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the practical calculation of the aerodynamic characteristics of slender finned vehiclesThe basic objective of this thesis is to provide a practical method of computing the aerodynamic characteristics of slender finned vehicles such as sounding rockets, high speed bombs, and guided missiles. The aerodynamic characteristics considered are the normal force coefficient derivative, c(sub N(sub alpha)); center of pressure, bar-X; roll forcing moment coefficient derivative, c(sub l(sub delta)); roll damping moment coefficient derivative, c(sub l(sub p)); pitch damping moment coefficient derivative, c(sub mq); and the drag coefficient, c (sub D). Equations are determined for both subsonic and supersonic flow. No attempts is made to analyze the transonic region. The general configuration to which the relations are applicable is a slender axisymmetric body having three or four fins.
Document ID
20010047838
Document Type
Thesis/Dissertation
Authors
Barrowman, James S.
(Catholic Univ. of America Washington, DC United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 1967
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:209983
NASA/TM-2001-209983
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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