I. E. Beckwith

发表

Injection, distribution, and evaporation of liquids in the flow fields of hypersonic vehicles

I. E. Beckwith, 1964 .

Design requirements for the NASA Langley supersonic low-disturbance wind tunnel

I. E. Beckwith, F. J. Chen, T. R. Creel, 1986 .

Design and operational features of low-disturbance wind tunnels at NASA Langley for Mach numbers from 3.5 to 18

I. E. Beckwith, Fang-Jenq Chen, S. P. Wilkinson, 1990 .

Design and preliminary test results at Mach 5 of an axisymmetric slotted sound shield. [for supersonic wind tunnels (noise reduction in wind tunnel nozzles)

I. E. Beckwith, P. C. Stainback, W. D. Harvey, 1975 .

Supersonic and hypersonic quiet tunnel technology at NASA Langley

I. E. Beckwith, Fang-Jenq Chen, S. P. Wilkinson, 1992 .

A survey of NASA Langley studies on high-speed transition and the quiet tunnel

I. E. Beckwith, M. H. Bertram, 1972 .

Fluid mechanics aspects of the Gemini reentry communications experiment

I. E. Beckwith, D. M. Bushnell, J. K. Huffman, 1965 .

Sound and fluctuating disturbance measurements in the settling chamber and test section of a small, Mach 5 wind tunnel

I. E. Beckwith, P. C. Stainback, J. B. Anders, 1975 .

Comments on settling chamber design for quiet, blowdown wind tunnels

I. E. Beckwith, 1981 .

Instabilities and transition in the wall boundary layers of low-disturbance supersonic nozzles

I. E. Beckwith, M. R. Malik, M. Malik, 1985 .

Free stream noise and transition measurements in a Mach 3.5 pilot quiet tunnel

I. E. Beckwith, T. R. Creel, J. Kendall, 1983 .

Fluctuating disturbances in a Mach 5 wind tunnel

I. E. Beckwith, J. B. Anders, P. C. Stainback, 1977 .

Transition Research in the Mach 3.5 Low-Disturbance Wind Tunnel and Comparisons of Data with Theory

I. E. Beckwith, M. R. Malik, Chen, 1989 .

Development of a High Reynolds Number Quiet Tunnel for Transition Research

I. E. Beckwith, 1974 .

Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise

I. E. Beckwith, T. R. Creel, I. Beckwith, 1984 .

Nozzle optimization study for quiet supersonic wind tunnels

I. E. Beckwith, M. R. Malik, Fang-Jenq Chen, 1984 .

Transition on swept leading edges at Mach 3.5

I. E. Beckwith, T. R. Creel, F. J. Chen, 1987 .

A new technique for reducing test section noise in supersonic wind tunnels

I. E. Beckwith, J. B. Anders, P. C. Stainback, 1978 .

Transition Research in Low-Disturbance High-Speed Wind Tunnels

I. E. Beckwith, M. R. Malik, M. Malik, 1990 .

Calculation by a finite difference method of supersonic turbulent boundary layers with tangential slot injection

I. E. Beckwith, D. M. Bushnell, D. Bushnell, 1971 .

Progress in the development of a Mach 5 quiet tunnel

I. E. Beckwith, W. D. Harvey, A. J. Srokowski, 1977 .

Mean flow and noise measurements in a Mach 3.5 pilot quiet tunnel

I. E. Beckwith, W. O. Moore, 1982 .

Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel

I. E. Beckwith, T. R. Creel, F. J. Chen, 1985 .

Comparison of boundary-layer transition on a cone and flat plate at Mach 3.5

I. E. Beckwith, M. R. Malik, F.-J. Chen, 1988 .

Control of supersonic wind-tunnel noise by laminarization of nozzle-wall boundary layer

I. E. Beckwith, W. D. Harvey, J. E. Harris, 1973 .

Effects of streamwise variations in noise levels and spectra on supersonic boundary-layer transition

