J. W. Cleary

发表

Investigations to the space shuttle orbiter 2A configuration 0.015-scale model in the NASA Ames Research Center 3.5-foot hypersonic wind tunnel at Mach numbers 5, 7 and 10 (OA11B)

M. E. Nichols, M. D. Milam, J. A. Mellenthin, 1974 .

Results of tests of a 0.010- and 0.015-scale models of space shuttle orbiter configurations 3 and 3A in the Ames Research Center 3.5 foot hypersonic wind tunnel (OA23)

M. D. Milam, J. A. Mellenthin, J. W. Cleary, 1974 .

Static and dynamic aerodynamics of space shuttle vehicles

J. A. Axelson, V. L. Peterson, J. A. Mellenthin, 1971 .

A study of numerical methods for predicting flow about bodies at angle of attack

J. W. Cleary, W. F. Gallo, J. V. Rakich, 1967 .

Transonic wind-tunnel tests of the launch, jettison, and longitudinal characteristics of an airplane- and missile-model combination

J. W. Cleary, C. F. Dewey, J. L. Frank, 1957 .

Results of investigations on an 0.015-scale 140A/B configuration of the Rockwell International space shuttle orbiter (model 49-O) in the NASA/Ames Research Center 3.5-foot hypersonic wind tunnel (OA36)

M. D. Milam, R. L. Gillins, J. W. Cleary, 1974 .

Wind tunnel test of the 0.010-scale space shuttle integrated vehicle in the NASA-Ames 3.5 foot hypersonic wind tunnel (IA10)

J. A. Mellenthin, J. W. Cleary, M. T. Petrozzi, 1973 .

Effects of angle of attack and bluntness on laminar heating-rate distributions of a 15 deg cone at a Mach number of 10.6

J. W. Cleary, J. Cleary, 1969 .

Trailing-Edge Flows at High Reynolds Number

P. R. Viswanath, J. W. Cleary, H. L. Seegmiller, 1980 .

Effects of angle of attack and bluntness on the shock-layer properties of a 15 deg cone at a Mach number of 10.6

J. W. Cleary, 1968 .

Approximation for distribution of flow properties in the angle-of-attack plane of conical flows

J. W. Cleary, 1970 .

Asymmetric Trailing-Edge Flows at High Reynolds Number

P. R. Viswanath, J. W. Cleary, H. L. Seegmiller, 1980 .

An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic mach numbers

J. W. Cleary, J. Cleary, 1965 .

Effects of angle of attack and nose bluntness on the hypersonic flow over cones.

J. W. Cleary, J. Cleary, 1966 .