Methods for calculating zero-fuel internal drag of scramjet engine modules from experimental measurements are presented. These methods include two control-volume approaches, and a pressure and skin-friction integration. The three calculation techniques are applied to experimental data taken during tests of a version of the NASA parametric scramjet. The methods agree to within seven percent of the mean value of zero-fuel internal drag even though several simplifying assumptions are made in the analysis. The mean zero-fuel internal drag coefficient for this particular engine is calculated to be 0.150. The zero-fuel internal drag coefficient when combined with the change in engine axial force with and without fuel defines the internal thrust of an engine.
Methods for determining the internal thrust of scramjet engine modules from experimental data
1990-07-01
Conference paper
No indication
English
Thrust, Lift, and Pitching Moment of a Scramjet Engine
AIAA | 2001
|Thrust, Lift and Pitching Moment of a Scramjet Engine
British Library Conference Proceedings | 1999
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