Results 201 to 210 of about 15,113 (249)
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Optimization of the Porosity Distribution in Transonic Wind Tunnel
Volume 2: Fora, 2012During past years, to improve the quality of wind tunnel data in transonic configurations, researchers first designed new wind tunnel geometries (as porous and/or slotted wind tunnels), then developed more accurate correction laws giving acceptable results in certain conditions but absolutely not sufficient to satisfy the increasing aeronautical ...
Antonello Marino, Aldo Bonfiglioli
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1990
Abstract From the preceding chapters it has become obvious that a purely theoretical treatment of most transonic problems is not possible, at least today. For a reasonable assurance of the accuracy of the theoretical results, comparisons with test data are still a necessity. Data for this purpose may be obtained from free-flight tests or
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Abstract From the preceding chapters it has become obvious that a purely theoretical treatment of most transonic problems is not possible, at least today. For a reasonable assurance of the accuracy of the theoretical results, comparisons with test data are still a necessity. Data for this purpose may be obtained from free-flight tests or
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Transonic wind tunnel wall interference minimization
Journal of Aircraft, 1984Obtaining accurate predictions of aircraft aerodynamic coefficients from wind tunnel tests is a difficult task Wind tunnel users have struggled with the effects of wall interference, model support interference, subscale Reynolds number, etc for almost the entire history of powered flight Since wall interference is one of the principal problems this ...
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Computational Optimization and Wind Tunnel Test of Transonic Wing Designs
Journal of Aircraft, 1979A practical procedure for the optimum design of transonic wings is demonstrated. The procedure uses an optimization program based on the method of feasible directions coupled with an aerodynamic analysis program which solves the three-dimensional potential equation for subsonic through transonic flow. Two new wings for the A-7 aircraft were designed by
H. HANEY, R. JOHNSON, R. HICKS
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Evaluation of Flow Quality in Two NASA Transonic Wind Tunnels
Journal of Aircraft, 1979Tests have been conducted in the Langley Research Center 8-foot Transonic Pressure Tunnel and the Ames Research Center 12-foot pressure wind tunnel in order to measure characteristic disturbance levels and energy spectra in their respective settling chambers, test sections, and diffusers and to determine the sources of these disturbances.
F. OWEN, P. STAINBACK, W. HARVEY
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Transonic wind tunnel for investigation of turbomachinery blades
1972The design of a two-stream wind tunnel was undertaken to allow the simulation and study of certain features of the flow field around the blades of high-speed axial-flow turbomachineries. The mixing of the two parallel streams with designed Mach numbers respectively equal to 1.4 and 0.7 will simulate the transonic Mach number distribution generally ...
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Cryogenic transonic wind tunnels and the condensation of nitrogen
Experiments in Fluids, 1991A brief tutorial on the need for Reynolds number similarity and the advent of cryogenic transonic wind tunnels is presented. Experimental results of nitrogen condensation in nozzles are collected and related to the flow in the wind tunnels. New theoretical approaches to a solution of the condensation problem in the supersaturated state are proposed.
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Wind tunnel investigation of transonic limit cycle flutter
39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit, 1998Transonic wind tunnel tests were conducted for a high aspect ratio aeroelastic wing model in order to clarify bifurcation characteristics of the limit cycle oscillation (LCO). During the tests, a large amplitude LCO (LC-H) and a small amplitude LCO (LC-1) appeared in a way as saddle-node-, subcritical Hopfand supercritical Hopf- biftircation.
Hiroshi Matsushita +2 more
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Computation of power requirements for subsonic and transonic wind tunnels
15th Applied Aerodynamics Conference, 1997A computational method has been developed which allows the prediction of circuit losses and power requirements of subsonic and transonic wind tunnels with a minimum of empirical data input. The method is an extension of the incompressible pressure loss calculation scheme based on the usual onedimensional approach.
T. Wolf, T. Wolf
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The Assessment of Results obtained in Transonic Wind Tunnels
The Journal of the Royal Aeronautical Society, 1958The development of wind tunnel sections with partly open walls has made it possible to operate at continuously variable speeds through the transonic range up to low supersonic speeds. Some consideration must be given, however, to the general reliability of the measurements in these tunnels of the aerodynamic characteristics of air vehicles or missiles.
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