2+2 Place Personal Air Vehicle Performance
Civilian 200 HP Diesel Version w/ 34' Wingspan & Rotor Diameter
- Turbo Delta Hawk Engine - 200 HP to 17.5K ft
- 34 ft Wing Span & Rotor Diameter
- 2400 lb Gross Weight
- 1000 lb Empty Weight
- 400 lb Max Fuel
- 4 Place
Note: Program solves for speed based on given horsepower available at each altitude and the given inputs.
Also note how the mpg and range increase at the higher altitudes with minimal effect on speed (requires a pressurized cabin).
Performance calulation for Max Speed
Calculated Results:
| Altitude |
0 |
7.5K |
10K |
15K |
20K |
25K |
| Air Density |
0.00238 |
0.001898 |
0.001756 |
0.001496 |
0.001267 |
0.001065 |
| Vel (ft/s) |
260 |
280 |
287 |
302 |
308 |
303 |
| Vel (mph) |
177 |
191 |
195 |
206 |
210 |
206 |
| CL |
0.25 |
0.27 |
0.28 |
0.30 |
0.35 |
0.44 |
| Profile HP |
163.39 |
162.14 |
161.61 |
160.38 |
144.25 |
115.41 |
| Induced HP |
11.90 |
13.88 |
14.63 |
16.32 |
18.89 |
22.84 |
| Rotor HP |
24.70 |
23.99 |
23.76 |
23.30 |
20.86 |
16.75 |
| Engine HP Req'd |
200.00 |
200.00 |
200.00 |
200.00 |
184.00 |
155.00 |
| Engine HP Available |
200.00 |
200.00 |
200.00 |
200.00 |
184.00 |
155.00 |
| Total Drag |
359.08 |
333.85 |
325.66 |
309.51 |
279.10 |
239.01 |
| MPG |
12.77 |
13.74 |
14.08 |
14.82 |
16.43 |
19.19 |
| L/D |
6.68 |
7.19 |
7.37 |
7.75 |
8.60 |
10.04 |
| Range |
903 |
972 |
996 |
1048 |
1162 |
1357 |
| Rotor Flate Plate |
0.65 |
0.63 |
0.63 |
0.62 |
0.62 |
0.62 |
| Total Flat Plate |
4.28 |
4.27 |
4.26 |
4.26 |
4.25 |
4.26 |
Input Variables and Assumptions:
| AWD= |
86 |
|
AREA WING DRAG -SQ FT; |
| AWL= |
100 |
|
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= |
34 |
|
SPAN - FT. |
| RD= |
34 |
|
ROTOR DIA. - FT. |
| AB= |
34 |
|
AREA OF BLADES - SQ FT |
| RPMR= |
135 |
|
RPM - ROTOR |
| P.E.= |
0.85 |
|
PROP EFF. |
| HP SL= |
200 |
|
HORSEPOWER AVAILABLE @ SEA LEVEL |
| BSFC= |
0.43 |
|
BRAKE SPECFIC FUEL CONSUMPTION |
| WTG= |
2,400 |
|
WEIGHT GROSS - LBS |
| WTE= |
2,000 |
|
WEIGHT LANDING - LBS |
Return to 2+2 Place Personal Air Vehicle & UAV
|
Home
