NOL Hypervelocity Wind Tunnel
| Author | : Naval Ordnance Laboratory (White Oak, Md.). |
| Publisher | : |
| Total Pages | : 154 |
| Release | : 1971 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
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NOL Hypervelocity Wind Tunnel: Aerodynamic design
| Author | : Naval Ordnance Laboratory (White Oak, Md.). |
| Publisher | : |
| Total Pages | : 92 |
| Release | : 1971 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
Download NOL Hypervelocity Wind Tunnel: Aerodynamic design Book in PDF, ePub and Kindle
NOL Hypervelocity Wind Tunnel
| Author | : Naval Ordnance Laboratory (White Oak, Md.). |
| Publisher | : |
| Total Pages | : 70 |
| Release | : 1971 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
Download NOL Hypervelocity Wind Tunnel Book in PDF, ePub and Kindle
The NOL Hypervelocity Wind Tunnel
| Author | : |
| Publisher | : |
| Total Pages | : 13 |
| Release | : 1971 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
Download The NOL Hypervelocity Wind Tunnel Book in PDF, ePub and Kindle
Includes bibliographical references.
NOL Hypervelocity Wind Tunnel. Report No. 2: Nozzle Design
| Author | : |
| Publisher | : |
| Total Pages | : 150 |
| Release | : 1971 |
| Genre | : |
| ISBN | : |
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The NOL hypervelocity wind tunnel will provide a high Reynolds number turbulent flow simulation in the Mach number range 10 to 20. This facility, much needed for large-scale testing of hypersonic vehicles, will be operational late in 1972. This report presents the detailed procedure used to design three nozzles for the facility. Pressure and temperature effects on the thermodynamic properties of nitrogen are taken into account in both the inviscid core and the boundary layer calculations. The supersonic portion of the inviscid core is calculated by the method of characteristics and the subsonic portion is approximated as a one-dimensional flow. The boundary layer calculation procedure is based on an integral moment of momentum equation and is valid for thick as well as thin boundary layers.
NOL Mach 18 Hypervelocity Research Tunnel
| Author | : Ray H. Cornett |
| Publisher | : |
| Total Pages | : 58 |
| Release | : 1974 |
| Genre | : Diffusers |
| ISBN | : |
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The aerodynamic capabilities and physical characteristics of the Naval Ordnance Laboratory's Mach number 18 Hypervelocity Research Tunnel are described. This tunnel is a high-pressure, blowdown-type facility that uses nitrogen as the working gas. The facility provides a maximum test section Reynolds number of 0.2 million per meter (0.7 million per foot) at the maximum stagnation pressure of 700 atmospheres and a supply temperature of 2100 Kelvin. A forced-convection electric heater with a graphite heater element is used to achieve the required flow temperatures. The axisymmetric, contoured nozzle is 3.96 meters long with an exit diameter of 0.61 meters. Flow times are from one to four minutes.
NOL Hypersonic Tunnel No. 4
| Author | : James E. Danberg |
| Publisher | : |
| Total Pages | : 84 |
| Release | : 1964 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
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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).
NOL Hypervelocity Wind Tunnel Report No. III: Theoretical Analysis of the Boundary Layer in the Nozzle
| Author | : Neal Tetervin |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1971 |
| Genre | : |
| ISBN | : |
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The equations used to calculate the boundary layer properties for use in the design of the Mach 10, 15, and 20 axisymmetric nozzles of the hypervelocity wind tunnel at NOL are derived. One equation is the integral moment-of-momentum differential equation for the boundary layer velocity profile shape parameter; the form of the equation is valid for a real gas. This equation is used with an axisymmetric integral momentum equation that is valid for thick as well as for thin boundary layers to calculate the total thickness and the displacement effect of the boundary layer. (Author).
Simplified Performance Data for the NOL Hypersonic Wind Tunnel
| Author | : Peter P. Wegener |
| Publisher | : |
| Total Pages | : 14 |
| Release | : 1947 |
| Genre | : |
| ISBN | : |
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The Specific Heats of Air in the Range of NOL Hypersonic Wind Tunnel Operation
| Author | : Peter P. Wegener |
| Publisher | : |
| Total Pages | : 2 |
| Release | : 1947 |
| Genre | : |
| ISBN | : |
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