Flow-turning Losses Associated with Zero-drag External-compression Supersonic Inlets
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Meyer, Rudolph C↗
Engineering topics
Meyer, Rudolph C
Publications and source records attributed to Meyer, Rudolph C.
Investigation of an asymmetric 'penshape' exit having circular projections and discharging into quiescent air
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Connors, James F↗
A variable-geometry annular cascade-type inlet at Mach numbers of 1.9 and 3.05
A variable-geometry annular cascade-type inlet is proposed and demonstrated. Such an inlet yielded total-pressure recoveries of 0.84 and 0.53 at Mach numbers of 1.9 and 3.05., respectively. Unity mass-flow ratios were obtained at each Mach number with only marginal subcritical stability ranges of mass-flow ratio (?0.03). Angles of attack up to 6 percent produced only moderate decreases in performance.
Connors, James F↗
Performance Characteristics of Axisymmetric Two-cone and Isentropic Nose Inlets at Mach Number 1.90
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Conners, James F↗
A Variable-geometry Axisymmetric Supersonic Inlet with Telescoping Centerbody
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Conners, James F↗