Shock-tube technique developed by Grumman Aircraft Engineering Corp simulates exhaust plumes and their effects on vehicles in space environment; helium driver gas expands behind detonation wave that propagates through combustible driven gas; initial conditions in shock tube can be adjusted to produce steady, uniform flow region behind detonation wave; after wave reflects from end wall of tube, stagnant, burned gas flows through nozzle into test chamber; density and velocity distributions, enthalpy, chemical constituency, full-scale Reynolds number, and hard vacuum background pressure are simulated simultaneously; facility, prerun calculations, instrumentation, and some results. (11877)
Detonation tube technique for simulating rocket plumes in space environment
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 10
1968
7 pages
Article (Journal)
English
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