Engineering topics
Publications and source records attributed to Hicks, R. M..
Pressure signatures were measured at roll angles ranging from 0 to 180 deg for a .016-scale model of the Apollo Command Module spacecraft at 25 deg angle of attack. The test Mach numbers ranged from 1.50 to 10.02.
Technique of extrapolating measured near-field overpressure data to larger altitude applied to wind tunnel overpressure data
Parameter effects on coalescence of nose and wing shocks in wing/body pressure signature for sonic boom reduction
Extrapolation of measured overpressure data for predicting sonic boom characteristics of different aerodynamic configurations
Comparison of spherical and triangular boundary layer trips on flat plate at supersonic speed
Supersonic skin friction measurements in grit type boundary layer transition trips with zero heat transfer
Aircraft sonic boom characteristics predicted from near field data obtained in wind tunnel
Boundary layer trips for producing turbulence in hypersonic flow
Aerodynamic characteristics of leading-edge sweep wing-body combinations
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Explore the source record for details and available documents.
Guidelines applicable to grit-type boundary layer transition trips near leading edges of wind tunnel models
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Explore the source record for details and available documents.
Exact equation for cross-sectional area distribution of maximum sonic boom over pressure at zero lift for two configurations