Measurements of Scramjet Thrust in Shock Tunnels

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Measurements of Scramjet Thrust in Shock Tunnels

Measurements of Scramjet Thrust in Shock Tunnels

R. J. Stalker / J. M. Simmons / A. Paull / D. J. Mee

By using results obtained in tests on supersonic combustion of hydrogen in air, the conditions governing model size and operating pressure levels for shock tunnel experiments on models of flight vehicles with scramjet propulsion are established. It is seen that large models are required. The development of the stress wave force balance is then described, and its use as a method of measuring thrust/drag on such models is discussed. Test results on a simple, fully integrated scramjet model, with intakes, combustion chambers, thrust surfaces and exterior surfaces, using a 13 percent silane 87 percent hydrogen fuel mixture, showed that a steady state with thrust generation could be achieved within the shock tunnel test time, and the thrust could be measured. Results are presented for a range of stagnation enthalpies, and show that the scramjet model produces net positive thrust at velocities up to 2.4 km/sec.

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Title :

Measurements of Scramjet Thrust in Shock Tunnels

Contributors:

R. J. Stalker (author) / J. M. Simmons (author) / A. Paull (author) / D. J. Mee (author)

Publication date :

1995

Size :

11 pages

Type of media :

Report

Type of material :

No indication

Language :

English

Keywords :

Jet & Gas Turbine Engines , Aerodynamics , Force distribution , Scale models , Shock tunnels , Steady state , Stress waves , Thrust loads , Thrust measurement , Wind tunnel tests , Aerodynamic drag , Combustion chambers , Drag measurement , Enthalpy , Hydrogen fuels , Pressure distribution , Silanes , Supersonic combustion , Supersonic combustion ramjet engines , Foreign technology

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