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Aerodynamic Prediction for Supersonic Canard-Tail MissilesLRCDM2 computer program developed to calculate pressure distribution at points on surfaces of complete supersonic missile. Missile comprises up to two finned sections attached to axisymmetric body of circular cross section. Includes effects of vortex shedding due to forebody and forward fins, providing more accurate rolling moments. LRCDM2 written in FORTRAN IV.
Document ID
19860000529
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Dillenius, M. F. (Nielsen Engineering and Research, Inc.)
Date Acquired
August 12, 2013
Publication Date
November 1, 1986
Publication Information
Publication: NASA Tech Briefs
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LAR-13527
ISSN: 0145-319X
Report Number: LAR-13527
Accession Number
86B10529
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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