Accession Number : ADA018680
Title : Prediction of Aerodynamics of Missiles at High Angles of Attack in Supersonic Flow.
Descriptive Note : Annual technical rept. 1 Oct 74-30 Sep 75,
Corporate Author : NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CALIF
Personal Author(s) : Dillenius,Marnix F. E. ; Nielsen,Jack N.
Report Date : OCT 1975
Pagination or Media Count : 203
Abstract : Improvements have been added to a computer program previously reported in NEAR Technical Report 74 for calculating the loadings on cruciform wing-body combinations at supersonic speeds and it has been extended to wing-body-tail combinations. An improvement in the accuracy of calculating the pressures acting on the combination enables good agreement between experimental and theoretical fin forces and moments up to 20 deg to angle of attack. An option has been added to the computer program to include the effect of nose vortices on the loading of the canard fins and body. In addition, the necessary distributions of leading-edge and side-edge suction forces have been calculated to set up the model of the separation vortices from the leading edges and side edges of the canard fins using the Polhamus vortex-lift analogy. For the case considered, compressibility was shown to have little effect on the trajectories of vortices from the canard fins to the empennage. In addition, the effect of the nose and canard vortices on the cruciform tail forces and moments have been determined. Thus, the capability for determining the characteristics of a complete missile has been developed. A listing of the computer program and a calculative example are included. Extensive comparisons between the prediction of the computer program and experiment are included with generally good agreement. (Author)
Descriptors : *Wing body configurations, Supersonic flow, Cruciform wings, Aerodynamic loading, Mathematical prediction, Computer programs, Angle of attack, Leading edges, Vortices, Guided missile trajectories, Canard configuration, Roll
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE