Accession Number:

AD0755355

Title:

Heat-Transfer Investigation of Langley Research Center Delta Wing Configurations at Mach Numbers 8 and 10.5

Descriptive Note:

Final rept. Jun-Sep 1971

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Report Date:

1973-02-01

Pagination or Media Count:

44.0

Abstract:

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.

Subject Categories:

  • Aerodynamics
  • Unmanned Spacecraft
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE