Accession Number : AD0668103

Title :   SUPERSONIC FLOW PAST BODIES OF ROTATION WITH ANNULAR GAP,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Morozov,M. G. ; Baryshev,Yu. V.

Report Date : 17 AUG 1967

Pagination or Media Count : 11

Abstract : The results of an experimental investigation of supersonic flows past bodies of revolution with annular recesses of various lengths by means of a wind tunnel in the Mach ranges M = 1.79 to 3.69 and Re = 290,000 to 1,050,000 for 1 cm are presented. Various cylindrical models 6 to 60 mm in diameter with conical forward sections and with annular recesses of different lengths and depths were considered. The length of the recess 1 sub cr called critical for which the flows changed from flows with one to flows with two stagnation regions and also its ratio to its depth were determined experimentally from schlieren photographs. An attempt was made to establish the relationship between 1 sub cr/h and M and Re. The results of measurements on aerodynamic drag confirmed the conclusions from an analysis of the available data stating that the transition from the first to the second type of flow is accompanied by a jump-type increase in drag, thus an increase in the diameter of the rear cylinder in the region 1 sub cr may lead to a decrease in drag, and vice versa. The transition from the first type of flow to the second occurs in a quite narrow range of the value K1 sub cr/L = 12 to 22, where k is the coefficient accounting for the curvature of the model. (Author)

Descriptors :   (*LAMINAR FLOW, SUPERSONIC CHARACTERISTICS), STAGNATION POINT, BODIES OF REVOLUTION, WIND TUNNEL MODELS, MODEL TESTS, DRAG, CYLINDRICAL BODIES, CONICAL BODIES, USSR

Subject Categories : Aerodynamics
      Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE