Nol Hypersonic Tunnel No 4 Results 2 Diffuser Investigation
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| Total Pages | : 45 |
| Release | : 1952 |
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Results of a diffuser investigation in the continuous 12 x 12 cm on Hypersonic Tunnel No. 4 are presented. A brief introduction describes previous supersonic diffuser work. The diffuser investigated and the experimental techniques are then discussed. The results show first that air condensation has little or no effect on diffuser performance. Data on diffuser throat areas and overall pressure ratios needed to start and maintain hypersonic flow are given for a Mach number range from 5.9 to 9.6. The effect of two different throat locations and different diffuser configurations on tunnel performance is investigated. A peaked throat diffuser with 3 deg wall divergence aft of the throat was selected for a more detailed study. The pressure recovered by this optimum diffuser in the range 5.9
| Author | : James E. Danberg |
| Publisher | : |
| Total Pages | : 84 |
| Release | : 1964 |
| Genre | : Hypersonic wind tunnels |
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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).
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| Total Pages | : 72 |
| Release | : 1956 |
| Genre | : Science |
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| Author | : |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1957 |
| Genre | : Aerodynamics |
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| Author | : Patrick J. Johnston |
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| Total Pages | : 24 |
| Release | : 1960 |
| Genre | : Mach number |
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| Author | : |
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| Total Pages | : 424 |
| Release | : 1971 |
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| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 790 |
| Release | : 1955 |
| Genre | : Aeronautics |
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| Author | : |
| Publisher | : |
| Total Pages | : 652 |
| Release | : 1952 |
| Genre | : Science |
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| Author | : Harvey G. McComb |
| Publisher | : |
| Total Pages | : 702 |
| Release | : 1955 |
| Genre | : Cylinders |
| ISBN | : |
Comparisons are made between a theory for calculating stresses about rectangular cutouts in circular cylinders of semimonocoque construction published in NACA TN 3200 and previously published NACA experimental data. The comparisons include stresses in the stringers and shear stresses in the center of the shear panels in the neighborhood of the cutout. The theory takes into account the bending flexibility of the rings in the structure, and this factor is found to be important in the calculation of stresses about cutouts. In general, when the ring flexibility is considered, good agreement is exhibited between the calculated and experimental results.
| Author | : North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development |
| Publisher | : |
| Total Pages | : 458 |
| Release | : 1954 |
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