NOL Hypervelocity Wind Tunnel: Aerodynamic design
Author | : Naval Ordnance Laboratory (White Oak, Md.). |
Publisher | : |
Total Pages | : 92 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
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Author | : Naval Ordnance Laboratory (White Oak, Md.). |
Publisher | : |
Total Pages | : 92 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Author | : Naval Ordnance Laboratory (White Oak, Md.). |
Publisher | : |
Total Pages | : 70 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Author | : Naval Ordnance Laboratory (White Oak, Md.). |
Publisher | : |
Total Pages | : 154 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Author | : James E. Danberg |
Publisher | : |
Total Pages | : 84 |
Release | : 1964 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
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).
Author | : |
Publisher | : |
Total Pages | : 150 |
Release | : 1971 |
Genre | : |
ISBN | : |
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.
Author | : |
Publisher | : |
Total Pages | : 13 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Includes bibliographical references.
Author | : Frank P. Baltakis |
Publisher | : |
Total Pages | : 146 |
Release | : 1968 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
The report summarizes the performance capability data of the U.S. Naval Ordnance Laboratory's Hypersonic Tunnel. The report includes a brief description of the facility, overall performance capability data, nozzle calibration data, and some nozzle boundary-layer thickness and temperature variation data. The nozzle aerodynamic design method is indicated and its adequacy in the range of the supply and test flow conditions of the Hypersonic Tunnel is briefly discussed. (Author).
Author | : Colin Britcher |
Publisher | : Academic Press |
Total Pages | : 672 |
Release | : 2023-10-20 |
Genre | : Technology & Engineering |
ISBN | : 0128181001 |
Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed Provides a discussion of similarity laws as well as material on statistical analysis Includes coverage on facility-to-facility and facility-to-CFD correlation Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing
Author | : Neal Tetervin |
Publisher | : |
Total Pages | : 44 |
Release | : 1971 |
Genre | : |
ISBN | : |
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).