U= freestream velocity x= axial coordinate for 2-D nozzles, usually from the nozzle throat y=
vertical coordinate, in the curvature plane for 2-D nozzles z= for 2-D nozzles, a horizontal …

Hypersonic reentry vehicles are subjected to high levels of fluctuating pressures. These
intense fluctuations can cause vibration of internal components and can lead to structural …

A 20%-scale X-51A forebody model was tested in the Boeing and US Air Force Office of
Scientific Research Mach-6 Quiet Tunnel. The effect of a smooth blank and two different trip …

Accurate prediction of boundary-layer transition is desired to predict heating and skin friction
on a hypersonic flight vehicle. Boundary-layer transition is caused by the growth of …

A 2: 1 aspect-ratio elliptic cone was tested in the Boeing/AFOSR Mach-6 Quiet Tunnel to
investigate the effects of freestream noise level, surface roughness, angle of attack, and …

The research program of the aerodynamics, aerothermodynamics and plasmadynamics
discipline of NASA's Hypersonic Project is reviewed. Details are provided for each of its …

The quiet-flow capabilities of the Boeing/AFOSR Mach-6 Quiet Tunnel have been well
established in the last decade, but a full characterization of the nozzle flow is an ongoing …

To investigate the effect of roughness on the stationary crossflow vortices, roughness
elements 2 inches from the nosetip were created in a Torlon insert section of a 7-deg half …

Laminar-turbulent transition is critical for vehicles which fly at hypersonic speeds for
extended periods, yet conventional wind tunnels suffer from turbulent nozzle-wall boundary …

The BoeingAFOSR Mach-6 Quiet Tunnel continues to be developed to simulate the low
noise of the free-flight environment. An investigation of the flow entering the contraction of …