Accession Number : AD0610663

Title :   EXPERIMENTAL REYNOLDS ANALOGY FACTOR FOR A COMPRESSIBLE TURBULENT BOUNDARY LAYER WITH A PRESSURE GRADIENT.

Descriptive Note : Final rept.,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Pasiuk,Lionel ; Hastings,Samuel M. ; Chatham,Rodney

Report Date : 27 NOV 1964

Pagination or Media Count : 55

Abstract : An experimental study was made of the effect of a favorable pressure gradient on the Reynolds analogy factor, K = 2St/C sub f, for a natural two-dimensional supersonic turbulent boundary layer in air. Integrated values of the skin friction coefficient and Stanton number were determined from experimental data. The results show that Colburn's value of K = Pr to the - 2/3 power, which was found empirically from zero pressure gradient data, is satisfactory for relating skin friction and heat transfer for the magnitudes of pressure gradients investigated. (Author)

Descriptors :   (*TURBULENT BOUNDARY LAYER, HEAT TRANSFER), (*AERODYNAMIC HEATING, GUIDED MISSILES), (*HEAT TRANSFER, FRICTION), TWO DIMENSIONAL FLOW, SUPERSONIC FLOW, REYNOLDS NUMBER, PRESSURE, NOZZLES, TABLES(DATA), REENTRY VEHICLES

Distribution Statement : APPROVED FOR PUBLIC RELEASE