FoilSim III 1.5b beta - 4 Sep 13 Joukowski Airfoil Camber = 5.0 % chord , Thickness = 12.5 % chord , Chord = 5.0 ft , Span = 20.0 ft , Angle of attack = 7.0 degrees , Standard Earth Atmosphere Ambient Pressure = 11.087lb/sq in, Ambient Velocity = 27 mph , Upper Surface X/c Y/c P V -0.508 0.072 11.074 44 -0.494 0.09 11.065 51 -0.469 0.107 11.065 51 -0.432 0.122 11.067 50 -0.385 0.133 11.069 48 -0.329 0.14 11.071 47 -0.265 0.142 11.073 45 -0.194 0.138 11.075 44 -0.119 0.129 11.077 42 -0.041 0.115 11.079 40 0.038 0.096 11.081 38 0.118 0.074 11.083 36 0.195 0.049 11.085 34 0.269 0.023 11.087 32 0.336 -0.001 11.089 30 0.394 -0.023 11.091 28 0.442 -0.041 11.092 26 0.475 -0.053 11.093 25 0.493 -0.06 11.094 24 Lower Surface -0.508 0.072 11.074 44 -0.508 0.053 11.095 22 -0.496 0.035 11.102 1 -0.47 0.019 11.099 14 -0.431 0.006 11.097 19 -0.38 -0.002 11.095 22 -0.316 -0.009 11.095 23 -0.241 -0.013 11.094 23 -0.157 -0.014 11.095 23 -0.066 -0.014 11.095 22 0.029 -0.014 11.095 22 0.126 -0.016 11.095 21 0.219 -0.02 11.096 21 0.305 -0.027 11.096 21 0.378 -0.036 11.096 21 0.435 -0.046 11.095 21 0.474 -0.055 11.095 22 0.493 -0.06 11.095 23 0.493 -0.06 11.094 24 Volume =9.536 cu ft Joukowski Airfoil Camber = 5.0 % chord , Thickness = 12.5 % chord , Chord = 5.0 ft , Span = 20.0 ft , Angle of attack = 7.0 degrees , Standard Earth Atmosphere Ambient Pressure = 11.087lb/sq in, Ambient Velocity = 27 mph , Upper Surface X/c Y/c P V -0.508 0.072 11.074 44 -0.494 0.09 11.065 51 -0.469 0.107 11.065 51 -0.432 0.122 11.067 50 -0.385 0.133 11.069 48 -0.329 0.14 11.071 47 -0.265 0.142 11.073 45 -0.194 0.138 11.075 44 -0.119 0.129 11.077 42 -0.041 0.115 11.079 40 0.038 0.096 11.081 38 0.118 0.074 11.083 36 0.195 0.049 11.085 34 0.269 0.023 11.087 32 0.336 -0.001 11.089 30 0.394 -0.023 11.091 28 0.442 -0.041 11.092 26 0.475 -0.053 11.093 25 0.493 -0.06 11.094 24 Lower Surface -0.508 0.072 11.074 44 -0.508 0.053 11.095 22 -0.496 0.035 11.102 1 -0.47 0.019 11.099 14 -0.431 0.006 11.097 19 -0.38 -0.002 11.095 22 -0.316 -0.009 11.095 23 -0.241 -0.013 11.094 23 -0.157 -0.014 11.095 23 -0.066 -0.014 11.095 22 0.029 -0.014 11.095 22 0.126 -0.016 11.095 21 0.219 -0.02 11.096 21 0.305 -0.027 11.096 21 0.378 -0.036 11.096 21 0.435 -0.046 11.095 21 0.474 -0.055 11.095 22 0.493 -0.06 11.095 23 0.493 -0.06 11.094 24 Volume =9.536 cu ft Joukowski Airfoil Camber = 5.0 % chord , Thickness = 12.5 % chord , Chord = 5.0 ft , Span = 20.0 ft , Surface Area = 100.0 sq ft , Angle of attack = 7.0 degrees , Standard Earth Atmosphere Altitude = 7600 ft , Density = 0.00189slug/cu ft Pressure = 11.087lb/sq