Accession Number:

AD0431533

Title:

THE INFLUENCE OF SLIGHT LEADING-EDGE BLUNTNESS ON BOUNDARY-LAYER TRANSITION AT A MACH NUMBER OF EIGHT

Descriptive Note:

Technical documentary rept.

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1964-03-01

Pagination or Media Count:

29.0

Abstract:

The influence of leading-edge geometry on boundary-layer transition on a hollow cylinder aligned with the flow was studied under hypersonic conditions with near adiabatic wall temperature. Effects on the Reynolds number of boundary-layer transition produced by varying free-stream unit Reynolds number and small degrees of leading-edge bluntness are shown to be qualitatively similar to results previously reported by the authors for Mach numbers of 3 to 5. There was a pronounced favorable effect associated with increases in both factors. Comparisons are made with the theoretical estimates of the influence of bluntness given by Moeckel. Although qualitative agreement with Moeckels theory is noted, quantitative agreement is not shown and some doubt concerning the theory is expressed.

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE