Analysis of Nosetip Boundary Layer Transition Mechanisms
FLOW RESEARCH INC KENT WA
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Linear stability theory is being used to investigate the mechanisms which lead to boundary layer transition on re-entry vehicle nosetips. Specific efforts are aimed at determining the effects of various parameters including surface roughness, ablation, wall cooling, local Mach numbers, pressure gradient, and axisymmetric geometry on transition. Roughness is simulated by means of the turbulent sublayer model which has been extended to compressible flow. Results indicate that both roughness and ablation strongly reduce the transition Reynolds number. A series of parametric stability solutions has been calculated for non-zero pressure gradient cases. Thus far, rough-wall solutions have been completed only near the stagnation point where the boundary layer is still stable to all disturbances.
- Guided Missile Trajectories, Accuracy and Ballistics
- Fluid Mechanics