Effects of angle of attack and bluntness on the shock-layer properties of a 15 deg cone at a Mach number of 10.6
Effects of angle of attack and bluntness on shock layer properties of cones at supersonic speeds
Cleary, J. W.↗
Engineering topics
Cleary, J. W.
Publications and source records attributed to Cleary, J. W..
A study of numerical methods for predicting flow about bodies at angle of attack
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Gallo, W. F.↗
Effects of angle of attack and nose bluntness on the hypersonic flow over cones.
Nose bluntness and angle of attack effects on hypersonic flow, noting shock wave deflection decrease of minimum possible shock angle, varying specific heat ratio, convective heating, boundary layer transition, etc
SPECIFIC HEAT↗
Wedge and cone theory for m infinity equals infinity.
Tabulated values of ratio of cone surface pressure-pressure at shock
CONE↗
An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic mach numbers
Pressure distribution and flow fields of blunted cones at hypersonic Mach numbers
MACH NUMBER↗
Transonic wind tunnel tests of the launch, jettison, and longitudinal characteristics of an airplane and missile model combination
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Cleary, J. W.↗