Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber
Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber
- New search for: Vincent, K. R.
- New search for: Gale, B. M.
- New search for: Vincent, K. R.
- New search for: Gale, B. M.
An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet. Performance of the engine at any flight Mach number in the range investigated can be predicted for those operating condition a t which critical flow exits in the exhaust nozzle with the exception of the variables corrected net thrust, and net-thrust specific fuel consumption.
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Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber
1951-01-03
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English