in, Temperature = 31F, Airspeed = 27 mph , Lift = 202 lbs Drag = 32 lbs Joukowski Airfoil Camber = 5.0 % chord , Thickness = 12.286 % chord , Chord = 5.0 ft , Span = 55.099 ft , Angle of attack = 7.079 degrees , Standard Earth Atmosphere Ambient Pressure = 11.087lb/sq in, Ambient Velocity = 27 mph , Upper Surface X/c Y/c P V -0.507 0.072 11.072 45 -0.494 0.09 11.064 51 -0.468 0.107 11.064 51 -0.431 0.122 11.066 50 -0.384 0.133 11.069 48 -0.328 0.139 11.071 47 -0.264 0.141 11.073 45 -0.193 0.137 11.075 43 -0.118 0.128 11.077 42 -0.04 0.114 11.079 40 0.039 0.095 11.081 38 0.119 0.073 11.083 36 0.196 0.048 11.085 34 0.269 0.022 11.087 32 0.336 -0.002 11.089 30 0.394 -0.024 11.091 28 0.442 -0.042 11.092 27 0.475 -0.054 11.093 25 0.493 -0.06 11.094 24 Lower Surface -0.507 0.072 11.072 45 -0.508 0.054 11.095 22 -0.495 0.036 11.102 1 -0.47 0.021 11.099 13 -0.431 0.008 11.097 19 -0.379 -0.001 11.095 21 -0.315 -0.007 11.095 22 -0.24 -0.011 11.095 23 -0.156 -0.012 11.095 22 -0.064 -0.013 11.095 22 0.03 -0.013 11.095 22 0.127 -0.016 11.095 21 0.22 -0.02 11.096 21 0.306 -0.028 11.096 21 0.378 -0.037 11.096 21 0.436 -0.047 11.095 21 0.474 -0.055 11.095 22 0.493 -0.06 11.095 23 0.493 -0.06 11.094 24 Volume =25.832 cu ft Joukowski Airfoil Camber = 5.0 % chord , Thickness = 12.286 % chord , Chord = 5.0 ft , Span = 55.099 ft , Surface Area = 120.062 sq ft , Angle of attack = 7.079 degrees , Standard Earth Atmosphere Altitude = 7600 ft , Density = 0.00189slug/cu ft Pressure = 11.087lb/sq in, Temperature = 31F, Airspeed = 27 mph , Lift = 262 lbs Drag = 21 lbs Joukowski Airfoil Camber = 5.0 % chord , Thickness = 12.286 % chord , Chord = 0.15 m , Span = 1.2 m , Angle of attack = 7.079 degrees , Standard Earth Atmosphere Ambient Pressure = 100.902kPa, Ambient Velocity = 25 km/hr , Upper Surface X/c Y/c P V -0.507 0.072 100.888 41 -0.494 0.09 100.865 47 -0.468 0.107 100.866 46 -0.431 0.122 100.871 45 -0.384 0.133 100.877 44 -0.328 0.139 100.883 42 -0.264 0.141 100.889 41 -0.193 0.137 100.894 39 -0.118 0.128 100.9 38 -0.04 0.114 100.906 36 0.039 0.095 100.912 34 0.119 0.073 100.918 33 0.196 0.048 100.924 31 0.269 0.022 100.929 29 0.336 -0.002 100.933 27 0.394 -0.024 100.938 26 0.442 -0.042 100.941 24 0.475 -0.054 100.944 23 0.493 -0.06 100.947 22 Lower Surface -0.507 0.072 100.888 41 -0.508 0.054 100.949 20 -0.495 0.036 100.97 1 -0.47 0.021 100.962 12 -0.431 0.008 100.955 17 -0.379 -0.001 100.951 19 -0.315 -0.007 100.949 20 -0.24 -0.011 100.949 21 -0.156 -0.012 100.949 20 -0.064 -0.013 100.95 20 0.03 -0.013 100.951 20 0.127 -0.016 100.951 19 0.22 -0.02 100.952 19 0.306 -0.028 100.952 