Computational study of the cavity flow over sharp nose cone in supersonic flow.

Pish, F.; Tran Dinh Manh; Gerdroodbary, M. Barzegar; Nguyen Dang Nam; Moradi, Rasoul; Babazadeh, Houman

Heat and drag reduction on the nose cone is a significant issue for increasing the speed of the supersonic vehicles. In this paper, computational fluid dynamic method is applied to investigate the thermal and drag coe±cient on the sharp nose cone with different cavity shapes. In order to simulate our model, the CFD method with SST turbulence model is applied to study the flow feature and temperature distribution in the vicinity of the nose body. The effect of depth and length of the cavity on the thermal characteristic of the nose cone is comprehensively investigated. In addition, the influence of the number of the cavity in the thermal performance of the main body is studied. According to our results, increasing the length of the cavity highly e±cient for the reduction of the drag at Mach = 3. As the Mach number is increased to 3, the number of the cavity becomes a significant role and it is observed that case 9 with four cavities is more e±cient. Obtained results also show that increasing the cavity depth declines the temperature on the main body. Our findings confirm that the main source of the expansion is the edge of the cavity.

SUPERSONIC flow; MACH number; NOSE; CONES; DRAG reduction; TEMPERATURE distribution

International Journal of Modern Physics C: Computational Physics & Physical Computation, 2020, Vol 31, Issue 6, p1

0129-1831

Academic Journal

10.1142/S0129183120500795