Roll Effects on Carryover for Hypersonic Delta Fin Missiles
Abstract
An Euler code is used to predict hypersonic missile flowfields and to determine the carryover factors for the effect of the body on wing lift KW(B) and for the effect of the wing on body lift KB(W). Results are presented for Mach 4, 6, 8, and 10 at an angle of attack of 2 deg. The missile has a conical nose, a cylindrical fuselage with a 1-deg flare angle, and delta fins. Both x and + fin configurations are considered. Results are given for 20- and 30-deg semivertex angles as a function of finspan to body radius (at fin leading edge), S/RLE. The wing-body carryover for x fins is smaller for the top set of fins than it is for the bottom set of fins. The value of KW(B) for the missile with x fins is slightly larger than it is for + fins at Mach 8 and 10. At Mach 4 and 6, KW(B) is independent of fin configuration. KB(W) is larger for x fins than it is for + fins, and it increases as semivertex angle decreases from 30 to 20 deg. KB(W) generally decreases as both Mach number and finspan increase. Equations and tables are presented for the carryover factors.
Recommended Citation
H. F. Nelson, "Roll Effects on Carryover for Hypersonic Delta Fin Missiles," Journal of Spacecraft and Rockets, vol. 38, no. 1, pp. 21 - 27, American Institute of Aeronautics and Astronautics, Jan 2001.
The definitive version is available at https://doi.org/10.2514/2.3667
Department(s)
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
0022-4650
Document Type
Article - Journal
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 2001
