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) : Whitfield, Jack D ; Potter, J Leith


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/431533.pdf


Report Date : Mar 1964


Pagination or Media Count : 29


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 Moeckel's theory is noted, quantitative agreement is not shown and some doubt concerning the theory is expressed.


Descriptors :   *AERODYNAMIC CONTROL SURFACES , *BOUNDARY LAYER TRANSITION , LEADING EDGES , HYPERSONIC CHARACTERISTICS , REYNOLDS NUMBER , BLUNT BODIES , FINS , HYPERSONIC FLOW , MODEL TESTS , CYLINDRICAL BODIES , WINGS


Subject Categories : Aircraft
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE