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 (Re\(_\mathrm{d}\)) for each case based on the initial flight Mach number was Re\(_\mathrm{d}\) = 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 Re\(_\mathrm{d}\) = 177,000 case. This result contributed towards validation of the numerical acceleration technique. Differences for the Re\(_\mathrm{d}\) = 90,000 case are explained with reference to experiment and simulation data.

在名古屋大学以过渡雷诺数范围内的超音速马赫数对半球-耀斑-圆柱模型进行了弹道范围实验。自由飞行部分在 ANSYS Fluent ^® V.19.0 中建模为轴对称。弹丸减速度作为阻力的函数包含在模拟中，飞行马赫数近似范围为 2.0-1.90。对于两个实验案例，弹丸减速幅度平均约为 700 g和 1550 g（g = 9.81 ms \(^{-2}\)）。基于初始飞行马赫数的每种情况的雷诺数 (Re \(_\mathrm{d}\) ) 是 Re \(_\mathrm{d}\)= 90,000 和 177,000 分别。比较了实验与模拟的流场、分离激波角、平均减速度幅度和平均阻力系数。这些参数的一致性对于 Re \(_\mathrm{d}\) = 177,000 情况是一致的。这一结果有助于验证数值加速技术。参考实验和模拟数据解释了 Re \(_\mathrm{d}\) = 90,000 情况的差异。