WorldCat Identities

Lew, Henry G.

Overview
Works: 12 works in 17 publications in 1 language and 24 library holdings
Roles: Author
Classifications: TL507,
Publication Timeline
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Most widely held works by Henry G Lew
The compressible laminar boundary layer over a flat plate with uniform suction and heat transfer at the wall by Henry G Lew( Book )

4 editions published in 1948 in English and held by 5 WorldCat member libraries worldwide

The cooling of a flat plate in a laminar compressible flow by uniform fluid injection by Henry G Lew( Book )

2 editions published in 1948 in English and held by 3 WorldCat member libraries worldwide

Approximate solution for shock waves in a steady, one-dimensional, viscous and compressible gas by Paul Lieber( Book )

1 edition published in 1949 in English and held by 2 WorldCat member libraries worldwide

The compressible laminar boundary layer over a flat plate with partial or variable suction at the wall by Henry G Lew( Book )

1 edition published in 1949 in English and held by 2 WorldCat member libraries worldwide

Effect of mass transfer and body forces on two phase boundary layers by Jerome Ben Fanucci( Book )

1 edition published in 1959 in English and held by 2 WorldCat member libraries worldwide

A study of melting surfaces by Henry G Lew( Book )

1 edition published in 1959 in English and held by 2 WorldCat member libraries worldwide

On the stability of a laminar compressible boundary layer over a flat plate subject to uniform suction and injection by Paul A Libby( Book )

1 edition published in 1948 in English and held by 2 WorldCat member libraries worldwide

Shock Layer Ionization at High Altitudes( Book )

1 edition published in 1970 in English and held by 1 WorldCat member library worldwide

Electron production from the high temperature shock layer of blunt re-entry bodies are considered at high altitudes. The dissociation and subsequent ionization of air species due to the high flight speeds are predicted by analytical techniques with the consideration of the prevalent viscous effects at low density throughout the flow and with chemical relaxation of these species. The effect of vibrational nonequilibrium is also determined. Finally the spatial distributions of air species, temperature, velocity, and electron concentrations over a sphere-cone body, the Trailblazer, is mapped in detail for several altitude velocity conditions. (Author)
A study of electron density distribution in viscous flows by Henry G Lew( Book )

2 editions published in 1972 in English and held by 1 WorldCat member library worldwide

The electron production for the viscous flow over a body in hypersonic flight and high altitudes has been studied and predictions of its magnitude have been made. The flight parameters selected for this study were typical of those encountered by the reentry nosecone experiments launched in a series of Air Force Cambridge Research Laboratories/Trailblazer 2 Rocket Flights. A chemical system appropriate for high temperature dissociated and ionized air has been utilized. In addition to NO+ the chemical kinetic system includes N2+, O2+, O+, N+. Both chemical and nonequilibrium effects are included. An evaluation of various wall conditions such as catalyticity and slip, of diffusion coefficients, and of magnitudes of various rate constants has also been considered
Angle-of-Attack Effects on Electron Density Distribution over Blunt Bodies( Book )

1 edition published in 1974 in English and held by 1 WorldCat member library worldwide

The electron density distribution over re-entry bodies of the blunt sphere cone class at angle-of-attack to the hypersonic free stream is studied in this report. The shock layer is considered as a mixture of dissociated and ionized air species chemically reacting at finite nonzero rates to produce electrons which are distributed three dimensionally by the nonzero angle-of-attack. Both the viscous three dimensional boundary layer and inviscid flow are included in the study. A numerical implicit finite difference scheme is utilized in the method of solution. Results are given in this report for the hypersonic flow over the AFCRL Trailblazer II body at the angle-of-attack of 12 degrees for the two altitudes of 240,000 ft and 220,000 ft
Electron Density Distribution over Blunt Bodies in Three Dimensional Flow( Book )

1 edition published in 1973 in English and held by 1 WorldCat member library worldwide

The electron density distribution in the shock layer of reentry bodies in hypersonic flight is determined by many factors. Among these, the effect of a nonzero angle-of-attack of the body to the free stream is an important one. The report considers the three dimensional boundary layer over a sphere-cone body at hypersonic flight and a nonzero angle-of-attack at conditions where the air is a mixture of dissociated and ionized components reacting with each other at finite chemical rates. The equations of motion for the three dimensional flow are formulated and method of attack by an implicit finite difference scheme is used for their solutions
Fluctuating Pressure Loads for Hypersonic Vehicle Structures. Phase 1( )

1 edition published in 1991 in English and held by 0 WorldCat member libraries worldwide

This investigation was conducted to determine the ability to predict acoustic loads on supersonic/hypersonic structures with attached and separated flows. These techniques, which are based on laws governing boundary layer flow and shock physics, provide scaling parameters to extrapolate ground test results to flight conditions and can be used for the design process. It was determined that efficient, thin aerodynamic control surfaces generally produce weak shock/ boundary layers interactions where the rms pressure levels are not significantly augmented over attached flow levels. The exception to these findings include: (1) corner flow (inlet and stabilizers); (2) bow shock interaction (inlet and stabilizer); and (3) shock on shock/boundary layer (cowl/inlet, bow shock/inlet, and bow/inlet/cowl). Other potential interactions that may cause problems have been identified as: (1) axial offset (non-common intersection of two planes); (2) shock interaction with laminar boundary layers; (3) angle of attack effects; and (4) viscous approach flow along ramp leading to the inlet. An experimental program is recommended to address these issues; in particular for M> 3 where acoustic data does not exist. These experiments should be conducted in a facility that allows for preliminary test runs to ensure desired results. The WRDC Mach 3 and Mach 12 facilities are recommended for a Phase II investigation. Results of the Phase I and II efforts will provide the ability to design structures subject to complex flow interactions such as the National AeroSpace Plane
 
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Audience level: 0.77 (from 0.72 for The compre ... to 1.00 for Electron D ...)

Languages
English (17)