An innovative pressure rail concept for wind tunnel sonic boom testing of modern aircraft configurations with very low overpressures was designed with an adjoint-based solution-adapted Cartesian grid method. The computational method requires accurate free-air calculations of a test article as well as solutions modeling the influence of rail and tunnel walls. Specialized grids for accurate Euler and Navier-Stokes sonic boom computations were used on several test articles including complete aircraft models with flow-through nacelles. The computed pressure signatures are compared with recent results from the NASA 9- x 7-foot Supersonic Wind Tunnel using the advanced rail design.
Design of Rail Instrumentation for Wind Tunnel Sonic Boom Measurements and Computational-Experimental Comparisons
International Conference on Computational Fluid Dynamics (ICCFD7) ; 2012 ; Big Island, HI, United States
2012-07-09
Conference paper
No indication
English
Wind-tunnel sonic-boom testing techniques
AIAA | 1966
|Wind-tunnel sonic-boom testing techniques.
AIAA | 1967
|