Study of transonic flow over swept wings final technical report

Cover of: Study of transonic flow over swept wings |

Published by NASA-Ames in [Palo Alto, Calif.?] .

Written in English

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Subjects:

  • Aerodynamics, Transonic,
  • Transonic planes -- Wings,
  • Aerofoils

Edition Notes

Book details

SeriesNASA-CR -- 173799, NASA contractor report -- 173799
ContributionsAmes Research Center, New York University
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL14928834M

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Get this from a library. Study of transonic flow over swept wings: final technical report. [Ames Research Center.; New York University.;]. The objective of the present study is to explain the evolution of the transonic buffet phenomenon from two-dimensional airfoils to three-dimensional swept wings by a global stability analysis.

Transonic Aerodynamics of Airfoils and Wings Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ). Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic File Size: 2MB.

A numerical method is presented for analyzing the transonic potential flow past a lifting, swept wing. A finite difference approximation to the full potential equation is solved in a coordinate. A Conceptual Study of a Transonic NLF Transport Aircraft with Forward Swept Wings Martin Kruse1, Tobias Wunderlich2 and Lars Heinrich.3 German Aerospace Center (DLR), Braunschweig, Germany, DLR’s concept for a natural laminar flow transonic transport File Size: 1MB.

Aerodynamics of Wings and Bodies Book Summary: This excellent, innovative reference offers a wealth of useful information and a solid background in the fundamentals of aerodynamics. Fluid mechanics, constant density inviscid flow, singular perturbation problems, viscosity, thin-wing and slender body theories, drag minimalization, and other essentials are addressed in a lively, literate manner.

A swept wing will delay the formation of the shock waves encountered in transonic flow to a higher Mach number. Additionally, it reduces the wave drag over all Mach numbers.

Figure 91 shows experimental data confirming this result as a wing is swept from no sweep to a high degree of sweep. Large-Eddy Simulation of Aeroelastic Flutter for the ONERA M6 Wing in the Transonic Flow.

In this case, we study the flow over an ONERA M6 wing. It was tested in a wind tunnel at transonic Mach numbers (, and ) and various angles of attack up to 6 degrees by Schmitt and Charpin [23]. The wings of airliners are typically swept in planform to reduce the transonic drag. For Mach numbers less thanthe frictional heating of the airframe is low enough that light weight aluminum is used for the structure.

Kruse, Martin und Wunderlich, Tobias und Heinrich, Lars () A Conceptual Study of a Transonic NLF Transport Aircraft with Forward Swept Wings. 30th AIAA Applied Aerodynamics Conference, - JunNew Orleans, USA. ISBN eISBN: Cited by: Bailey F.R., Ballhaus W.F.

() Relaxation methods for transonic flow about wing-cylinder combinations and lifting swept wings. In: Cabannes H., Temam R. (eds) Proceedings of the Third International Conference on Numerical Methods in Fluid Mechanics.

Lecture Notes in Physics, vol Springer, Berlin, Heidelberg. First Online 01 December Cited by: of the flow phenomena over a swept-wing fuselage combination has been made. The results of this study provide not only a contribution to the knowledge of the flow over swept wings in the transonic range but also an indication of the nature of sweptback wing-fuselage interference at transonic Mach numbers.

NACA RM L52D Guderley was perhaps the first to study 3-D effects on high AR wings in transonic flow [43]; he assumed small disturbances and M = 1, and found the 3-D corrections for a Asymptotic Structure of Transonic Flow straight and unyawed wing to belong to the order (AR) -6/: H.K.

Cheng. 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. An analysis of transonic flow about lifting wings with large aspect ratios is also presented.

The analysis is performed with the The angles attack which are considered are The modification to the Security Classif. (of this page) No. of Pages Price' 73 $ In this chapter we discuss the aerodynamics of swept wings in transonic flow.

To demonstrate the merits of swept-back wings, simple sweep theory is presented. 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 : Roelof Vos, Saeed Farokhi.

Introduction to Aircraft Design Introduction •!Aerodynamics is the study of the loads exerted by the flow of air over an aircraft (there are other applications but they are boring) •!There are six loads: –!Three forces: •!Lift •!Drag •!Sideforce –!Three moments: •!Pitch •!Roll •!Yaw x z y cg L D S Roll Yaw Pitch.

Fighter Wings: A more complicated story From Richard G. Bradley, “Practical Aerodynamic Problems-Military Aircraft” in Transonic Aerodynamics, AIAA Rather than cruise, fighter wings have to consider supersonics and low speed speed maneuvering as well as transonic cruise and maneuver.

Full text of "Numerical calculations of the transonic flow past a swept wing" See other formats N^y' Courant Institute of Mathematical Sciences ERDA Mathematics and Computing Laboratory Numerical Calculation of the Transonic Flow Past a Swept Wing Antony Jameson and D.

Caughey ERDA Research and Development Report Mathematics and Computing June New. We have already had something to say about the swept wing in Chapters 2 and 8. In this section we will look at the advantages to be gained from using swept wings in the transonic speed range, emphasising how conflicting design requirements are resolved and a suitable compromise solution is reached for a particular aircraft.

A numerical method is presented for analyzing the transonic potential flow past a lifting, swept wing. A finite-difference approximation to the full potential equation is solved in a coordinate system which is nearly conformally mapped from the physical space in planes parallel to the symmetry plane, and reduces the wing surface to a portion of.

spatial flow past wing segment J with a twist [9, 10]. In [11] 3D flow past unswept wing with elliptic nose was studied. In this paper, the study of 3D flow past swept and unswept wings with elliptic nose is presented.

