3 edition of An investigation of scale effects on the transonic flow over swept wings. found in the catalog.
An investigation of scale effects on the transonic flow over swept wings.
D J. Weeks
|Series||Reports and memoranda -- no.3842.|
|Contributions||Great Britain. Ministry of Defence. Procurement Executive.|
|The Physical Object|
|Pagination||39, (87)p. :|
|Number of Pages||87|
CFD Investigations of a Transonic Swept-Wing Laminar Flow Control Flight Experiment. (May ) Tyler Patrick Neale, B.S., Louisiana Tech University Chair of Advisory Committee: Dr. Helen Reed Laminar flow control has been studied for several decades in an . Thus the flow elements sketched in Fig. , which are central to the problem of wings in transonic flow, are as yet beyond the available theoretical means and recourse must be taken to experiment: the tool at our disposal for estimating the flow over full-scale aircraft is the windtunnel (see e. .
This image was generated on a very fine mesh of over one million cells. The second image was generated on a less fine mesh (clear because of the coarseness seen in the color of the vorticity) but this one also shows the Q Criterion at a level of so we can see the vorticity present on the wing. Experimental study of transonic buffet phenomenon on a 3D swept wing Physics of Fluids 28 receptivity, and sensitivity analyses of buffeting transonic flow over a profile “The interaction between local effects at the shock and rear separation—A source of significant scale effects in wind-tunnel tests on airfoils and wings,” AGARD Cited by:
Three-Dimensional Transonic Flow Over Wing-Body Combinations, including Viscous Effects,” AFFDL-TR, February Extend Korn to swept wings using simple sweep theory so that we ﬁnd M crit: C D M = Hybrid Wing Vortex Flow Effects Compared to Attached Flow Concepts E Lift Coefficient Attachedflow concept Vortex flow concept. Most notable is the use of swept wings, but another common form is a wasp-waist fuselage as a side effect of the Whitcomb area rule. Severe instability can occur at transonic speeds. Shock waves can cause large-scale separation downstream, increasing drag and adding asymmetry and unsteadiness to the flow around the vehicle.
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Transonic flows over swept wings. In the part of the investigation described here a study has been made of the effects of changes in Reynolds number and transition location on the transonic flow over the upper surface of a wing suitable for a variable-sweep strike-fighter Size: 7MB.
AN INVESTIGATION OF SCALE EFFECTS ON THE TRANSONIC FLOW OVER SWEPT WINGS PART I: MEASUREMENTS ON A MODEL OF A TRANSPORT-AIRCRAFT CONFIGURATION By D. Jo Weeks Aerodynamics Department, RAE, Farnborough, Hants REPORTS AND MEMORANDA No" PART l November SUMMARY. An Introduction to the Flow about Plane Swept-back Wings at Transonic Speeds* - Volume 64 Issue - E.
Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic Size: 2MB. 3D transonic flow over swept and unswept wings with an J airfoil at spanwise sections is studied numerically at negative and vanishing angles of attack.
Aerodynamic Parameters Analysis of Transonic Flow Past Unswept and Swept Wings Raad Shehab Ahmed* Received on:2 /4/ 6/ Accepted on: 3/3/ Abstract The transonic flow past unswept and swept wings has been studied.
For this purpose the transonic potential flow equation is solved for inviscid compressible flow. It is shown why a swept wing can experience local supersonic flow while still being in subcritical conditions, thereby postponing the onset of strong shock waves and drag divergence.
It is also shown how the wave drag coefficient of a swept wing can be estimated based on the wave drag coefficient of an unswept : Roelof Vos, Saeed Farokhi.
Numerical Calculation of the transonic flow past a swept wing numerical analysis of transonic potential flow past lifting, swept wing. for predicting transonic flows over wings and bodies. angle of sweep can be varied in flight, an investigation was made at transonic speeds by the MACA wing-flow method on a scale semispan model of a preliminary configuration.
1 30 Results of tests covering several phasea of investigations at low supersonic Mach nmibers have been reported in references 1 to 4. TheAuthor: Joseph J Kolnick, Robert M Kennedy. In effect, the flow in the mid-span region is more like that for a wing of low aspect ratio. Accordingly, the generation of lift will be considerably impaired in that region.
This effect is evident in the comparison of pressure coefficient distributions over straight and swept wings shown in Fig. The reduction in peak pressure over the. swept wing reduces the wave drag over all Mach numbers as a wing is swept from no sweep to a high degree of sweep.
Types of Wings and Transonic Flow There are a number of ways of delaying the increase in drag encountered when an aircraft travels at high speeds, i.e., the transonic wave drag rise, or of increasing the drag-divergence.
Summary. A new flow model is proposed for describing quasi two-dimensional flows with shock-induced separation on wings of modest sweep. Correlations of the main features of the flow model over a wide range of Reynolds number have been deduced from wind-tunnel tests on wings and by: 3.
Full text of "NASA Technical Reports Server (NTRS) The Effects of Sweepback on Longitudinal Characteristics of a 1/scale Semispan Model of the Bell X-5 Airplane as Determined from NACA Wing-flow Tests at Transonic Speeds" See other formats NACA RM L 3 SECURITY INFORMATION Copykd4 RM L52I23 NACA RESEARCH MEMORANDUM THE EFFECTS OF.
The wing in a transonic flow is forced to be deformed owing to the strong aerodynamic force. The deformation of the wing structure changes the flow field around the wing.
The change of the flow field affects the distribution of the aerodynamic force on the wing surface and drives the elastic motion of the wing. effect when flying at transonic speed. Disadvantages* * When a swept wing travels at high speed, the airflow airflow is moving along the wing instead of over it, a problem known as spanwise flow.
The lift from a wing is generated by the airflow over it from front to The spanwise flow on swept wings produces airflow that moves the File Size: 2MB.
Investigation into scale effects on the performance of sub boundary-layer vortex generators on civil aircraft high-lift devices, AIAA, 1st Flow Control Conference, St. Louis, Missouri, June Cited by: This paper investigates the effect of a swept airfoil design on the aerodynamic instabilities of transonic axial-flow compressors based on global stability analysis.
An approach aimed at predicting This paper investigates the effect of a swept airfoil design on the aerodynamic instabilities of transonic axial-flow compressors based on global stability by: 6. 3D transonic flow over swept and unswept wings with an J airfoil at spanwise sections is studied numerically at negative and vanishing angles of attack.
Solutions of the unsteady Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver on unstructured meshes.
The numerical simulation shows that adverse Mach numbers Cited by: 6. for swept tapered wings or near wing root for unswept untapered wing. At Mach number that corresponds to coalescence of supersonic regions the average lift is not equal to zero. Keywords: transonic flight, supersonic regions, lift oscillations, swept wing.
INTRODUCTION Numerical studies demonstrated that the transonic flow around an airfoil Author: A. Ryabinin. laminar flow technology for a typical jet airliner, a reduction of total drag by 10%% is predicted for an extent of laminar flow over 50% of the wing surface4.
In fact controlling the stability of the boundary layer of a swept wing at high chord Reynolds numbers is a difficult task.
Unlike for unswept wings, where transition to turbulence isFile Size: 1MB. Transonic effect around airfoils visualized in flowing soap films Sunyi Wang, The Applied Math Lab, Courant Institute, New York University and NYU.
Investigation of large scale shock movement in transonic flow International Journal of Heat and Fluid Flow, Vol. 31, No. 4 Advanced Experimental and Numerical Investigations of an Aircraft Powerplant ConfigurationCited by: Test conducted at NASA Langley Research Center's Full Scale Tunnel using a 49 degree swept wing model with trailing edge and leading edge blowing applied.
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