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오늘 본 자료
Numerical Investigation of a Ballistic Range Free Flight Model
I. Mahomed,H. Roohani,B. W. Skews,I. M. A. Gledhill,Y. Yamashita,H. Fujiwara,T. Suzuki,A. Iwakaka,A. Sasoh 한국항공우주학회 2021 International Journal of Aeronautical and Space Sc Vol.22 No.6
Ballistic range experiments were performed for a hemisphere-flare-cylinder model at supersonic Mach numbers in the transitional Reynolds number range at Nagoya University. The free-flight portion was modelled as axisymmetric in ANSYS Fluent® V.19.0. Projectile deceleration was included in the simulation as a function of the drag force over an approximate flight Mach number range 2.0–1.90. The projectile deceleration magnitude averaged approximately 700g and 1550g (g = 9.81 m s−2) for two experiment cases. The Reynolds number (Red) for each case based on the initial flight Mach number was Red = 90,000 and 177,000 respectively. The flow field, separation shock angle, averaged deceleration magnitude and averaged drag coefficient were compared between experiment and simulation. Agreement of these parameters was consistent for the Red = 177,000 case. This result contributed towards validation of the numerical acceleration technique. Differences for the Red = 90,000 case are explained with reference to experiment and simulation data.