Measurement of scramjet thrust in shock tunnels

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