Wing-body Interference Lift For Supersonic Missiles With Elliptical Cross-section Fuselages


The effect of elliptical fuselage cross sections on wing lift is calculated for supersonic, delta-wing missiles at Mach 3 and 4. Aspect ratios of 2.4, 3.2, and 4.0 are considered. Wing lift in the presence of an elliptical fuselage is computed by solving the Euler equations using a finite-difference method, and it is presented in terms of the wing-body interference parameter KW(B) The fuselage cross sections are defined in terms of the ratio of their vertical-to-horizontal semiaxes B/R. KW(B) values are presented for B/R =0.33, 0.50, 0.75, 1.0, 1.5, 2.0, and 2.4 for planar and cruciform fin configurations. Numerical results at constant Mach number and fin size show that KW(B) decreases as B/R increases. For small fins, typical of missiles, wing lift is quite sensitive to fuselage shape; whereas for large wings, typical of airplanes, wing lift is not very sensitive to fuselage shape. As Mach number increases for a specific fin size, KW(B) increases slightly for B/R < 1 and decreases slightly for B/R > 1; however, for preliminary design purposes the change in KW(B) with Mach number is negligible. Evaluation of KW(B) is necessary for missile preliminary design component build-up methods. Simple equations are presented for KW(B) as a function of wing span to body radius ratio and B/R, which are suitable for preliminary design. KW(B) values from this research are the only ones available for elliptical cross section fuselages. © American Institute of Aeronautics and Astronautics, Inc., 1989, All rights reserved.


Mechanical and Aerospace Engineering

International Standard Serial Number (ISSN)


Document Type

Article - Journal

Document Version


File Type





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

Publication Date

01 Jan 1989