Heat-Transfer Investigation of Langley Research Center Delta Wing Configurations at Mach Numbers 8 and 10.5
Final rept. Jun-Sep 1971
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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Heat-transfer tests for two simple delta wing configurations submitted by NASA-Langley Research Center were conducted at Mach numbers 8 and 10.5. Test conditions provided both Mach number and Reynolds number simulation for typical lifting body reentry trajectories. This report presents the major test results and comparisons with theoretical calculations. Specific test results include heat-transfer distributions, shock angles, limited pressure measurements, and boundary-layer transition results.
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry