A Shock Tube For Producing Subsonic Transonic And Supersonic Flows For Aerodynamic Testing PDF Download
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| Author | : |
| Publisher | : |
| Total Pages | : 24 |
| Release | : 1963 |
| Genre | : |
| ISBN | : |
Download A SHOCK TUBE FOR PRODUCING SUBSONIC, TRANSONIC, AND SUPERSONIC FLOWS FOR AERODYNAMIC TESTING. Book in PDF, ePub and Kindle
A shock tube is proposed in which the flow conditions between the shock wave and advancing interface are expected to range from low subsonic to moderate supersonic speeds. Furthermore, testing times of 10 msec or more are predicted, a time quite adequate for aerodynamic force measurements. The driven section in the proposed facility is large enough to accommodate large scale models. To test the feasibility of the proposed tube, a shock tube was assembled using a surplus 7-foot diameter vacuum tank as a driven section and 12-in. flanged pipe for the driver. A series of tests were performed to determine shock formation time and experimental testing time. The results of thest tests are reported.
| Author | : John W. Davis |
| Publisher | : |
| Total Pages | : 9 |
| Release | : 1968 |
| Genre | : Aerodynamics |
| ISBN | : |
Download A Shock Tube Technique for Producing Subsonic, Transonic and Supersonic Flows with Extremely High Reynolds Numbers Book in PDF, ePub and Kindle
| Author | : Frederick William Geiger |
| Publisher | : |
| Total Pages | : 216 |
| Release | : 1949 |
| Genre | : Transportation |
| ISBN | : |
Download The Shock Tube as an Instrument for the Investigation of Transonic and Supersonic Flow Patterns Book in PDF, ePub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 704 |
| Release | : 1995 |
| Genre | : Aeronautics |
| ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
| Author | : Charles William Mautz |
| Publisher | : |
| Total Pages | : 276 |
| Release | : 1949 |
| Genre | : |
| ISBN | : |
Download The Use of the Shock Tube in the Production of Uniform Fields of Transonic and Supersonic Flow Book in PDF, ePub and Kindle
| Author | : F. W. Geiger |
| Publisher | : |
| Total Pages | : |
| Release | : 1981 |
| Genre | : |
| ISBN | : |
Download The Shock Tube as an Instrument for the Investigation of Transonic and Supersonic Flow Patterns Book in PDF, ePub and Kindle
| Author | : I. I. Glass |
| Publisher | : |
| Total Pages | : 642 |
| Release | : 1959 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Download Handbook of Supersonic Aerodynamics Book in PDF, ePub and Kindle
| Author | : Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md |
| Publisher | : |
| Total Pages | : 642 |
| Release | : 1950 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Download Handbook of Supersonic Aerodynamics Book in PDF, ePub and Kindle
| Author | : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel |
| Publisher | : |
| Total Pages | : 450 |
| Release | : 1971 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
Download Facilities and Techniques for Aerodynamic Testing at Transonic Speeds and High Reynolds Number Book in PDF, ePub and Kindle
In September 1968, the FDP of AGARD held a specialists' meeting in Paris on transonic aerodynamics, in recognition of the fact that the absence of adequate theoretical methods and wind-tunnels of high enough Reynolds number had already led to costly shortcomings in the transonic performance of certain combat and transport aircraft. Since projected aerospace systems, military, civil and space-oriented, would involve flight at Reynolds number of up to 100 million, the FDP undertook an examination of the requirements of NATO nations for wind tunnel facilities for testing large models at high Reynolds numbers.
| Author | : Robert L. Trimpi |
| Publisher | : |
| Total Pages | : 674 |
| Release | : 1955 |
| Genre | : Gas flow |
| ISBN | : |
Download A Theory for Predicting the Flow of Real Gases in Shock Tubes with Experimental Verification Book in PDF, ePub and Kindle
The nonlinear characteristic differential equations applicable to a quasi-one-dimensional unsteady channel flow with friction and heat transfer are linearized and integrated in functional form for the particular study of small perturbations from ideal shock-tube flows. If the equivalence of unsteady- and steady-flow boundary layers is assumed, the problem of determining the perturbation in the unsteady flow reduces to an evaluation of the drag of a flat plate in the equivalent steady flow.