I. E. Beckwith, T. R. Creel, F. J. Chen, 1984 .

Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel

I. E. Beckwith, T. R. Creel, F. J. Chen, 1983 .

Wind tunnel noise reduction at Mach 5 with a rod-wall sound shield

I. E. Beckwith, T. R. Creel, 1983 .

Effects of nozzle design parameters on the extent of quiet test flow at Mach 3.5

I. E. Beckwith, D. M. Bushnell, M. R. Malik, 1985 .

Noise reduction in a Mach 5 wind tunnel with a rectangular rod-wall sound shield

I. E. Beckwith, J. W. Keyes, T. R. Creel, 1980 .

Boundary-layer transition on a cone and flat plate at Mach 3.5

I. E. Beckwith, M. R. Malik, Fang-Jeng Chen, 1989 .

Gortler vortices and transition in wall boundary layers of two Mach 5 nozzles

I. E. Beckwith, Ivan E. Beckwith, Barbara B. Holley, 1981 .

Development of a high Reynolds number quiet tunnel for transition research

I. E. Beckwith, Ivan E. Beckwith, 1974 .

The compressible turbulent boundary layer on a blunt swept slab with and without leading- edge blowing

I. E. Beckwith, D. Bushnell, J. Hunt, 1971 .

Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers

I. E. Beckwith, Ivan E. Beckwith, James J. Gallagher, 1961 .

Fluctuating properties of turbulent boundary layers for Mach numbers up to 9

I. E. Beckwith, W. D. Harvey, D. Bushnell, 1969 .

Calculation of nonequilibrium hypersonic turbulent boundary layers and comparisons with experimental data

I. E. Beckwith, D. Bushnell, I. Beckwith, 1969 .

Recent advances in research on compressible turbulent boundary layers

I. E. Beckwith, 1970 .

Goertler instability and hypersonic quiet nozzle design

I. E. Beckwith, Ivan E. Beckwith, Fang-Jenq Chen, 1991 .

Compressible laminar boundary layer over a yawed infinite cylinder with heat transfer and arbitrary Prandtl number

I. E. Beckwith, Ivan E. Beckwith, Eli Reshotko, 1957 .

Aerothermodynamics and Transition in High-Speed Wind Tunnels at NASA Langley

I. E. Beckwith, I. Beckwith, C. G. Miller, 1990 .

A new technique for reducing test section noise in supersonic wind tunnels

I. E. Beckwith, J. Anders, P. Stainback, 1978 .

Design and fabrication requirements for low-noise supersonic/hypersonic wind tunnels

I. E. Beckwith, Ivan E. Beckwith, Mujeeb R. Malik, 1988 .

Comment on "Spherically-Symmetric Supersonic Source Flow: A New Use for the Prandtl-Meyer Function"

I. E. Beckwith, 1974 .

Comments on Crocco's Solution and the Independence Principle for Compressible Turbulent Boundary Layers

I. E. Beckwith, I. Beckwith, 1974 .

COMPUTER PROGRAM FOR COMPRESSIBLE LAMINAR OR TURBULENT NONSIMILAR BOUNDARY LAYERS

I. E. Beckwith, D. Bushnell, B. A. Hixon, 1971 .

Detailed description and results of a method for computing mean and fluctuating quantities in turbulent boundary layers

I. E. Beckwith, D. Bushnell, 1968 .

Heat Transfer and Recovery Temperatures on a Sphere with Laminar, Transitional, and Turbulent Boundary Layers at Mach Numbers of 2.00 and 4.15

I. E. Beckwith, Ivan E. Beckwith, James J. Gallagher, 1957 .

Effects of wind-tunnel noise on swept-cylinder transition at Mach 3.5

I. E. Beckwith, T. R. Creel, F. Chen, 1986 .

Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel

I. E. Beckwith, T. Williams, C. Mclellan, 1950 .

Calculation of mean and fluctuating properties of the incompressible turbulent boundary layer

I. E. Beckwith, D. Bushnell, I. Beckwith, 1968 .

Experimental and theoretical investigation of boundary-layer instability mechanisms on a swept leading edge at Mach 3.5

I. E. Beckwith, Ivan E. Beckwith, Mujeeb R. Malik, 1987 .