I am trying to create a math model for the IVP.
The model uses the following critical parameters:
75% power = 262.5BHP, zero lift drag coefficient = .02, propeller efficiency range = .87-.80, and
gross weight = 2900 lbs.
The model predicts the following
Fuel flow @ 75% power = 17.5 GPH and 75% power speed vs ISA
altitude:
|
ALTITUDE FT |
TAS KTS |
|
0 |
218.5 |
|
2500 |
223 |
|
5000 |
227.5 |
|
7500 |
233 |
|
10000 |
238 |
|
12500 |
242 |
|
15000 |
247 |
|
17500 |
252 |
|
20000 |
257 |
|
22500 |
262 |
Is
this consistent with experience? I’d be interested in any other data such as ROC
and speed at these or other weights and power settings.
Thanks,
Carl