.373 m Btail = 6.96552 ft Btail_m = 2.12309 m Cd0 = 0.016 Clcruise = 0.346867 Clmax = 2 D = 35.5309 lbs D/q = 2.2 D< = 168.892 lbs Emax = 21.5378 K = 0.0336836 L/Dmax = 21.5378 Loadtot = 880 lbs RCmax = 13.1405 ft/s RCmax_ftmin = 788.429 ft/min RCmax_single_ftmin = 189.031 ft/min RCmax_singleengine = 3.15051 ft/s S = 137.5 sqft SFC = 0.458 S_m2 = 12.7742 m^2 Sv = 9.7037 sqft Sv_m2 = 0.901503 m^2 T = 168.892 lbs TavailTO = 487.165 lbs TavailTO_kg = 221.439 kg TavailTO_single = 243.583 lbs TavailTO_single_kg = 110.719 kg V = 140 kts VRCmax = 127.538 ft/s VRCmax_kts = 75.4665 kts V_ms = 72.1157 m/s Vapproach = 63.0964 kts Vapproach_km/h = 116.728 km/h Vapproach_ms = 32.5017 m/s Vbestglide = 80.8381 kts Vfeet = 236.6 ft/s Vr = 106.383 Vs = 48.5357 kts Vs_ms = 25.0013 m/s Vv = 0.034 W/P = 20.6457 lbs/hp W/S = 16 lbs/sqft We = 1320 lbs We_kg = 600 kg Wfuel = 440 lbs Wg = 2200 lbs Wg_kg = 1000 kg Wseat = 220 lbs airframetoweight = 0.6 ratio alpha = 0.0630922 altitude = 100 ft areatemp = 13.0059 bhpcruise = 69.2638 hp chord = 3.13392 ft chord_m = 0.955218 m chordtail = 1.3931 ft chordtail_m = 0.424618 m climbangle = 5.99581 degrees consumption = 20.3091 l/h cruise% = 0.65 cruisestallratio = 2.19549 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 13.8701 h flatplatedrag = 2.2 sqft fuelflow = 31.7228 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 3.18079e+07 SL Re hpavail = 106.56 hp hpavailsingle = 53.2799 hp hpperengine = 53.2799 hp lengthfuselage = 21.1378 ft lv = 21.1378 ft lv_is_unset = 1 flag lv_m = 6.4428 nengines = 2 pcs nmpg = 26.1951 nm/gal nseats = 2 pcs propeff = 0.75 q = 16.1504 radclimbangle = 0.104647 rad range = 1941.82 nm rho = 0.001648 seatw = 100 kg tail_Re_Vapproach = 944790 SL Re tail_Re_Vcruise = 2.09633e+06 SL Re tail_Re_Vs = 726762 SL Re thpreq = 51.9479 hp tothp = 106.56 hp usefulload = 440 lbs usefulload_kg = 200 kg usefulloadratio = 0.2 wing_Re_Vapproach = 2.12539e+06 wing_Re_Vcruise = 4.71588e+06 SL Re wing_Re_Vs = 1.63492e+06 > airframetoweight airframetoweight = 0.6 ratio {airframetoweight} [ratio] (default = 0.6 ) = 0.58 airframetoweight = 0.58 ratio > weights reiterating weights > iter W/S Iterating for wing loading (W/S known, Vs not known) AR = 14 ARtail = 5 ratio B = 41.833 ft B_m = 12.7507 m Btail = 6.55646 ft Btail_m = 1.99841 m Cd0 = 0.016 Clcruise = 0.346867 Clmax = 2 D = 35.5309 lbs D/q = 2.2 D< = 153.538 lbs Emax = 21.5378 K = 0.0336836 L/Dmax = 21.5378 Loadtot = 840 lbs RCmax = 13.1405 ft/s RCmax_ftmin = 788.429 ft/min RCmax_single_ftmin = 189.031 ft/min RCmax_singleengine = 3.15051 ft/s S = 125 sqft SFC = 0.458 S_m2 = 11.6129 m^2 Sv = 8.59743 sqft Sv_m2 = 0.798727 m^2 T = 153.538 lbs TavailTO = 442.878 lbs TavailTO_kg = 201.308 kg TavailTO_single = 221.439 lbs TavailTO_single_kg = 100.654 kg V = 140 kts VRCmax = 127.538 ft/s VRCmax_kts = 75.4665 kts V_ms = 72.1157 m/s Vapproach = 63.0964 kts Vapproach_km/h = 116.728 km/h Vapproach_ms = 32.5017 m/s Vbestglide = 80.8381 kts Vfeet = 236.6 ft/s Vr = 106.383 Vs = 48.5357 kts Vs_ms = 25.0013 m/s Vv = 0.034 W/P = 20.6457 lbs/hp W/S = 16 lbs/sqft We = 1160 lbs We_kg = 527.273 kg Wfuel = 400 lbs Wg = 2000 lbs Wg_kg = 909.091 kg Wseat = 220 lbs airframetoweight = 0.58 ratio alpha = 0.0630922 altitude = 100 ft areatemp = 12.5992 bhpcruise = 62.9671 hp chord = 2.98807 ft