高温衝撃風洞スクラムジェット試験技術の評価(流体工学,流体機械)

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Large-scale scramjet combustion test was performed in the free-piston shock tunnel HIEST. For short test duration of order of msec, force measurement technique and fuel injection system were developed. The model scramjet of 2m length and of 143kg mass had integrated configuration, which includes sidewall compression inlet, parallel combustor and sidewall divergent nozzle. Thrust and pressure distribution of the model was measured under flow condition equivalent to flight Mach number 8. Gaseous hydrogen, which equivalence ratio was varied from 0.0 to 2.2 was used as fuel. In order to evaluate testing reliability, comparison with the vitiated air heating wind tunnel RJTF was conducted. The comparison showed un-start characteristics, thrust increment and wall pressure distribution were different between two facilities. A numerical simulation of three-dimensional Navier-Stokes code including combustion and additional wind tunnel tests in HIEST at different stagnation enthalpy were carried out to analyze these differences. The numerical study and the wind tunnel tests showed that (1) un-start characteristics was affected by facility-nozzle boundary layer, which was ingested into the model inlet and (2) thrust increment and pressure distribution was caused by difference of stagnation condition of the test flow between the two facilities. The test result demonstrated that scramjet ground testing with large scale model under hypervelocity flow condition can be performed with sufficient reliability for scramjet research.
一般社団法人日本機械学会の論文
2004-11-25

高温衝撃風洞スクラムジェット試験技術の評価(流体工学,流体機械)

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