2+2 Place Personal Air Vehicle Performance
200 HP Diesel Military UAV w/ 45' Wingspan & Rotor Diameter
- Turbo Delta Hawk Engine - 200 HP to 17.5K ft
- 45 ft Wing Span & Rotor Diameter
- 3000 lb Gross Weight
- 1200 lb Empty Weight
- 800 lb Useful Load
- 1000 lb Fuel
- Usually Unmanned, but Space for 4 Passengers
Note: Program solves for speed based on given horsepower available at each altitude and the given inputs.
Performance Calculation for Max Endurance
Calculated Results:
| Altitude |
0 |
10K |
15K |
17.5 |
20K |
25K |
| Air Density |
0.00238 |
0.001756 |
0.001496 |
0.001378 |
0.001267 |
0.001065 |
| Vel (ft/s) |
149 |
173 |
188 |
196 |
204 |
223 |
| Vel (mph) |
101 |
118 |
128 |
133 |
139 |
151 |
| CL |
0.9 |
0.9 |
0.9 |
0.9 |
0.9 |
0.9 |
| Profile HP |
31.77 |
36.98 |
40.07 |
41.75 |
43.54 |
47.49 |
| Induced HP |
18.56 |
21.61 |
23.41 |
24.4 |
25.44 |
27.75 |
| Rotor HP |
9.8 |
9.81 |
9.99 |
10.12 |
10.29 |
10.72 |
| Engine HP Req'd |
60.13 |
68.4 |
73.47 |
76.27 |
79.27 |
85.96 |
| Engine HP Available |
200.00 |
200.00 |
200.00 |
200.00 |
184.00 |
155.00 |
| Total Drag |
188.77 |
184.47 |
182.88 |
182.2 |
181.58 |
180.54 |
| MPG |
24.29 |
24.86 |
25.07 |
25.17 |
25.25 |
25.4 |
| L/D |
15.89 |
16.26 |
16.4 |
16.47 |
16.52 |
16.62 |
| Range |
4777 |
4888 |
4931 |
4949 |
4966 |
4995 |
| Rotor Flate Plate |
1.37 |
1.18 |
1.11 |
1.08 |
1.05 |
1 |
| Total Flat Plate |
5.15 |
4.96 |
4.89 |
4.86 |
4.83 |
4.78 |
Input Variables and Assumptions:
| AWD= |
104 |
|
AREA WING DRAG -SQ FT; R=55", T=12.3" |
| AWL= |
118 |
|
AREA WING LIFT - SQ FT |
| AHS= |
10.5 |
|
AREA HORIZONTAL STAB - SQ FT |
| AVS= |
16 |
|
AREA VERTICAL STAB - SQ FT |
| FW= |
190 |
|
FUSELAGE WETTED AREA - SQ FT |
| MW= |
5 |
|
MAST WETTED AREA - SQ FT |
| BW= |
40 |
|
TAIL BOOM WETTED AREA |
| LGW= |
20 |
|
LG NACELLE WETTED AREA |
| SPW= |
4 |
|
SPINNER WETTED AREA - SQ FT |
| CDR= |
0.012 |
|
COEFFICIENT OF DRAG (ROTOR) |
| CDA= |
0.008 |
|
COEFF DRAG AIRFOIL |
| CDW= |
0.004 |
|
COEFF DRAG WETTED |
| WDM= |
0.6 |
|
WING + LG DRAG MISC - FLATE PLATE SQ FT |
| CD= |
0.3 |
|
COOLING DRAG - FLATE PLATE SQ FT |
| FDM= |
0.6 |
|
FUSELAGE, PYLON, HUB DRAG MISC- FLATE PLATE SQ FT |
| TDM= |
0.2 |
|
TAIL DRAG MISC - FLATE PLATE SQ FT |
| VISC= |
3.74E-07 |
|
ABSOLUTE VISC COEFF- slug/(ft)(s) |
| MU= |
0.92 |
|
WING EFF |
| SPN= |
45 |
|
SPAN - FT. |
| RD= |
45 |
|
ROTOR DIA. - FT. |
| AB= |
50 |
|
AREA OF BLADES - SQ FT |
| RPMR= |
100 |
|
RPM - ROTOR |
| P.E.= |
0.85 |
|
PROP EFF. |
| HP SL= |
200 |
|
HORSEPOWER AVAILABLE @ SEA LEVEL |
| BSFC= |
0.43 |
|
BRAKE SPECFIC FUEL CONSUMPTION |
| WTG= |
3,000 |
|
WEIGHT GROSS - LBS |
| WTE= |
2,000 |
|
WEIGHT LANDING - LBS |
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