Mechanisms of Hypersonic Transition on a Generic Scramjet Forebody
Final rept. 15 Nov 1999-14 Nov 2002
PURDUE UNIV LAFAYETTE IN AEROSPACES SCIENCES LAB
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This grant supported measurements and computations of laminar-turbulent transition on a generic scramjet forebody. The computations, described in the appendix, were carried out under a subcontract. The experiments were carried out using the new BoeingAFOSR Mach-6 Quiet Tunnel BAM6QT Much of the experimental effort was expended in the first phase, completion and development of the necessary tunnel, which took longer than expected. Furthermore, although the tunnel was operational in April 2001, it is still not running quiet at significant Reynolds numbers. However, the tunnel is already successful at providing low-cost operation. The work carried out at Purdue has already been documented in a series of AIAA papers and other publications. Therefore, the present final report is a summary of past progress, current issues, and future plans. The appendix reports mean-flow and linear-stability results. Computations are reported for Stetsons blunt cone at zero angle of attack and Mach 8 and Maslovs blunt cone at Mach 6 In addition, preliminary computations are reported for more complex geometries.
- Fluid Mechanics
- Jet and Gas Turbine Engines