Accession Number : AD0709515

Title :   VERMINDERUNG DES WIDERSTANDS VON UEBERSCHALLFLUGKOERPERN DURCH HECKHEIZUNG (Reduction of Drag of a Supersonic Missile by Base Burning),

Corporate Author : DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V AACHEN (WEST GERMANY)

Personal Author(s) : Bartlmae,Fritz

Report Date : 10 JUL 1969

Pagination or Media Count : 9

Abstract : By means of continuous stable combustion of highly reactive fuels in the wake of a supersonic missile, the base drag can be reduced considerably and thrust can be achieved under certain conditions. The possibilities and limits of base burning are examined. It turns out that two entirely different flow patterns are obtained, depending on the magnitude of the base pressure. For a certain chemical reaction and a given flight Mach number, a maximum value for the thrust and the base drag reduction respectively exists resulting from the interaction between base pressure and body geometry. (Author)

Descriptors :   (*GUIDED MISSILES, DRAG), (*BASE FLOW, DRAG), BASE PRESSURE, COMBUSTION, WAKE, THRUST, REDUCTION, WEST GERMANY

Subject Categories : Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE