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Airplane configuration scorecard
| Weight | Config. #1 | Config. #2 | Config. #3 | Config. #4 | |
|---|---|---|---|---|---|
| Safety | 0.5 | 3 | 3.5 | 2 | 4 |
| Performance | 0.3 | 4 | 4.5 | 4 | 3 |
| Appearance & handling | 0.2 | 4.5 | 3.5 | 4.5 | 2 |
| TOTAL WEIGHTED AVERAGE SCORE | 3.6 | 3.8 | 3.1 | 3.3 |
Comparison of moments of inertia_
| Aircraft | MTOW [kg] | Ixx [kg·m2] | Iyy [kg·m2] | Izz [kg·m2] | Ixx/MTOW | Iyy/MTOW | Izz/MTOW |
|---|---|---|---|---|---|---|---|
| Cessna 150 | 757.0 | 825.0 | 850.0 | 950.0 | 1.09 | 1.12 | 1.26 |
| DA20 Katana | 780.0 | 325.0 | 900.0 | 1100.0 | 0.42 | 1.15 | 1.41 |
| One pilot, 55 kg | 518.6 | 604.6 | 739.6 | 1288.4 | 1.17 | 1.43 | 2.48 |
| Two pilots, 110 kg each | 683.6 | 599.2 | 788.4 | 1331.1 | 0.88 | 1.15 | 1.95 |
Weight estimation summary_
| COMPONENT | Weight [kg] | AVERAGE | |||
|---|---|---|---|---|---|
| Electric motor | 9.54 | 9.54 | |||
| Fuel cell stack | 50.31 | 50.31 | |||
| Hydrogen tank with fuel | 104.71 | 104.71 | |||
| Battery packs | 10.59 | 10.59 | |||
| Propeller | 11.34 | 11.34 | |||
| ALL POWERPLANT | 186.50 | 186.50 | |||
| Method #1 Sadraey | Method #2 Raymer | Method #3 Roskam/Cessna | Method #4 Roskam/USAF | ||
| Wing | 54.6 | 85.27 | 138.16 | 72.17 | 87.55 |
| Horizontal stabilizer | 65.5 | 15.51 | 10.92 | 20.65 | 28.15 |
| Vertical stabilizer | 13.5 | 4.85 | 4.42 | 5.56 | 7.08 |
| Fuselage | 99.6 | 43.81 | 31.39 | 60.61 | 58.86 |
| Main landing gear | 34.5 | 23.97 | 29.78 | 15.65 | 25.98 |
| Nose landing gear | 8.6 | 4.25 | 15.50 | 5.02 | 8.35 |
| ALL STRUCTURE | 276.39 | 177.66 | 230.17 | 179.66 | 215.97 |
| Flight control system | 7.61 | 10.08 | 43.50 | 20.40 | |
| Hydraulic and pneumatic systems | 0.73 | 0.60 | 0.67 | ||
| Electrical system | 10.04 | 42.77 | 16.08 | 33.63 | 25.63 |
| Avionics | 1.71 | 10.68 | 1.81 | 1.81 | 4.01 |
| Air conditioning and AI | 0.98 | 12.14 | 8.98 | 7.37 | |
| Cabin (seats and furnishings) | 24.25 | 5.44 | 13.89 | 24.25 | 16.96 |
| ALL EQUIPEMENT | 37.72 | 79.24 | 41.86 | 112.17 | 67.75 |
| STRUCTURE + EQUIPEMENT | 314.11 | 256.89 | 272.03 | 291.83 | 283.72 |
| STRUCTURE + EQUIPEMENT + POWERPLANT | 500.61 | 443.39 | 458.53 | 478.33 | 470.21 |
Airplane center of gravity and moments of inertia_
| CG position | Config. | Xcg [m] | Ycg [m] | Zcg [m] | Ixx [kg·m2] | Iyy [kg·m2] | Izz [kg·m2] | Ixy | Ixz | Iyz |
|---|---|---|---|---|---|---|---|---|---|---|
| Most forward | One pilot, 55 kg | 2.01 | −0.11 | 0.03 | 604.6 | 739.6 | 1288.4 | 9.53 | 7.49 | 0.93 |
| Most aft | Two pilots, 110 kg each | 2.102 | −0.1 | 0 | 599.2 | 788.4 | 1331.1 | 0.00 | 12.23 | 0.00 |
Results of training airplane trend analysis
| Parameter | Unit | Average | Min | Max | Standard deviation | Standard deviation as % of average |
|---|---|---|---|---|---|---|
| Length | m | 6.49 | 5.50 | 7.50 | 0.45 | 7% |
| Height | m | 2.30 | 1.70 | 2.96 | 0.26 | 11% |
| Wingspan | m | 9.20 | 7.55 | 13.00 | 0.96 | 10% |
| Wing chord | m | 1.28 | 0.88 | 1.65 | 0.19 | 15% |
| Aspect ratio | - | 7.45 | 5.00 | 14.10 | 1.62 | 22% |
| Wing area | m2 | 11.71 | 8.04 | 17.09 | 2.04 | 17% |
| Empty weight | kg | 343.3 | 200.0 | 658.0 | 91.1 | 27% |
| MTOW weight | kg | 580.2 | 431.0 | 1043.0 | 140.7 | 24% |
| Max wing loading | kg/m2 | 55.75 | 36.00 | 95.90 | 11.31 | 20% |
| Max power loading | kg/kW | 7.93 | 4.46 | 10.99 | 1.30 | 16% |
| Max rate of climb | m/min | 336.3 | 137.0 | 640.0 | 95.5 | 28% |
| Max level speed | km/h | 231.4 | 169.0 | 375.0 | 40.0 | 17% |
| Cruise speed | km/h | 204.0 | 120.0 | 332.0 | 37.4 | 18% |
| Stall speed | km/h | 75.8 | 52.0 | 130.0 | 12.3 | 16% |
| Range | km | 1054 | 424 | 2055 | 359 | 34% |
| Endurance | h | 5.68 | 3.00 | 14.00 | 2.06 | 36% |
| Power | kW | 81.11 | 44.69 | 156.57 | 26.92 | 33% |
| Wempty/WMTOW | - | 0.592 | 0.437 | 0.747 | 0.058 | 10% |
Wing and stabilizer parameters
| Component | Area [m2] | MAC [m] | Span [m] | Profile | Taper ratio | Sweep angle [°] | Incidence angle [°] | Dihedral angle [°] | Volume coefficient |
|---|---|---|---|---|---|---|---|---|---|
| Wing | 13.04 | 1.32 | 9.85 | NACA 63(2)-415 | 1 | 0 | 1 | 4 | - |
| Horizonal stabilizer | 3.11 | 0.91 | 3.42 | NACA 0012 | 1 | 0 | 0 | 0 | 0.65 |
| Vertical stabilizer | 1.42 | 1.04 | 1.46 | FX-71-L-150/30 | 0.413 | 0 | 0 | 0 | 0.04 |
Fuel system weight estimation
| MTOW = 600 KG | ||||||
|---|---|---|---|---|---|---|
| Airplane structure | Two pilots | Classical propulsion system | ||||
| Combustion engine | Fuel system | Fuel | ||||
| 62.23 kg | 12.92 kg | 100 kg | ||||
| 261.55 kg | 163.3 kg | Hydrogen-electric propulsion system | ||||
| Electric motor | Battery | Fuel cell stack | Hydrogen tank | Hydrogen | ||
| 9.66 kg | 10.6 kg | 50.3 kg | 98.3 kg | 6.275 kg | ||