Aerodynamic force measurements over missile configurations in IISc shock tunnel at M∞ = 5.5

Dynamic calibration of force balances for impulse hypersonic facilities

“…Another possibility is to measure the acceleration of the model and use flexible supports for the model (e.g. Joshi and Reddy, 1986) or to let the model fly freely during the test (e.g. Naumann et al, 1993).…”

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

“…But the complete measurement system is cumbersome and moreover it is difficult to maintain the necessary level of accuracy during measurement. The other type of support system is by mounting the model with flexible rubber bushes [7,9] such that the rubber bushes have negligible effect during the free flight duration of $1 ms. However the analysis is limited to simple slender configurations such as cones and cylinders.…”

“…The experiments were carried out at CAL (Cornell Aeronautical Laboratory) reflected mode shock tunnel during a steady test time of 2-10 ms at various Mach numbers ranging from 5 to 14. In order to overcome the limitations associated with model size and calibration, an accelerometer-based force balance system has been developed by Joshi and Reddy [7] for shock tunnel applications where the test time is $1 ms. In these balance systems the model suspension system plays a very vital role in determining the free-floating behaviors of the model during short test times.…”

Fabrication and Installation of Moderate Size Shock Tube Facility – A Case Study

“…[10][11] Extending this facility to shock tunnels, researchers conducted force measurement successfully on a missile shaped configuration at supersonic and hypersonic Mach numbers. [12][13] The surface heating measurements on blunt bodies for variety of interdisciplinary space science applications have also been exhaustively carried out. [14][15][16] With the above viewpoint, the authors report about installation of a particular shock tube facility as one of the case study.…”