WING DESCRIPTION We consider a three-dimensional flow past a smooth wing with symmetric airfoil of thickness h whoseAuthor: A. Ryabinin. He had simply observed the direction of air flow over a swept-wing design and was trying to design a fuselage that would follow the contours of that flow.

Whitcomb's area rule was also, in retrospect, said to be implicit in a doctoral thesis on supersonic flow by Wallace D. Hayes, published in A Study of the Effect of Leading-Edge Modifications on the Flow over a 5o-deg Sweptback Wing at Transonic Speeds C.

BE~RY and J. TOWNSEND, AERODYNAMICS DIVISION, N.P.L. By E. ROGERS, OF THE Reports and Memoranda No. o* May, z96o Size: 6MB. On the Inception Lengths of Swept Shock-Wave/ Turbulent Boundary-Layer Interactions.- Experimental Study of the Boundary-Layer Separation Conditions through a Shock-Wave on Airfoil and Swept Wing.- A Model of the Flow over Swept Wings with Shock Induced Separation.- Separation ahead of Blunt Fins in Supersonic Turbulent Boundary-Layers Start studying ASA Chapter 3 - High Speed Flight.

Learn vocabulary, terms, and more with flashcards, games, and other study tools. Search. What is the highest speed possible without supersonic flow over the wing. Swept wings causes a significant. Method to Analyze Transonic Flow Over Oscillating Wings.

Butler, rill, J. ian, and Boeing Commercial Airplane Company Seattle, Washington. * Analyze wings with swept leading and trailing edges * Take advantage of autosymmetry in the case of a wing at zero angle of attack and with a. Wong, WS and Qin, N and Sellars, N and Holden, H and Babinsky, H () A combined experimental and numerical study of flow structures over three-dimensional shock control bumps.

Aerospace Science and Technology, pp. ISSN Jones, AR and Bakhtian, NA and Babinsky, H () Low reynolds number aerodynamics of leading-edge. Other topics covered are on flow transition to analyse NLF airfoils, bypass transition, streamwise and cross-flow instability over swept wings, viscous transonic flow over airfoils, low Reynolds number aerodynamics, high lift devices and flow control.

A theory for base pressures in transonic and supersonic flow / (Urbana, Ill.: Mechanical Engineering Dept., Univ. of Illinois, May ), by Helmut Hans Korst, M. Childs, R. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA In transonic flow, swept wings delay the formation of shock waves to a far much higher Mach number. This reduces the wave drag over all these mach numbers. Shockwaves depend on the span component that is to the trailing edge, and this is a far much smaller.

A delta wing is a wing shaped in the form of a triangle. It is named for its similarity in shape to the Greek uppercase letter delta (Δ).

Although long studied, it did not find significant applications until the jet age, when it proved suitable for high-speed subsonic and supersonic the other end of the speed scale, the Rogallo flexible wing proved a practical design for the hang. Set the flow domain body to fluid. The geometry is given in STEP format: Download Geometry.

This geometry is a scaled down version of the experimental Onera M6 geometry to more closely match with the results from NASA. If you would like to know more about how the geometry was created you can go to see how here. Geometry Part 1: Importing the.

The study revealed the existence of narrow bands of the Mach number, angle of attack, and spoiler deflection angle, in which the flow was extremely sensitive to small perturbations. Simulations of 3D flow past a swept wing confirmed the flow sensitivity to small perturbations of boundary conditions.

Firstly, one is concerned with the lifting part of the flow. According to the transonic equivalence law, Ref. 54, linearized theory is capable of describing the steady lifting flow for wings of low aspect ratio, and wind tunnel experiments do, indeed, confirm fairly well the predictions of the theory at least for wings with swept leading : Dover Publications.

Mach tuck occurred at speeds above Mach ; the air flow over the wing center section became transonic, causing a loss of lift. The resultant change in downwash at the tail caused a nose-down pitching moment and the dive to steepen (Mach tuck).

The aircraft was very stable in this condition making recovery from the dive very difficult. Transonic effect around airfoils visualized in flowing soap films Sunyi Wang, The Applied Math Lab, Courant Institute, New York University and NYU. View Notes - ConfigAeroTransonics from AOE at Virginia Tech.

W.H. Mason 7. Transonic Aerodynamics of Airfoils and Wings Introduction Transonic flow occurs when there is mixed sub- and. @article{osti_, title = {An interactive three-dimensional laminar and turbulent boundary-layer method for compressible flow over swept wings}, author = {Woodson, S.H.}, abstractNote = {A three-dimensional laminar and turbulent boundary-layer method is developed for compressible flow over swept wings.

The governing equations and curvature terms are derived in detail for a nonorthogonal. CALCULATION OF INVISCID TRANSONIC FLOW OVER A COMPLETE AIRCRAFT ∗ A. Jameson, T.J. Baker and N.P. Weatherill Department of Mechanical Engineering Princeton University Princeton, New Jersey U.S.A.

We present preliminary results for the calculation of inviscid transonic ow over a complete aircraft.Firstly, one is concerned with the lifting part of the flow.

According to the transonic equivalence law, Ref. 54, linearized theory is capable of describing the steady lifting flow for wings of low aspect ratio, and wind tunnel experiments do, indeed, confirm fairly well the predictions of the theory at least for wings with swept leading : $Search the history of over billion web pages on the Internet.

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