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Title: Numerical analysis of supersonic base flow in the presence of thermal action on the wake

Journal Article · · Combust., Explos. Shock Waves (Engl. Transl.); (United States)
DOI:https://doi.org/10.1007/BF00750351· OSTI ID:6203025

There exist several types of aircraft for which the base drag at supersonic speed is a significant fraction of the total aerodynamic drag. The base drag is determined by the low pressure in the region of the near wake formed behind the body with a blunt tail cutoff. One way to raise the pressure on the tail is to deliver heat from the combustion of fuel injected into the base region or the external inviscid flow from the surface of the body. The effectiveness of this method has already been proven experimentally; the authors of this paper seek to carry out a detailed theoretical analysis of the complex base flow when this process of drag reduction is employed.

OSTI ID:
6203025
Journal Information:
Combust., Explos. Shock Waves (Engl. Transl.); (United States), Vol. 22:3; Other Information: Translated from Fiz. Goreniya Vzryva; 22: No.3, 78-84(May-Jun 1986)
Country of Publication:
United States
Language:
English

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