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Wind Tunnel Force And Pressure Tests Of Rocket Engine Nozzle Extensions On The 00667 Scale X 15 2 Model At Supersonic And Hypersonic Speeds
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Book Synopsis Wind-tunnel Force and Pressure Tests of Rocket-engine Nozzle Extensions on the 0.0667-scale X-15-2 Model at Supersonic and Hypersonic Speeds by : Earl J. Montoya
Download or read book Wind-tunnel Force and Pressure Tests of Rocket-engine Nozzle Extensions on the 0.0667-scale X-15-2 Model at Supersonic and Hypersonic Speeds written by Earl J. Montoya and published by . This book was released on 1969 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects by : Ralph C. Tolle
Download or read book Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects written by Ralph C. Tolle and published by . This book was released on 1996 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fluid Flow Analysis of a Hot-core Hypersonic-wind-tunnel Nozzle Concept by : John B. Anders
Download or read book Fluid Flow Analysis of a Hot-core Hypersonic-wind-tunnel Nozzle Concept written by John B. Anders and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
Book Synopsis NOL Hypervelocity Wind Tunnel by : Naval Ordnance Laboratory (White Oak, Md.).
Download or read book NOL Hypervelocity Wind Tunnel written by Naval Ordnance Laboratory (White Oak, Md.). and published by . This book was released on 1971 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Description and Preliminary Calibration Tests of a Small Arc-heated Hypersonic Wind Tunnel by : William B. Boatright
Download or read book Description and Preliminary Calibration Tests of a Small Arc-heated Hypersonic Wind Tunnel written by William B. Boatright and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The High-speed Flexible-throat Supersonic Wind Tunnel by :
Download or read book The High-speed Flexible-throat Supersonic Wind Tunnel written by and published by . This book was released on 1948 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High-speed Wind Tunnels by : Luigi Crocco
Download or read book High-speed Wind Tunnels written by Luigi Crocco and published by . This book was released on 1946 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: The importance assumed in recent times by experimental supersonic wind tunnels, as well as the power required, has brought about the need for a study which would permit a comparison of the types tested and the principal theoretical plans.
Book Synopsis High Speed Wind Tunnel Testing by : Alan Pope
Download or read book High Speed Wind Tunnel Testing written by Alan Pope and published by John Wiley & Sons. This book was released on 1965-01-15 with total page 496 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Testing of Interactions of High Altitude Rocket Plumes with the Free Stream by : H. K. Smithson
Download or read book Wind Tunnel Testing of Interactions of High Altitude Rocket Plumes with the Free Stream written by H. K. Smithson and published by . This book was released on 1971 with total page 440 pages. Available in PDF, EPUB and Kindle. Book excerpt: Interactions of model rocket plumes and the free stream at varying simulated altitudes have been investigated in an altitude simulation chamber. Free-stream variables were Mach number, gas, total temperature, and total pressure. Model rocket parameter variables were exhaust gas, area ratio, chamber total pressure and total temperature, and the orientation of the model relative to the free stream. In addition to pitot probe measurements, plume photographs and density measurements were obtained using the electron beam technique. (Author).
Book Synopsis Wind-Tunnel Tests on an Aircraft Designed for Supersonic Speeds, Etc by : WIND-TUNNEL TESTS.
Download or read book Wind-Tunnel Tests on an Aircraft Designed for Supersonic Speeds, Etc written by WIND-TUNNEL TESTS. and published by . This book was released on 1950 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Space shuttle wind tunnel testing program summary by : A. M. Whitnah
Download or read book Space shuttle wind tunnel testing program summary written by A. M. Whitnah and published by . This book was released on 1984 with total page 524 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic and Supersonic Wind Tunnel Force Tests on a 1/40-scale 8-jet VTOL with Wing Tip Mounted Nacelles (U) by : Kenneth A. Larsen
Download or read book Transonic and Supersonic Wind Tunnel Force Tests on a 1/40-scale 8-jet VTOL with Wing Tip Mounted Nacelles (U) written by Kenneth A. Larsen and published by . This book was released on 1961 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Parallel-jet Mixing on Downstream Mach Number and Stagnation Pressure with Application to Engine Testing in Supersonic Tunnels by : Harry Bernstein
Download or read book Effects of Parallel-jet Mixing on Downstream Mach Number and Stagnation Pressure with Application to Engine Testing in Supersonic Tunnels written by Harry Bernstein and published by . This book was released on 1953 with total page 686 pages. Available in PDF, EPUB and Kindle. Book excerpt: A one-dimensional analysis of the results of the parallel-jet mixing encountered in the testing of engines in supersonic wind tunnels is reported. Equations were derived for determining the total pressure and Mach number behind the tunnel terminal shock. The method represents a simple procedure for determining these quantities while a tunnel is still in the design stage. A specific example of the method is included.
Book Synopsis Annular Internal-external-expansion Rocket Nozzles for Large Booster Applications by : James F. Connors
Download or read book Annular Internal-external-expansion Rocket Nozzles for Large Booster Applications written by James F. Connors and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The High-Temperature Hypersonic Gasdynamics Facility Estimated Mach Number 6 Through 14 Performance by : Paul Czysz
Download or read book The High-Temperature Hypersonic Gasdynamics Facility Estimated Mach Number 6 Through 14 Performance written by Paul Czysz and published by . This book was released on 1963 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: The High Temperature Gas Dynamics Facility was developed as a result of the Aeronautical Systems Division's effort to extend the state-of the-art in hypersonic aerodynamic simulation. The facility is a hypersonic wind tunnel supplied with high pressure air, heated from a zirconia dioxide pebble heater. The maximum stagnation pressure and temperature is 40 atres and 4700 R, respectively. This facility is one of four of its kind in this hemisphere and the only Air Force facility of its type. This report discusses the modification of the facility to a two foot diameter test section with a Mach number range of 6 through 14 and its expected performance. This facility is scheduled to be operational in the Fall of 1963.
Book Synopsis Wind tunnel performance test of coannular plug nozzles by : Paul S. Staid
Download or read book Wind tunnel performance test of coannular plug nozzles written by Paul S. Staid and published by . This book was released on 1978 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design and Operation of a Continuous-flow Hypersonic Wind Tunnel Using a Two-dimensional Nozzle by : Harris M. Schurmeier
Download or read book Design and Operation of a Continuous-flow Hypersonic Wind Tunnel Using a Two-dimensional Nozzle written by Harris M. Schurmeier and published by . This book was released on 1959 with total page 304 pages. Available in PDF, EPUB and Kindle. Book excerpt:
