Accession Number : AD0425468


Title :   METHOD OF DETERMINING EFFECTS OF HEAT CONDUCTION IN LEADING EDGE OF WIND TUNNEL MODELS.


Descriptive Note : Rept. for Aug 62-Apr 63,


Corporate Author : RESEARCH AND TECHNOLOGY DIV BOLLING AFB D C


Personal Author(s) : Miller,Linn E ; Hankey,Wilbur L ,Jr


Report Date : Oct 1963


Pagination or Media Count : 49


Abstract : A technique is developed for correcting heat transfer data for conduction effects in the vicinity of the leading edges of wind tunnel models. A solution is obtained by solving the general heat equation as applied to a cylindrical leading edge under a step heat impulse by means of Fourier and Laplace transforms. The local temperature is found to be a power series in time for thin skin models. By comparison of wind tunnel data with the theory developed it was ascertained that only three terms in the series (second degree curve in time) adequately represented the data. The coefficient of the linear time term is shown to be directly proportional to the applied heating rate. This theory is applied to several hypersonic wind tunnel tests and results in the elimination of large conduction errors in the heat transfer coefficient data. (Author)


Descriptors :   *LEADING EDGE FLAPS , HEAT TRANSFER , MEASUREMENT , WIND TUNNEL MODELS , CYLINDRICAL BODIES , INTEGRAL TRANSFORMS , TAYLORS SERIES , HYPERSONIC FLOW , TEMPERATURE , THERMAL CONDUCTIVITY , FLAT PLATE MODELS , BOUNDARY LAYER , WINGS , TABLES(DATA) , TWO DIMENSIONAL FLOW


Distribution Statement : APPROVED FOR PUBLIC RELEASE