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NOL Hypersonic Tunnel No. 4
NOL's Hypersonic Tunnel No. 4 is a continuous blow-down hypersonic tunnel designed for research and development testing of models, instrumentation, and wind tunnel components. It can operate at Mach numbers from 5 to 10 with supply pressures up to 52 atmospheres and supply temperatures up to 1700 R. This report summarizes the pertinent aerodynamic design criteria and operating experience compiled during its first eleven years of operation. Included are descriptions of the major components and their performance along with the flight simulation capability of the facility and a bibliography of previously published reports. (Author).
Sonic Boom Research
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Sonic Boom Research
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Wrap-around-fin (WAF) Pressure Distribution
The principal difference between a wrap around fin and a planar fin is that the WAF exhibits an induced rolling moment at zero degree angle of attack, while a straight fin has none. The Naval Ordnance Laboratory, along with other members of The Technical Cooperation Program, initiated a joint investigation into the causes of the induced roll moment. Measurements of the pressure distribution over both the convex and concave sides of a WAF showed that the primary difference in pressure across the fin occurred immediately behind the leading edge with the pressure on the convex side apparently being affected more by the curvature than that on the concave side. In general, for a WAF with fixed curvature, it appeared that the physical characteristic which would have the most effect on changing the roll moment would be the fin cross-sectional profile, especially the leading-edge profile. (Author).
Proceedings
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Temperature-step Effects on Direct Measurement of Skin-friction Drag
Wall-temperature discontinuities can occur in skin-friction balance tests whenever a balance drag element is thermally insulated from the surrounding test surface. An experimental study was conducted to investigate the effects of such a temperature step on the local friction drag. A temperature step was produced by varying the temperature of the NSWC skin-friction-balance drag element above the temperature of the surrounding nozzle wall. Drag-element temperatures ranged from 100 K to 240 K with the surrounding wall maintained at a temperature of 89 K. Nominal Mach numbers were 2.9 and 4.9 over a unit Reynolds number range of 2.6 to 20 million per meter. The results show that the value of the measured shear stress is higher than the cold wall value for a drag element which is at a higher temperature than the surrounding wall temperature and the change in shear stress is proportional to the difference between the drag element and the surrounding wall temperatures. The data has been correlated and corrections to previously published skin-friction results are presented.
ICO Pamphlet
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