Computational Parametric Study of the Aerodynamics of Spinning Slender Bodies at Supersonic Speeds

Sturek, Walter B.; Mylin, Donald C; Bush, Clarence C.

doi:10.2514/3.51030

Cited by 2 publications

(1 citation statement)

References 6 publications

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“…The concept of circulation, prevalent in the circular cylinder analysis, has been mentioned in a few analytical approaches. 13,14 At higher angles of attack, the projectile closely resembles a cylinder set in the crossflow and the flowfield over it is found to be analogous to that of the circular cylinder. [15][16][17] The various existing theories that attempt to predict the Magnus effects are rather limited for practical applications.…”

Section: Introductionmentioning

confidence: 92%

Effects of spin rate on the surface pressure distribution of a rotating model

Askary

Soltani

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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A new experimental technique has been developed to measure the pressure distribution over the surface of a rotating model in a wind tunnel for various spin rates, free-stream Mach numbers, and angles of attack. In this method, all of the measuring instruments are placed inside the rotating model which eliminated previous operational limitations and technical problems associated with attempts to measure the Magnus effect. The validity and reliability of the measured data was verified by comparing the integrated surface pressure values and aerodynamic forces, with those directly measured from an internal strain gauge balance. From the acquired surface pressure data distribution of both local and total Magnus force on the model as well as the interpretation of the boundary layer and flow separation effects on the rotating model could be determined. The Magnus force distribution shows that the local Magnus force increases along the length of the model and the maximum local Magnus force occurs at the end of the projectile. The acquired experimental data were further compared with the numerical simulations and satisfactory results were achieved. This new experimental technique can be easily applied to a variety of model configurations testing at different Mach numbers, spin rates, angles of attack, etc.

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