Evaluation of transonic and supersonic wind-tunnel background noise and effects of surface pressure fluctuation measurements

Experiments are performed to study the interaction of an impinging shock wave and an expansion fan in a Mach 1.280 flow. The expansion fan neutralizes the pressure rise induced by the impinging shock wave. The mean surface static pressure shows a linear combination of the effect of both perturbations. Surface pressure fluctuations, which are associated with the characteristics of the perturbed boundary layer, indicate a transitional behavior. This is related to a nonlinear phenomenon arising the simultaneous action of the impinging shock wave and the expansion fan. The level of downstream pressure fluctuation depends on the overall inviscid interaction strength.

show abstract

Pressure fluctuations underlying attached and separated supersonic turbulent boundary layers and shock waves

Coe

Chyu

Dods

1973

Aeroacoustics Conference

View full text Add to dashboard Cite

Evaluation of transonic and supersonic wind-tunnel background noise and effects of surface pressure fluctuation measurements

Cited by 5 publications

References 0 publications

Unsteadiness of the shock wave structure in attached and separated compression ramp flows

Unsteadiness of the shock wave structure in attached and separated compression ramp flows

Investigation on Turbulent Expansion-Corner Flow With Shock Impingement

Pressure fluctuations underlying attached and separated supersonic turbulent boundary layers and shock waves

Contact Info

Product

Resources

About