A method is developed to obtain quick engineering estimates for the normal load on slender airbreathing shapes. Estimates of the normal load can be obtained using a Trefftz plane analysis. This computation, although two-dimensional and subsonic, agrees fairly well with experimental data (from NASA and AGARD) for three-dimensional slender bodies in supersonic flows. The computational technique is simple and extremely fast.

Surya C. Rajan

Sundarm Moses Santhakumar

Aspect ratio

Computational methods

Data reduction

Density (specific gravity)

Loads (forces)

Perturbation techniques

Free-stream

Mach number

PERTURBATION POTENTIAL

surface area

Aerodynamics

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IIT Madras

Engineering Estimates of Normal Loads on Slender Airbreathing Bodies

Journal of Spacecraft and Rockets

The momentum theorem is used to obtain the expression for the leading-edge suction force as it brings out some subtle features that are not seen when the conservation of energy is applied. The circulation distribution is elliptical and does not depend on the shape of the leading edge. The results are obtained from the theory of low aspect ratio wings by treating the crossflow past a triangular wing to be approximately two dimensional, giving the leading term in an asymptotic expansion for small aspect ratio wings.

Journal of Aircraft

Exact leading-term solution for low aspect ratio wings

Low-Speed Aerodynamics

Engineering estimates of normal loads on slender airbreathing bodies

Journal	Data powered by TypesetJournal of Spacecraft and Rockets
Publisher	Data powered by TypesetAmerican Institute of Aeronautics and Astronautics Inc.
ISSN	00224650
Impact Factor	1.868
Open Access	No
Citation Style	unsrt
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