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Reynolds Number Effects In Transonic Flow
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Book Synopsis Reynolds Number Effects in Transonic Flow by : A. Elsenaar
Download or read book Reynolds Number Effects in Transonic Flow written by A. Elsenaar and published by . This book was released on 1988 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reynolds number effects in transonic flow are critically reviewed. This review, which may be considered a supplement to AR 224 'Boundary Layer Simulation and Control in Wind Tunnels', is mainly concered with a discussion of viscous effects actually observed on realistic configurations. The following geometries are considered: Airfoils and high aspect ratio wings typical and transport aircraft, fighter-type low aspect ratio delta wings, tow- and three-dimensional bodies characteristic of missiles and combat aircraft fuselages, and afterbodies. "Pseudo"--Reynolds number on the wind tunnel environment and in turn affect the flow about a model. As an introduction, a brief retrospect of the "history" of Reynolds number effect is presented. This AGARDograph has been produced at the request of the Fluid Dynamics Panel of AGARD.
Book Synopsis Reynolds Number Influences in Aeronautics by :
Download or read book Reynolds Number Influences in Aeronautics written by and published by . This book was released on 1993 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range by : John M. Swihart
Download or read book Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range written by John M. Swihart and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 106 to 39 x 106, and on maximum diameter from 1.35 x 105 to 4.53 x 105. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Book Synopsis The Effects of Reynolds Number, Mach Number, Spin Rate, and Other Variables on the Aerodynamics of Spheres at Subsonic and Transonic Velocities by : C. M. Sabin
Download or read book The Effects of Reynolds Number, Mach Number, Spin Rate, and Other Variables on the Aerodynamics of Spheres at Subsonic and Transonic Velocities written by C. M. Sabin and published by . This book was released on 1956 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Reynolds Number and Mach Number on Flow Angularity Probe Sensitivity by : Leigh Ann Smith
Download or read book Effect of Reynolds Number and Mach Number on Flow Angularity Probe Sensitivity written by Leigh Ann Smith and published by . This book was released on 1986 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Fluctuating Pressure in a Rectangular Cavity in Transonic Flow at High Reynolds Numbers by : M. B. Tracy
Download or read book Measurements of Fluctuating Pressure in a Rectangular Cavity in Transonic Flow at High Reynolds Numbers written by M. B. Tracy and published by . This book was released on 1992 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers by : C. E. Robinson
Download or read book Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by C. E. Robinson and published by . This book was released on 1976 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to study the effects of Reynolds number variation on isolated nozzle afterbody performance. A strut-mounted cone-cylinder model with three separate afterbody configurations for Aerospace Research and Development (AGARD) was used for this investigation. This program was conducted in two phases distinguished by the model size and the wind tunnels used to obtain the experimental results. The effect of tunnel wall porosity on nozzle afterbody (NAB) performance was investigated.
Download or read book High Reynolds Number Research written by and published by . This book was released on 1977 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Fluctuating Pressure in a Rectangular Cavity in Transonic Flow at High Reynolds Numbers by : M. B. Tracy
Download or read book Measurements of Fluctuating Pressure in a Rectangular Cavity in Transonic Flow at High Reynolds Numbers written by M. B. Tracy and published by . This book was released on 1992 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Reynolds Number and Mach Number on Flow Angularity Probe Sensitivity by : Leigh Ann Smith
Download or read book Effect of Reynolds Number and Mach Number on Flow Angularity Probe Sensitivity written by Leigh Ann Smith and published by . This book was released on 1986 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Study of the Effects of Reynolds Number and Mach Number on Constant Pressure Coefficient Jump for Shock-induced Trailing-edge Separation by : Atlee M. Cunningham
Download or read book A Study of the Effects of Reynolds Number and Mach Number on Constant Pressure Coefficient Jump for Shock-induced Trailing-edge Separation written by Atlee M. Cunningham and published by . This book was released on 1987 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722362751 Total Pages :32 pages Book Rating :4.3/5 (627 download)
Book Synopsis Measurements of Fluctuating Pressure in a Rectangular Cavity in Transonic Flow at High Reynolds Numbers by : National Aeronautics and Space Administration (NASA)
Download or read book Measurements of Fluctuating Pressure in a Rectangular Cavity in Transonic Flow at High Reynolds Numbers written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experiment was performed in the Langley 0.3 meter Transonic Cryogenic Tunnel to study the internal acoustic field generated by rectangular cavities in transonic and subsonic flows and to determine the effect of Reynolds number and angle of yaw on the field. The cavity was 11.25 in. long and 2.50 in. wide. The cavity depth was varied to obtain length-to-height (l/h) ratios of 4.40, 6.70, 12.67, and 20.00. Data were obtained for a free stream Mach number range from 0.20 to 0.90, a Reynolds number range from 2 x 10(exp 6) to 100 x 10(exp 6) per foot with a nearly constant boundary layer thickness, and for two angles of yaw of 0 and 15 degs. Results show that Reynolds number has little effect on the acoustic field in rectangular cavities at angle of yaw of 0 deg. Cavities with l/h = 4.40 and 6.70 generated tones at transonic speeds, whereas those with l/h = 20.00 did not. This trend agrees with data obtained previously at supersonic speeds. As Mach number decreased, the amplitude, and bandwidth of the tones changed. No tones appeared for Mach number = 0.20. For a cavity with l/h = 12.67, tones appeared at Mach number = 0.60, indicating a possible change in flow field type. Changes in acoustic spectra with angle of yaw varied with Reynolds number, Mach number, l/h ratios, and acoustic mode number. Tracy, M. B. and Plentovich, E. B. and Chu, Julio Langley Research Center RTOP 505-68-70-08...
Book Synopsis A Review of Some Reynolds Number Effects Related to Bodies at High Angles of Attack by : Edward C. Polhamus (Jr.)
Download or read book A Review of Some Reynolds Number Effects Related to Bodies at High Angles of Attack written by Edward C. Polhamus (Jr.) and published by . This book was released on 1984 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Shock Wave-Boundary-Layer Interactions by : Holger Babinsky
Download or read book Shock Wave-Boundary-Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Book Synopsis A Review of Some Reynolds Number Effects Related to Bodies at High Angles of Attack by : Edward C. Polhamus
Download or read book A Review of Some Reynolds Number Effects Related to Bodies at High Angles of Attack written by Edward C. Polhamus and published by . This book was released on 1984 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low Reynolds Number by : Mustafa Serdar Genç
Download or read book Low Reynolds Number written by Mustafa Serdar Genç and published by BoD – Books on Demand. This book was released on 2012-04-04 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book reports the latest development and trends in the low Re number aerodynamics, transition from laminar to turbulence, unsteady low Reynolds number flows, experimental studies, numerical transition modelling, control of low Re number flows, and MAV wing aerodynamics. The contributors to each chapter are fluid mechanics and aerodynamics scientists and engineers with strong expertise in their respective fields. As a whole, the studies presented here reveal important new directions toward the realization of applications of MAV and wind turbine blades.
Book Synopsis Reynolds Number Effects at High Angles of Attack by : David F. Fisher
Download or read book Reynolds Number Effects at High Angles of Attack written by David F. Fisher and published by . This book was released on 1998 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lessons learned from comparision between ground-based tests and flight measurements for the high-angle-of-attack programs on the F-18 High Alpha Research Vehicle (HARV), the X-29 forward-swept wing aircraft, and the X-31 enhanced fighter maneuverability aircraft are presented. On all three vehicles, Reynolds number effects were evident on the forebodies at high angles of attack. The correlation between flight and wind tunnel forebody pressure distributions for the F-18 HARV were improved by using twin longitudinal grit strips on the forebody of the wind-tunnel model. Pressure distributions obtained on the X-29 wind-tunnel model at flight Reynolds numbers showed excellent correlation with the flight data up to [alpha]=50 deg. Above [alpha]=50 deg. the pressure distributions for both flight and wind tunnel became asymmetric and showed poorer agreement, possibly because of the different surface finish of the model and aircraft. The detrimental effect of a very sharp nose apex was demonstrated on the X-31 aircraft. Grit strips on the forebody of the X-31 reduced the randomness but increased the magnitude of the asymmetry. Nose strakes were required to reduce the forebody yawing moment asymmetries and the grit strips on the flight test noseboom improved the aircraft.
