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Computer Program for Estimating Stability Derivatives of Missile Configurations.
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL ALA AEROBALLISTICS DIRECTORATE
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This report describes a computer program for estimating the stability coefficients of typical missile configurations with wings or tail fins or both. The Mach range is from zero to approximately 4.5. The roll orientation is zero plus configuration. Wings and tails must be in-line. Control are included ogive cylinder or cone cylinder however, body alone tables can be input if desired. A conical boattail segment can be added. The program does not predict drag data. Static stability and damping derivatives at zero angle of attack are predicted by this program.
APPROVED FOR PUBLIC RELEASE