Preliminary Design Aerodynamic Prediction Methodology for Missiles with Nose Bluntness.
Final rept. Apr 77-Jun 78,
SYSTEMS RESEARCH LABS INC DAYTON OH AEROSYSTEMS RESEARCH DIV
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A semi-empirical methodology is presented for predicting the axial and normal force coefficients and the center of pressure to include nose bluntness effects for missiles. This methodology includes the transonic and supersonic Mach number regime with angles of attack from 0 to 180 degrees. This methodology correlates well with wind tunnel test data. Author
- Guided Missile Dynamics, Configurations and Control Surfaces
- Guided Missiles