Numerical Analysis for the Pressure Distribution along a Typical Fin-stabilized Missile

Document Type : Original Article

Authors

Aerospace Engineering Department, Military Technical College, Cairo, 11776, Egypt.

10.1088/1742-6596/2616/1//asat.2025.453552

Abstract

Realizing the aerodynamic forces exerted on the missile structure for fin-stabilized missiles requires a good estimation of the pressure distribution along the missile body. This distribution has a direct impact on its structure, stability, and controllability, providing an essential pressure estimation to missile design. This study is performed by applying numerical calculations on a fin-stabilized missile with a slenderness ratio of 16.2. A detailed 3D model of the missile and its computational domain is constructed. The numerical simulations are performed by using the commercial software ANSYS Fluent. The results are validated with experimental wind tunnel data. The study has deep insight into how the pressure distribution along the missile airframe behaves at 4° and 8° angles of attack for Mach numbers 2 and 3.55. Finally, the effects of altitude impact on the pressure are also discussed, providing useful information on how the missile performs under different flight conditions.
International Conference on Aerospace Sciences and Aviation Technology
Volume 21, Issue 21
21st International Conference on Aerospace Sciences & Aviation Technology, ASAT 21, 2025.
September 2025
Pages 1-9

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