Novel Calibration Approach for Prediction of Aerodynamic Coefficients over Large-size Aerodynamic Configurations in High-speed Flow

In proper design era of any hypersonic spacecraft, such as space shuttles or missiles, has a serious problem with aerodynamic heating and drag force. Having an approximation of this drag force is desirable. For these calculations, any appropriate force balance is used in conjunction with ground-based test facilities. To anticipate the force inversely from recorded responses, these force balances must be calibrated. There are many calibration techniques reported in the literature. Multi point calibration is found to be convenient and effective technique. However, conventionally a multi-point calibration has been carried out over a test model. But there is no any evidence in literature that effect of number of points changes during calibration on a recovered forces. Hence experimental studies focus on different set of loading points over a test model for calibration. Therefore, a blunt bicone model has been fabricated in-house for present studies. The associated three component accelerometer balance has also been made with the concern of achieving free flying condition.