Accession Number : AD0457591


Title :   EXPERIMENTAL INVESTIGATION OF THE IMPACT PROBE METHOD FOR DETERMINING LOCAL SKIN FRICTION IN THE PRESENCE OF AN ADVERSE PRESSURE GRADIENT FOR A RANGE OF MACH NUMBERS FROM 1.70 TO 2.75.


Descriptive Note : Technical rept.,


Corporate Author : TEXAS UNIV AT AUSTIN DEFENSE RESEARCH LAB


Personal Author(s) : Hill, Oliver


Report Date : Jan 1963


Pagination or Media Count : 1


Abstract : This thesis presents the results of an experimental program to determine the feasibility of using a surface impact probe to measure values of local skin friction in a turbulent boundary layer over a range of Mach Numbers and pressure gradients. This work is an extension of previous work on adverse pressure gradients which was done at a nominal Mach Number of 2.0. The present investigation was conducted on an adiabatic flat surface which formed the test-section floor of a variable Mach Number supersonic wind tunnel. The Mach Numbers ranged from 1.70 to 2.75 with adverse pressure gradients of zero to 1.57 psi/in. (Author)


Descriptors :   *PITOT TUBES , *SKIN(ANATOMY) , FRICTION , FRICTION , SHEAR STRESSES , PRESSURE , SUPERSONIC FLOW , TURBULENT BOUNDARY LAYER , FLAT PLATE MODELS , WIND TUNNEL MODELS , MODEL TESTS , DRAG , ADIABATIC GAS FLOW , COMPRESSIBLE FLOW , MATHEMATICAL ANALYSIS , EQUATIONS , MEASUREMENT , ERRORS , EXPERIMENTAL DATA , TABLES(DATA) , GRAPHICS , FEASIBILITY STUDIES , SURFACE PROPERTIES


Distribution Statement : APPROVED FOR PUBLIC RELEASE