Experimental and analytical comparison of aerodynamic characteristics of a forward-control missileComparisons of analytical and experimental aerodynamic data for canard controlled missile configurations are presented. Recently, techniques to estimate the longitudinal, directional and lateral aerodynamic characteristics for cruciform missiles have been developed. Nielsen Engineering and Research, Inc. (NEAR, Inc.), supported by various governmental agencies, has been the originator of many of these new computational techniques. Two of these are major computer programs currently being implemented by several research organizations. Predicted data from these two programs are compared with experimental data recently obtained at the NASA Langley Research Center Unitary Plan wind tunnel facility. Comparisons cover the supersonic Mach number regime of 1.60 to 3.50, angles-of-attack from 0 to 20 degrees and roll angles of 0, 26.57 and 45 degrees. Major emphasis is on the roll characteristics due to aileron with limited longitudinal and directional characteristics addressed.
Document ID
19800038834
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Blair, A. B. (NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)
Rapp, G. H. (Motorola, Inc. Government Electronics Div., Scottsdale, Ariz., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-0374
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Pasadena, CA
Start Date: January 14, 1980
End Date: January 16, 1980
Sponsors: American Institute of Aeronautics and Astronautics