Accession Number:

ADA073664

Title:

Preliminary Design Aerodynamic Prediction Methodology for Missiles with Nose Bluntness.

Descriptive Note:

Final rept. Apr 77-Jun 78,

Corporate Author:

SYSTEMS RESEARCH LABS INC DAYTON OH AEROSYSTEMS RESEARCH DIV

Report Date:

1978-09-01

Pagination or Media Count:

199.0

Abstract:

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

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE