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Measurements Of Fluctuating Pressures In 8 By 6 Foot Supersonic Wind Tunnel For Mach Number Range Of 056 To 207
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Book Synopsis Measurements of Fluctuating Pressures in 8- by 6-foot Supersonic Wind Tunnel for Mach Number Range of 0.56 to 2.07 by : Raymond J. Karabinus
Download or read book Measurements of Fluctuating Pressures in 8- by 6-foot Supersonic Wind Tunnel for Mach Number Range of 0.56 to 2.07 written by Raymond J. Karabinus and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Tests of Seven Static-pressure Probes at Transonic Speeds by : Francis J. Capone
Download or read book Wind-tunnel Tests of Seven Static-pressure Probes at Transonic Speeds written by Francis J. Capone and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests have been conducted to determine the errors of 3 seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 and at angles of attack from -1.7° to 8.4°. The test Reynolds number per foot varied from 3.35 x 106 to 4.05 x 106. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at ±37.5° from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of free-stream static pressure through the test angle-of-attack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of free-stream static pressure.
Book Synopsis Flow Quality and Operational Enhancements in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel by :
Download or read book Flow Quality and Operational Enhancements in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel written by and published by . This book was released on 1998 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of the Mach Number and Pressure on the Afterbody of a Blunt-nosed Model in Free Flight at Mach Numbers from 6.5 to 14 by : Simon C. Sommer
Download or read book Measurements of the Mach Number and Pressure on the Afterbody of a Blunt-nosed Model in Free Flight at Mach Numbers from 6.5 to 14 written by Simon C. Sommer and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Measurement of Pressure Fluctuations in a Hypersonic Wind Tunnel by : M. D. Brown
Download or read book The Measurement of Pressure Fluctuations in a Hypersonic Wind Tunnel written by M. D. Brown and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: The measurements of pressure fluctuations in a continuous-flow, hypersonic wind tunnel at Mach number 8.08 are described. The prime objective of the measurements was to determine amplitudes and frequencies of the various components of pressure fluctuation and to establish the accuracy with which such measurements might be made. A description of the measurement apparatus, its mode of use, and a sampling of typical pressure fluctuation measurements are presented. Merit factors, providing convenient numerical descriptions of such pressure fluctuations as were encountered, are defined. The test results were used in the assignment of values to these merit figures. Limited accuracy among the test results indicates the need for a dynamic pressure calibration apparatus of wide frequency and amplitude capability. The method used in calibrating the data readout equipment is presented. A treatise on the response of analog readout instruments to input signals representable by time-varying function is also presented. (Author).
Book Synopsis Low Speed Calibration of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel (1995 Test) by : E. Allen Arrington
Download or read book Low Speed Calibration of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel (1995 Test) written by E. Allen Arrington and published by . This book was released on 1997 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Baseline Calibration of the NASA Lewis Research Center 8-by 6-Foot Supersonic Wind Tunnel (1991 and 1992 Tests) by :
Download or read book Baseline Calibration of the NASA Lewis Research Center 8-by 6-Foot Supersonic Wind Tunnel (1991 and 1992 Tests) written by and published by . This book was released on 1998 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Measurements of Surface-pressure Fluctuations at Mach Numbers of 1.6, 2.0, and 2.5 Using 12 Different Transducers by : Thomas L. Lewis
Download or read book Wind-tunnel Measurements of Surface-pressure Fluctuations at Mach Numbers of 1.6, 2.0, and 2.5 Using 12 Different Transducers written by Thomas L. Lewis and published by . This book was released on 1972 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The turbulent boundary layer on the wall of a 9 by 7 foot wind tunnel was measured with 12 different transducers at Mach numbers of 1.6, 2.0, and 2.5. The results indicated that the wall surface-pressure-fluctuation field was more homogeneous at a Mach number of 2.5 than at Mach numbers of 1.6 or 2.0. A comparison of power-spectral-density data at Mach 2.5 with a summary of similar data (Mach 0.1 to 3.45) showed good agreement. The measurement uncertainty was greatest when frequencies were low and the surface-pressure-fluctuation field was homogeneous. The uncertainty at higher frequencies increased as the surface-pressure-fluctuation field became more inhomogeneous. Since transducer mounting effects and system noise levels were determined not to have contributed appreciably to measurement uncertainties, the result was attributed to an interaction between the surface-pressure-fluctuation field and the transducers. Corcos' correction for size effects improved the comparison between transducers at the high frequencies, but did not eliminate an apparent size effect at the lower frequencies.
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 Flow Field Surveys of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel (1993 Test) by :
Download or read book Flow Field Surveys of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel (1993 Test) written by and published by . This book was released on 1998 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Fluctuation Measurements in the NAL 0.2-m Supersonic Wind Tunnel by : Hideo Sawada
Download or read book Pressure Fluctuation Measurements in the NAL 0.2-m Supersonic Wind Tunnel written by Hideo Sawada and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Review of Flight and Wind Tunnel Measurements of Boundary Layer Pressure Fluctuations and Induced Structural Response by : David Alan Bies
Download or read book A Review of Flight and Wind Tunnel Measurements of Boundary Layer Pressure Fluctuations and Induced Structural Response written by David Alan Bies and published by . This book was released on 1966 with total page 100 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 Survey of Primary Flow Measurement Parameters at the NASA Langley Transonic Dynamics Tunnel by : David J. Piatak
Download or read book Survey of Primary Flow Measurement Parameters at the NASA Langley Transonic Dynamics Tunnel written by David J. Piatak and published by . This book was released on 2003 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fluctuating Pressures Measured Beneath a High-temperature, Turbulent Boundary Layer on a Flat Plate at a Mach Number of 5 by : Tony L. Parrott
Download or read book Fluctuating Pressures Measured Beneath a High-temperature, Turbulent Boundary Layer on a Flat Plate at a Mach Number of 5 written by Tony L. Parrott and published by . This book was released on 1989 with total page 44 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 Studies at Subsonic and Transonic Speeds of a Multiple-mission Variable-wing- Sweep Airplane Configuration by : William J. Alford
Download or read book Wind-tunnel Studies at Subsonic and Transonic Speeds of a Multiple-mission Variable-wing- Sweep Airplane Configuration written by William J. Alford and published by . This book was released on 1959 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
