The Numerical Solution of the Asymptotic Equations of Trailing Edge Flow.
Final rept. Jul 70-Dec 73,
AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
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The report presents numerical analysis which provides additional validation for the triple-deck flow structure at the trailing edge of a flat plate also, the constants required to complete the asymptotic expansions of Stewartson 1969 are determined. The results are self-consistent for the various grid sizes and numerical ranges employed for the computation. The present results have been demonstrated consistent with the previous numerical analyses of others and with the experimental data of Janour 1951 for the entire laminar range of Reynolds numbers.
- Fluid Mechanics