Abstract
Combustion tests of a scramjet engine were conducted to obtain thrust, lift, and pitching moment essential for evaluation of the engine’s basic performance and for determination of the requirements to control the system of integrated engine and body. The engine was a side-compression type with a swept-back angle of 45 deg, and the inlet was open on the cowl side. Thrust, lift, and pitching moment were measured safely by a force measuring system under Mach 4, 6, and 8 simulated ight conditions including engine unstart. Measurements changed with transition of combustion conditions.Thrust decreased and lift increased suddenlywhen the engine fell into unstart conditions in theM6 andM8 tests although the changewas gradual in theM4 tests. Effects of engine con gurations were also investigated. Installation of a full-height strut improved combustion performance but increased drag more than thrust.
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