Abstract
The near-field pressure distributions, which are needed to predict the far-field sonic-boom signatures, are measured experimentally with use of the wind tunnel of Mach number 2.0 for the supersonic aircraft models having different wing planforms and nose configurations in the cases with and without lift. The overall boom characteristics are also discussed in the basis of visualization of the flow patterns around the aircraft model with use of Schlieren technique and pressure measurement at off-centerline region by changing the model roll angle. The major results are as follows: As for the wing planform, the near-field peak pressures by an arrow wing and a cranked arrow wing are smaller than that of a delta wing, which suggests that they will give smaller sonic boom intensity. As for the nose configuration, a blunt nose is considered to be effective for sonic boom reduction, but because of a noticeable increase of drag, a careful shaping of nose has to be needed.
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