Finite Span Effects on Flap Heating and Effectiveness in a Turbulent Boundary Layer.
Final technical rept. May 78-Dec 80,
SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV
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An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. Author
- Fluid Mechanics