Accelerometer force balance (AFB), in conjunction with various force prediction methodologies, has been used in hypersonic flow regime. Present studies focus on its ability to capture small and large alterations in the force and moment coefficients. For this objective, shock tunnel experiments are conducted on a bi-conic model without and with hemispherical or sharp aerospike. A three component AFB is equipped to measure acceleration responses during the experiments. Adaptive Neuro Fuzzy Inference System (ANFIS) is employed herein for the force recovery. Aerodynamic coefficients obtained from ANFIS are noticed to have encouraging match with the AFB theory. It has been shown here that, AFB and recently developed ANFIS based force recovery methodology can precisely predict as small as 6.3% and as large as 38% change in the force along with its temporal variation. Hence, this study strengthens the use of a soft computing technique like ANFIS for predicting steady state and temporal variations of aerodynamic coefficients during shock tunnel testing of hypersonic configurations.

加速度计力平衡 (AFB) 与各种力预测方法相结合，已被用于高超声速流动状态。目前的研究集中在它捕捉力和力矩系数的大小变化的能力上。为了这个目的，冲击隧道实验是在双圆锥模型上进行的，没有和有半球形或锋利的气刺。配备三组件 AFB 以测量实验过程中的加速度响应。本文采用自适应神经模糊推理系统（ANFIS）进行力恢复。注意到从 ANFIS 获得的空气动力系数与 AFB 理论有令人鼓舞的匹配。这里已经表明，AFB 和最近开发的基于 ANFIS 的力恢复方法可以精确预测小至 6。力的 3% 和大至 38% 的变化及其时间变化。因此，本研究加强了使用 ANFIS 等软计算技术来预测高超音速配置冲击隧道测试期间空气动力学系数的稳态和时间变化。