chord_m = 0.910764 m chordtail = 1.31129 ft chordtail_m = 0.399682 m climbangle = 5.99581 degrees consumption = 18.4628 l/h cruise% = 0.65 cruisestallratio = 1.9959 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 13.8701 h flatplatedrag = 2 sqft fuelflow = 28.8389 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 3.11182e+07 SL Re hpavail = 96.8725 hp hpavailsingle = 48.4362 hp hpperengine = 48.4362 hp lengthfuselage = 20.6795 ft lv = 20.6795 ft lv_is_unset = 1 flag lv_m = 6.3031 nengines = 2 pcs nmpg = 28.8147 nm/gal nseats = 2 pcs propeff = 0.75 q = 16.1504 radclimbangle = 0.104647 rad range = 1941.82 nm rho = 0.001648 seatw = 100 kg tail_Re_Vapproach = 889305 SL Re tail_Re_Vcruise = 1.97322e+06 SL Re tail_Re_Vs = 684081 SL Re thpreq = 47.2253 hp tothp = 96.8725 hp usefulload = 440 lbs usefulload_kg = 200 kg usefulloadratio = 0.22 wing_Re_Vapproach = 2.02648e+06 wing_Re_Vcruise = 4.49641e+06 SL Re wing_Re_Vs = 1.55883e+06 > airframetoweight airframetoweight = 0.58 ratio {airframetoweight} [ratio] (default = 0.58 ) = 0.57 airframetoweight = 0.57 ratio > weights reiterating weights > iter W/S Iterating for wing loading (W/S known, Vs not known) AR = 14 ARtail = 5 ratio B = 40.9135 ft B_m = 12.4704 m Btail = 6.37398 ft Btail_m = 1.94279 m Cd0 = 0.0176 Clcruise = 0.346867 Clmax = 2 D = 35.5309 lbs D/q = 2.2 D< = 159.204 lbs Emax = 20.5355 K = 0.0336836 L/Dmax = 20.5355 Loadtot = 822.609 lbs RCmax = 14.6546 ft/s RCmax_ftmin = 879.275 ft/min RCmax_single_ftmin = 229.506 ft/min RCmax_singleengine = 3.8251 ft/s S = 119.565 sqft SFC = 0.458 S_m2 = 11.108 m^2 Sv = 8.12552 sqft Sv_m2 = 0.754885 m^2 T = 159.204 lbs TavailTO = 459.221 lbs TavailTO_kg = 208.737 kg TavailTO_single = 229.611 lbs TavailTO_single_kg = 104.369 kg V = 140 kts VRCmax = 124.535 ft/s VRCmax_kts = 73.6895 kts V_ms = 72.1157 m/s Vapproach = 63.0964 kts Vapproach_km/h = 116.728 km/h Vapproach_ms = 32.5017 m/s Vbestglide = 80.8381 kts Vfeet = 236.6 ft/s Vr = 106.383 Vs = 48.5357 kts Vs_ms = 25.0013 m/s Vv = 0.034 W/P = 19.0452 lbs/hp W/S = 16 lbs/sqft We = 1090.43 lbs We_kg = 495.652 kg Wfuel = 382.609 lbs Wg = 1913.04 lbs Wg_kg = 869.565 kg Wseat = 220 lbs airframetoweight = 0.57 ratio alpha = 0.0630922 altitude = 100 ft areatemp = 12.4139 bhpcruise = 65.2908 hp chord = 2.92239 ft chord_m = 0.890745 m chordtail = 1.2748 ft chordtail_m = 0.388558 m climbangle = 6.59451 degrees consumption = 19.1442 l/h cruise% = 0.65 cruisestallratio = 2.06956 descrption: Default values are high efficiency, Rotax 914 turbo, cruise at 25000 feet = 0 e = 0.9 endurance = 12.7949 h flatplatedrag = 2.10435 sqft fuelflow = 29.9032 lbs/h fueltoweight = 0.2 ratio fuelweight = 0.71 kg/l fuselage_Re_Vcruise = 3.08017e+07 SL Re hpavail = 100.447 hp hpavailsingle = 50.2237 hp hpperengine = 50.2237 hp lengthfuselage = 20.4691 ft lv = 20.4691 ft lv_is_unset = 1 flag lv_m = 6.23899 nengines = 2 pcs nmpg = 27.7891 nm/gal nseats = 2 pcs propeff = 0.75 q = 16.1504 radclimbangle = 0.115096 rad range = 1791.29 nm rho = 0.001648 seatw = 100 kg tail_Re_Vapproach = 864554 SL Re tail_Re_Vcruise = 1.9183e+06 SL Re tail_Re_Vs = 665042 SL Re thpreq = 48.9681 hp tothp = 100.447 hp usefulload = 440 lbs usefulload_kg = 200 kg usefulloadratio = 0.23 wing_Re_Vapproach = 1.98194e+06 wing_Re_Vcruise = 4.39758e+06 SL Re wing_Re_Vs = 1.52457e+06