NASA and the U.S. aerospace industry are performing studies of supersonic aircraft concepts with low sonic boom pressure signatures. The computational analyses of modern aircraft designs have matured to the point where there is confidence in the prediction of the pressure signature from the front of the vehicle, but uncertainty remains in the aft signatures due to boundary layer and nozzle exhaust jet effects. Wind tunnel testing without inlet and nozzle exhaust jet effects at lower Reynolds numbers than in-flight make it difficult to accurately assess the computational solutions of flight vehicles. A wind tunnel test in the NASA Ames 9- by 7-Foot Supersonic Wind Tunnel is planned for February 2016 to address the nozzle jet effects on sonic boom. The experiment will provide pressure signatures of test articles that replicate waveforms from aircraft wings, tails, and aft fuselage (deck) components after passing through cold nozzle jet plumes. The data will provide a variety of nozzle plume and shock interactions for comparison with computational results. A large number of high-fidelity numerical simulations of a variety of shock generators were evaluated to define a reduced collection of suitable test models. The computational results of the candidate wind tunnel test models as they evolved are summarized, and pre-test computations of the final designs are provided.
Wind Tunnel Model Design for Sonic Boom Studies of Nozzle Jet Flows with Shock Interactions
2016
31 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fluid Mechanics , Supersonic wind tunnels , Wind tunnel models , Computational fluid dynamics , Wind tunnel tests , Boundary layers , Jet exhaust , Jet flow , Nozzle flow , Pressure ratio , Sonic booms , Shock wave interaction , Signature analysis , Direct numerical simulation , Grid generation (mathematics)
British Library Conference Proceedings | 2016
|Wind-Tunnel Sonic-Boom Testing Techniques
NTRS | 1966
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