Thrust modeling for hypersonic enginesExpressions for the thrust losses of a scramjet engine are developed in terms of irreversible entropy increases and the degree of incomplete combustion. A method is developed which allows the calculation of the lost vehicle thrust due to different loss mechanisms within a given flow-field. This analysis demonstrates clearly the trade-off between mixing enhancement and resultant increased flow losses in scramjet combustors. An engine effectiveness parameter is defined in terms of thrust loss. Exergy and the thrust-potential method are related and compared.
Document ID
19950055811
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Riggins, D. W. (University of Missouri-Rolla, Rolla, MO United States)
Mcclinton, C. R. (NASA Langley Research Center Hampton, VA, United States)