Engineering topics
Publications and source records attributed to Hunton, L. W..
A wind-tunnel investigation was conducted to determine the effect of wing planform on sonic boom at Mach numbers of 1.7, 2.0, and 2.7. The results of the investigation show that the wing leading-edge sweep is one of the primary planform variables affecting the overpressure characteristics.
An experimental investigation was made to examine the applicability of methods used to determine internal drag of small ducts and to study some of the problems encountered in assessing momentum losses in such ducts. Test Mach numbers ranged from 3.7 to 4.4 at angles of attack of 0 and 5 degrees and at a constant Reynolds number of 4.3 million per foot. The configurations represented small ducts used to simulate external aerodynamics of air breathing propulsion systems and consisted of wing nacelle models of ducts with circular, square, and rectangular inlets and with a two-dimensional inlet.
Aerodynamic method of characteristics for pressure field calculations about wing-body combinations
Pressure prediction methods, Mach number effects, and sonic boom reduction for supersonic transport
Mach number and geometry effects on level of sonic boom overpressure and applicability of Whitham theory to calculation of sonic boom
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Sonic boom characteristics of proposed supersonic and hypersonic aircraft
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Results of experimental and analytic studies of delta-wing supersonic transport configurations
Study of delta-wing configurations for supersonic transport application and their relation to aircraft performance
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