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I'm attaching a turbo spreadsheet I was working with
last year. I modified this sheet some from the
original. The main page shows data for a rotary. The
second worksheet is for a turbo Continental I was
working with.
My changes mainly consisted of adding capability of
determining characteristics at different altitudes. I
added a line for the user to specify:
Altitude above sea level at airport
Temperature at airport (ground)
Barometric pressure at airport (ground)
Desired altitude for data calculations
Desired manifold pressure at engine
I added calculations to determine barometric pressure
and temperature at altitude. Most tables we see are
based on standard temperature and pressure. (How many
59 degree, 29.92 inHg days do we fly?) Therefore,
temperature and pressure at altitude are corrected to
ground. If you think this is hooey, just enter
standard temp and pressure and it should be pretty
close to the tables.
If you note, the first page shows a rotary at 1500 ft
on a hot day at 6500 rpm, turbo is normalized, running
rich for power. Then next two show altitude at 10,000
feet, one of them at 4500 rpm cruise at lean.
Theoretically burning 7.6 gph, but I'm guessing at the
volumetric effeciency of the engine.
Have fun!
Mike LaFleur
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