facts especially in the aviation industry. We burn fuel at an air ratio of
13:1-13:4 at the higher RPM ranges of our engine. As you are well aware fuel
usage is based on Lbs/hp/hr IE BSFC. Below I have copied results of engine
testing at an engineering school who is building an LSA with our single
rotor engine.

I also want to comment that fuel burn in aviation is a very important
calculation with many variables, Aircraft, Prop, Wind speed, Air Speed,
Temperature Etc. We would caution individuals that these calculations are
very critical when making flight plans and can vary greatly based on the
stated conditions above.

Our engine produces very flat torque and we believe more testing will
validate these tests below that show proper use of torque can and will lower
the required HP thus fuel consumption in an aircraft. We also only run the
engine to 6000 RPM Max as the operating range as it relates to max thrust
shown below is 5000 RPM Max. At the end of the day we would like to take off
at 5500 and cruise at 5000. Depending on the application take off at 5000
and cruise at 4500 provides very manageable engine program as it relates to
EGT, noise, cooling Etc this is a great range as the torque is flat
throughout this range.

Test results from engineering students using a 650cc normally aspirated
single rotor with a belt PSRU and a Kiev prop:

Eric,

Eric,
Is that fuel burn ratio's 13.1:1 to 13.4:1 at WOT?
George (down under)


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