19 0.378 -0.037 100.952 19 0.436 -0.047 100.951 19 0.474 -0.055 100.95 20 0.493 -0.06 100.949 21 0.493 -0.06 100.947 22 Volume =0.016 cu m Joukowski Airfoil Camber = 5.0 % chord , Thickness = 10.0 % chord , Chord = 0.2 m , Span = 2.0 m , Surface Area = 0.4 sq m , Angle of attack = 0.0 degrees , Standard Earth Atmosphere Altitude = 75 m , Density = 1.216kg/cu m Pressure = 100.365kPa, Temperature = 14C, Airspeed = 35 km/hr , Lift = 14 Newtons Drag = 0 Newtons Joukowski Airfoil Camber = 5.0 % chord , Thickness = 10.0 % chord , Chord = 0.2 m , Span = 2.0 m , Surface Area = 0.4 sq m , Angle of attack = 3.0 degrees , Standard Earth Atmosphere Altitude = 75 m , Density = 1.216kg/cu m Pressure = 100.365kPa, Temperature = 14C, Airspeed = 30 km/hr , Lift = 16 Newtons Drag = 1 Newtons Joukowski Airfoil Camber = 5.0 % chord , Thickness = 10.0 % chord , Chord = 0.2 m , Span = 2.0 m , Surface Area = 0.4 sq m , Angle of attack = 3.0 degrees , Standard Earth Atmosphere Altitude = 75 m , Density = 1.216kg/cu m Pressure = 100.365kPa, Temperature = 14C, Airspeed = 30 km/hr , Lift = 16 Newtons Drag = 1 Newtons Joukowski Airfoil Camber = 5.0 % chord , Thickness = 10.0 % chord , Chord = 0.2 m , Span = 2.0 m , Angle of attack = 3.0 degrees , Standard Earth Atmosphere Ambient Pressure = 100.365kPa, Ambient Velocity = 30 km/hr , Upper Surface X/c Y/c P V -0.507 0.034 100.395 32 -0.494 0.051 100.36 42 -0.469 0.067 100.351 44 -0.433 0.082 100.35 45 -0.386 0.094 100.35 45 -0.329 0.104 100.352 44 -0.265 0.109 100.354 44 -0.194 0.11 100.358 43 -0.118 0.107 100.362 42 -0.039 0.099 100.367 40 0.041 0.087 100.372 39 0.122 0.072 100.378 38 0.2 0.055 100.383 36 0.273 0.036 100.389 34 0.34 0.018 100.394 33 0.398 0.001 100.399 31 0.445 -0.011 100.404 29 0.479 -0.02 100.407 28 0.496 -0.025 100.411 27 Lower Surface -0.507 0.034 100.395 32 -0.506 0.019 100.445 3 -0.492 0.005 100.43 18 -0.465 -0.004 100.414 25 -0.425 -0.012 100.408 28 -0.372 -0.016 100.407 28 -0.306 -0.016 100.408 28 -0.23 -0.014 100.409 27 -0.144 -0.009 100.411 27 -0.052 -0.004 100.413 26 0.043 0.0 100.415 25 0.139 0.001 100.416 24 0.231 0.0 100.417 24 0.315 -0.002 100.418 24 0.386 -0.008 100.417 24 0.441 -0.015 100.417 24 0.478 -0.021 100.415 25 0.497 -0.025 100.413 26 0.496 -0.025 100.411 27 Volume =0.03 cu m Joukowski Airfoil Camber = 5.0 % chord , Thickness = 10.0 % chord , Chord = 0.2 m , Span = 2.0 m , Surface Area = 0.4 sq m , Angle of attack = 3.0 degrees , Standard Earth Atmosphere Altitude = 75 m , Density = 1.216kg/cu m Pressure = 100.365kPa, Temperature = 14C, Airspeed = 30 km/hr , Lift = 16 Newtons Drag = 1 Newtons