SONIC-BOOM OF THE OBLIQUE FLYING WING

This article presents an analysis of oblique flying wing sonic boom ch aracteristics. This long asymmetric wing provides a reduction in sonic boom loudness as well as aerodynamic and structural improvements over conventional transports. The wing is represented by an oblique line e quivalent area distribution, a panel model, and a high-definition surf ace model. The near-field pressure signature of the first two represen tations is found using the Whitham F-function method applied to the ob lique equivalent area distribution and the panel model. The near-field pressure distribution of the high-definition surface model was found using TranAir, a full-potential analysis code. Good agreement between the methods was found. The near-field signature is extrapolated throug h the standard atmosphere by the Thomas waveform parameter method. The asymmetry in the geometry leads to an asymmetrical sonic boom under t he flight track. The bow shock amplitude is typically between 50-75 N/ m(2) depending on the size, weight, and altitude of the configuration. The aft shock has only one-half the amplitude of the bow shock due to favorable volume-lift interference. This article also includes a simp le method to estimate the maximum sonic boom overpressures of oblique flying wings.