Numerical simulation of roll induced moment of cruciform tactical missiles

This paper presents a numerical evaluation of the induced roll moment of cr uciform missiles by a turbulent Navier-Stokes solver. The numerical results have been computed with a high resolution implicit upwind scheme. Comparis ons with experiments performed at ONERA show a good agreement as well as a decisive improvement over numerical simulations based on Euler equations. R esults are presented for subsonic and supersonic onflow conditions and two different configurations: fuselage-fins and fuselage-wing-fins. Comparative detailed analysis results in the origin of the rolling moment as well as t he contributions of the different lifting surfaces. (C) 2001 Editions scien tifiques et medicales Elsevier SAS.