Abstract

The Zonal Euler Solver code (ZEUS) is used to predict hypersonic missile flow fields 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 and a cylindrical fuselage with a 1-degree flair angle. Both 'x' and '+' fin configurations are considered. Results are given for 20 and 30 deg semi vertex angles as a function of fur span 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 KB(w) for the missile with ' x ' fins is slightly larger than it is for '+' fins at Mach 8 and 10. At Mach 4 and 6 it is independent of fin configuration. KB(w) is greater for 'x ' fins than it is for '+' fins and it increases as semi vertex angle decreases from 30 to 20 deg. KB(w) generally decreases as both Mach number and fin span increase. Equations and tables are presented for the carryover factors. © 2000 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Department(s)

Mechanical and Aerospace Engineering

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Full Access

Document Type

Article - Conference proceedings

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text

Language(s)

English

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© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.

Publication Date

01 Jan 2000

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