CarterCopter Technology Demonstrator Performance Prediction
Note: Program solves for speed based on given horsepower available at each altitude and the given inputs.
Note how the mpg and range increase at the higher altitudes with minimal effect on speed (requires a pressurized cabin). Also note that at 25k ft, the wing CL is right around what is realistically possible with that airfoil.
CCTD performance potential as of 2004-12-02 w/ 400 HP non turbo engine, rotor spinner & vortex generators to reduce the air separation over the lower rear section of the fuselage.
Calculated Results:
| ALTITUDE |
0 |
7.5K |
15K |
17.5 |
25K |
| RHO |
0.00238 |
0.001898 |
0.001496 |
0.001378 |
0.001065 |
| V - SOUND FPS |
1116 |
1087 |
1057 |
1047 |
1016 |
| VEL FPS |
292 |
287 |
277 |
272 |
238 |
VEL MPH
(true airspeed) |
199 |
195 |
188 |
185 |
162 |
| CL WING |
0.42 |
0.58 |
0.82 |
0.94 |
1.64 |
| PROFILE HP |
319.19 |
240.87 |
170.69 |
148.33 |
77.47 |
| INDUCED HP |
32.5 |
41.51 |
54.56 |
60.39 |
89.05 |
| ROTOR HP |
48.32 |
36.62 |
26.18 |
22.87 |
12.48 |
| HP REQD |
400 |
318.99 |
251.43 |
231.6 |
178.99 |
| HP AVAIL |
400 |
318.99 |
251.43 |
231.6 |
178.99 |
| DRAG-THRUST |
655.1 |
532.13 |
434.57 |
408.14 |
359.45 |
| MPG |
5.6 |
6.9 |
8.44 |
8.99 |
10.21 |
| L/D |
6.11 |
7.52 |
9.2 |
9.8 |
11.13 |
| RANGE |
282 |
348 |
426 |
453 |
515 |
Input Variables and Assumptions:
| AWD= |
60 |
|
AREA WING DRAG -SQ FT; R=2.33', T=1.0' |
| AWL= |
76 |
|
AREA WING LIFT - SQ FT |
| AHS= |
18 |
|
AREA HORIZONTAL STAB - SQ FT |
| AVS= |
30 |
|
AREA VERTICAL STAB (2) - SQ FT |
| FW= |
180 |
|
FUSELAGE WETTED AREA - SQ FT |
| MW= |
8 |
|
MAST WETTED AREA - SQ FT |
| BW= |
60 |
|
BOOM WETTED AREA - SQ FT |
| SPW= |
10 |
|
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= |
2 |
|
WING INTERF & FUSE SEP DRAG - FLATE PLATE SQ FT |
| CD= |
0.5 |
|
COOLING DRAG - FLATE PLATE SQ FT |
| FDM= |
0.5 |
|
HUB & PYLON DRAG MISC- FLATE PLATE SQ FT |
| TDM= |
0.25 |
|
TAIL DRAG MISC - FLATE PLATE SQ FT |
| MU= |
0.92 |
|
WING EFF |
| SPN= |
32 |
|
SPAN - FT. |
| RD= |
45 |
|
ROTOR DIA. - FT. |
| AB= |
50 |
|
AREA OF BLADES - SQ FT |
| RPMR= |
100 |
|
RPM - ROTOR |
| P.E.= |
0.87 |
|
PROP AND DRIVE EFF. |
| HP SL= |
400 |
|
HORSEPOWER AVAILABLE @ SEA LEVEL |
| BSFC= |
0.55 |
|
BRAKE SPECFIC FUEL CONSUMPTION |
| WTG= |
4,000 |
|
WEIGHT GROSS - LBS |
| WTE= |
3,700 |
|
WEIGHT LANDING - LBS |
| FIXED CL= |
0.80 |
|
COEFF LIFT |
Fixed Calculations:
| AR= |
13.47 |
|
WING ASPECT RATIO |
| FP= |
5.15 |
|
FLAT PLATE EQ. AREA W/O ROTOR - SQ FT |
| FPR= |
0.98 |
|
FLAT PLATE EQ. AREA ROTOR - SQ FT |
| TFP= |
6.13 |
|
TOTAL FLAT PLAT EQ. AREA - SQ FT |
| RSA= |
1590 |
|
ROTOR SWEPT AREA - SQ FT |
| RTS= |
236 |
|
ROTOR TIP SPEED - FPS |
| RDL= |
2.52 |
|
ROTOR DISK LOADING - #/SQ. Ft. @ 0 MPH & GROSS WT |
| WL= |
48.78 |
|
WING LOADING WITH ROTOR CARRYING SOME WT - #/sq. ft. |
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