Recent trip.
3400 lbs….IV-P
ISA +36 degF
17,500 ft alt
17.4/17.5 gph LOP
ROC ~800-1000 fpm, full rich,
2500 rpm, 32 in Hg, 165 kts IAS
Chelton TAS 260 kts
MT-4 blade prop
Engine is not stock. Custom
intercoolers and exhaust tailpipes for example.
Phoenix to Corpus Christi, TX
in 3 hr 40min. Landed with 32 gal fuel. 30 kt head wind most of the way.
Craig Berland
7VG
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