Hypersonic waveriders have the potential to significantly reduce travel times on long haul civilian transport routes. The design of hypersonic aircraft is heavily influenced by the aerodynamic efficiency at the cruise Mach number, resulting in less than ideal geometries for subsonic flight. Waverider aerodynamics and stability in the low speed regime is rarely investigated and not well understood, but is crucial for horizontal take-offs and landings. To date, low speed analyses of waverider shapes have been confined to static investigations, with limited work on longitudinal dynamics. No studies outlining the lateral-directional dynamic stability and aerodynamic derivatives has ever been published. This paper presents results for the low speed propelled variant of the Mach 8 HEXAFLY-INT waverider, which was subjected to forced oscillations in roll, yaw and side-to-side translations. This was achieved using unsteady Reynolds Averaged Navier Stokes simulations. Tests were conducted at a speed of 20 m/s, which correlates to a Reynolds number of approximately $1.5\times {10}^6$. The dynamic motion was at forced frequency of 1 Hz with angle amplitudes of 1 degree. The vehicle was analysed through an angle of attack range from -5 to 15 degrees in 5 degree increments. Results for the nominal centre of gravity location at 44.4% of the vehicle length show values for the dynamic derivatives within expected ranges, apart from the rolling moment due to yaw rate below approximately 2 degrees angle of attack. A similar finding for the dihedral derivative in static tests concluded that the low mounted wing with anhedral results in instabilities at low angles of attack. Investigations conducted at a centre of gravity location of 53.1% of the vehicle length, the aft static stability limit, also showed data within normal ranges. For these cases, the derivative magnitudes were lower, which indicates decreased damping compared to the nominal centre of gravity location. Some significant impact was seen on the roll damping derivative due to lowering the centre of gravity. This is from a combination of non-linear wing side force variance with angle of attack and the reduction of the moment arm, which resulted in less damping. The derivatives generally showed little sensitivity to changes in the oscillation frequency, with frequency rates ranging from 0.5 to 2 Hz tested. Overall, the results from this study highlighted the complex combinations of rate induced forces which contribute to the dynamic behaviour of the aircraft.

高超音速行波器有可能显着减少长途民用运输路线的旅行时间。高超音速飞机的设计在巡航马赫数时受到空气动力效率的严重影响，导致亚音速飞行的几何形状不理想。在低速状态下，乘浪茄飞机的空气动力学特性和稳定性很少得到研究，也未得到很好的理解，但对于水平起降至关重要。迄今为止，对波峰飞行器形状的低速分析仅限于静态研究，而对纵向动力学的研究却很少。迄今尚未发表概述横向动态稳定性和空气动力学派生性的研究。本文介绍了Mach 8 HEXAFLY-INT消波器的低速推进变体的结果，该变体在侧倾中受到强迫振荡，偏航和并行翻译。这是通过使用不稳定的雷诺平均Navier Stokes模拟来实现的。测试以20 m / s的速度进行，与雷诺数约$1.5\times {10}^6$。动态运动的强制频率为1 Hz，角度幅度为1度。通过-5度到15度的迎角范围（以5度增量）对车辆进行了分析。在车辆长度的44.4％处的标称重心位置的结果显示了在预期范围内的动态导数值，除了由于偏航角低于大约2度迎角而产生的侧倾力矩外。在静态测试中对二面体导数的类似发现得出结论，带有反面的低架机翼在低迎角下会导致不稳定。在车辆长度的53.1％（后部静态稳定性极限）的重心位置进行的研究也显示了正常范围内的数据。对于这些情况，导数幅度较低，与标称重心位置相比，这表明阻尼降低。由于降低了重心，因此对侧倾阻尼导数产生了一些重大影响。这是由于非线性机翼侧向力方差与迎角以及力矩臂的减小相结合所致，从而减少了阻尼。导数通常对振荡频率的变化几乎不敏感，测试的频率范围为0.5至2 Hz。总的来说，这项研究的结果强调了速率感应力的复杂组合，这些组合会导致飞机的动态行为。这是由于非线性机翼侧向力方差与迎角以及力矩臂的减小相结合所致，从而减少了阻尼。导数通常对振荡频率的变化几乎不敏感，测试的频率范围为0.5至2 Hz。总体而言，这项研究的结果突出了速率感应力的复杂组合，这些组合会导致飞机的动态行为。这是由于非线性机翼侧向力方差与迎角以及力矩臂的减小相结合所致，从而减少了阻尼。导数通常对振荡频率的变化几乎不敏感，测试的频率范围为0.5至2 Hz。总体而言，这项研究的结果突出了速率感应力的复杂组合，这些组合会导致飞机的动态行为。