Wing Vertical Position Effects On Lift For Supersonic Delta Wing Missiles

Abstract

The effect of wing vertical position on lift is investigated for supersonic missiles with cylindrical bodies and delta wings. Wing locations above and below the body centerline are considered over a range of Mach number, angle of attack, and aspect ratio. A finite-difference Euler code, SWINT, is used to compute the wing lift. The lift forces are presented in terms of KW(B), which is a measure of wing-body interference due to body upwash. The SWINT KW(B) values for wings located on the missile centerline compare favorably with existing results from theoretical and experimental sources. SWINT results for wings located off the missile centerline indicate that wing lift decreases symmetrically as the wing is moved above or below the centerline. The results are valid for unrolled delta wing-body combinations at moderate-to-high supersonic Mach numbers and at low angles of attack. A simple model based on upwash theory is developed that agrees well with Kw(B) predicted by SWINT. Empirical formulas for calculating Kw(B) as a function of wing span and vertical position are presented for easy use in preliminary design. © American Institute of Aeronautics and Astronautics, Inc., 1989, All rights reserved.

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

© 2023 American Institute of Aeronautics and Astronautics, All rights reserved.

Publication Date

01 Jan 1989

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