CFD Prediction of Magnus Effect in Subsonic to Supersonic Flight
Final rept. Sep 2006-Dec 2007
ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
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The aerodynamic coefficients of the 7-cal. U.S. Army-Navy Spinner Rocket were characterized using computational fluid dynamic CFD calculations and validated using archival experimental data. The static aerodynamic coefficients, roll-damping, and pitch-damping moments were accurately predicted by steady-state Reynolds-averaged Navier-Stokes RANS as well as unsteady hybrid RANSlarge-eddy simulation LES CFD. The Magnus moment was overpredicted in the subsonic and transonic regime. Unsteady RANSLES computations did not improve the prediction of Magnus moment at the lower Mach numbers. Both steady-state RANS and unsteady RANSLES simulations resulted in similar predictions of all aerodynamic coefficients. Distributions of Magnus moment along the projectile body showed that the largest difference in Magnus moment between configurations and Mach numbers was in the last caliber of the projectile body.
- Military Aircraft Operations
- Fluid Mechanics