Engineering topics
Publications and source records attributed to Harris, J. E..
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One of the principal design requirements for a quiet supersonic or hypersonic wind tunnel is to maintain laminar boundary layers on the nozzle walls and thereby reduce disturbance levels in the test flow. The conditions and apparent reasons for laminar boundary layers which have been observed during previous investigations on the walls of several nozzles for exit Mach numbers from 2 to 20 are reviewed. Based on these results, an analysis and an assessment of nozzle design requirements for laminar boundary layers including low Reynolds numbers, high acceleration, suction slots, wall temperature control, wall roughness, and area suction are presented.
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Numerical solution of flow equations for laminar, transitional, and turbulent compressible boundary layers for planar or axisymmetric flows
Numerical solution of compressible laminar, transitional, and turbulent boundary layer equations
Tools made of ice facilitate the forming or shaping of materials that are soft and sticky in the uncured state. The low-temperature of the ice slows the curing of the material, extending the working time available before setup. Handling problems are eliminated because the material does not adhere to the tool, and the melting ice serves as a lubricant.
Aerodynamic characteristics and pressure distributions of spherically blunted 25 degree cone investigated in nitrogen at Mach 20
Aerodynamic characteristics of slightly blunted conical bodies with 30 and 60 degree base flares
Force coefficient and moment coefficient correlations and air-helium simulation of spherically blunted cones - hypersonic wind tunnel testing