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Sonic-boom Research
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The Near Noise Field of Static Jets and Some Model Studies of Devices for Noise Reduction
Choked operation of model jets with unheated air indicates the appearence of a discrete-frequency component of very large magnitude. Shadowgraph records of the flow show that this condtion is associated with the appearance of flow formations suggestive of partly formed toroidal vortices in the vicinity of the shocks. Elimination of these formations is found to eliminate the discrete component and thereby to reduce the overall noise level.
Ground Measurements of Sonic-boom Pressures for the Altitude Range of 10,000 to 75,000 Feet
The U.S. Air Force, National Aeronautics and Space Administration, and Federal Aviation Agency have engaged in a joint research program for the purpose of measuring sonic-boom pressure signatures. These measurements are presented for several locations for flight tests of fighter and bomber airplanes in the altitude range from about 10,000 to 75,000 feet and at Mach numbers from 1.1 to 2.0. Data were obtained for a variety of atmospheric wind and temperature gradients and for various flight paths and acceleration rates.
Oscillating Pressures Near a Static Pusher Propeller at Tip Mach Numbers Up to 1.20 with Special Reference to the Effects of the Presence of the Wing
Measurements of free-space oscillating presssures near a static propeller in the region where a wing might be located are presented for the tip Mach number range of 0.50 to 1.20 and these results are compared with available theory. Some measurements are also presented which were made near the tipes in the region where a fuselage might be located in order to extend the range of existing data from a tip Mach number of 1.00 to 1.20. In addition to a description of the free-space pressure field, meausrements are given from some of the same field points with a wing in place.
