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Wind Tunnel Tests Of Supersonic Two Dimensional And Half Axisymmetric Inlet Models In A Nonuniform Flow Field At Mach Numbers From 15 Through 25
Download Wind Tunnel Tests Of Supersonic Two Dimensional And Half Axisymmetric Inlet Models In A Nonuniform Flow Field At Mach Numbers From 15 Through 25 full books in PDF, epub, and Kindle. Read online Wind Tunnel Tests Of Supersonic Two Dimensional And Half Axisymmetric Inlet Models In A Nonuniform Flow Field At Mach Numbers From 15 Through 25 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5 by : Frederick K. Hube
Download or read book Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5 written by Frederick K. Hube and published by . This book was released on 1971 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5 by : Frederick K. Hube
Download or read book Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5 written by Frederick K. Hube and published by . This book was released on 1971 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of Two-dimensional and Half-axisymmetric Inlet Models at Mach Numbers 1.5 Through 3.0 by : Frederick K. Hube
Download or read book Wind Tunnel Tests of Two-dimensional and Half-axisymmetric Inlet Models at Mach Numbers 1.5 Through 3.0 written by Frederick K. Hube and published by . This book was released on 1970 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of Two-dimensional and Half-axisymmetric Inlet Models at Mach Numbers 1.5 Through 3.0 by : Frederick K. Hube
Download or read book Wind Tunnel Tests of Two-dimensional and Half-axisymmetric Inlet Models at Mach Numbers 1.5 Through 3.0 written by Frederick K. Hube and published by . This book was released on 1970 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Inlet Investigation by : T. W. Tsukahira
Download or read book Supersonic Inlet Investigation written by T. W. Tsukahira and published by . This book was released on 1971 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
Book Synopsis Supersonic Inlet Investigation. Volume III. Wind Tunnel Data Report by : Tatsuo W. Tsukahira
Download or read book Supersonic Inlet Investigation. Volume III. Wind Tunnel Data Report written by Tatsuo W. Tsukahira and published by . This book was released on 1971 with total page 159 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately .125 scale model air induction systems. The baseline models included a two-dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers. (Author).
Book Synopsis Supersonic Wind Tunnel Tests of a Half-Axisymmetric 12 Deg-Spike Inlet to a Rocket-Based Combined-Cycle Propulsion System by :
Download or read book Supersonic Wind Tunnel Tests of a Half-Axisymmetric 12 Deg-Spike Inlet to a Rocket-Based Combined-Cycle Propulsion System written by and published by . This book was released on 2001 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Inlet Investigation by : T. W. Tsukahira
Download or read book Supersonic Inlet Investigation written by T. W. Tsukahira and published by . This book was released on 1971 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reported herein are the results of an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests. The baseline models included a two-dimensional external compression inlet, a two-dimensional mixed compression inlet, and a half-axisymmetric external compression inlet. Alternate configurations for the external compression baseline inlets in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a non-uniform flow field, the later representing partial simulation of a vehicle flow field. Inlet steady state performance was characterized in terms of pressure recovery, pressure distortion, and turbulence levels at a simulated compressor face and immediately downstream of the inlet throat. In addition, detailed analysis and correlation of data obtained with high response dynamic instrumentation were made.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1966 with total page 1466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Journal of Propulsion and Power by :
Download or read book Journal of Propulsion and Power written by and published by . This book was released on 2008 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Flow-field Development for a Series of Sonic-boom Wind-tunnel Models by :
Download or read book Investigation of Flow-field Development for a Series of Sonic-boom Wind-tunnel Models written by and published by . This book was released on 1971 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1992 with total page 1046 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section by : Rudolf Hermann
Download or read book Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section written by Rudolf Hermann and published by . This book was released on 1950 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Book Synopsis SUPERSONIC WIND TUNNEL TESTS OF A HALF-AXISYMMETRIC 12 DEG-SPIKE INLET TO A ROCKET-BASED COMBINED-CYC... NASA/TM-2001-210567... AUG. 16, 200 by :
Download or read book SUPERSONIC WIND TUNNEL TESTS OF A HALF-AXISYMMETRIC 12 DEG-SPIKE INLET TO A ROCKET-BASED COMBINED-CYC... NASA/TM-2001-210567... AUG. 16, 200 written by and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Flow Field Visualization Studies of the MŒʻ by : Karl Garcia
Download or read book Supersonic Flow Field Visualization Studies of the MŒʻ written by Karl Garcia and published by . This book was released on 2001 with total page 91 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic tests of the conical flow derived MŒʻ = 6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel. These tests are part of a continuing effort to study the characteristics of waverider configured vehicles. Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel. Tests at Mach numbers of MŒʻ = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MŒʻ = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MŒʻ = 1.7 and 2.8. Horizontal (side-view) and vertical (top-view) mounted shadowgraph pictures and pressure sensitive paint images were taken at pitch angles of ♭¿ = 0Œʺ, 2Œʺ and 4Œʺ. The Mach 4 shadowgraph and pressure sensitive paint results correlate well with previous CFD results using the three-dimensional Price waverider model. The choked flow tests at MŒʻ = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum.
Book Synopsis An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 by : C. J. Schueler
Download or read book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 written by C. J. Schueler and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the test section flow blockage characteristics was conducted in the 12- by 12 inch supersonic wind tunnel (Tunnel E-1) of the Von Karman Gas Dynamics Facility (AEDC). The purpose of the tests was to determine whether a method of predicting the maximum size model which will permit the establishment of supersonic flow, based on the model frontal area and bow shock-wave strength, is applicable over a wide range of Mach numbers. The tests conducted over the Mach number range from 1.5 to 5 using test models consisting of 15, 20, and 20 degrees half-angle cones, cone-cylinder combinations, and a series of discs. The inadequacy of the one dimensional, normal shock theory for predicting allowable model sizes was reconfirmed in these tests. Furthermore a correlation based on shock wave strength and model frontal area was found to be suitable only over a limited range of Mach numbers. Permissible hemisphere-cylinder model sizes from several wind tunnels covering the Mach number range from 1.5 to 19.5 are also presented.
Book Synopsis Wind Tunnel Tests of a Two-Thirds Scale NASA HRE Inlet at Mach Numbers 4, 5, 6, and 8 by : Frederick K. Hube
Download or read book Wind Tunnel Tests of a Two-Thirds Scale NASA HRE Inlet at Mach Numbers 4, 5, 6, and 8 written by Frederick K. Hube and published by . This book was released on 1969 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An axisymmetric, variable geometry, two-thirds scale model of a NASA Hypersonic Research Engine (HRE) inlet was tested at Mach numbers 4, 5, 6, and 8. Surface pressures and temperatures were measured on the inlet centerbody and inside the cowl. Pitot pressure measurements were made at four stations along the internal passage. The measurements were obtained for various cowl positions at free-stream Reynolds numbers from 1.08 to 5.76 million (based on a 12-in. cowl diameter) and over an angle-of-attack range from -5 to +5 deg. The model walls were internally cooled and maintained at a minimum frost-free condition at each test condition. Selected results are presented to illustrate the effects of cowl position, angle of attack, Mach number, and Reynolds number on the surface and rake station measurements. Inlet performance data at design operating conditions are also presented. (Author).
