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Monday, July 27, 2020 | History

3 edition of Comparison of computational and experimental results for a supercritical airfoil found in the catalog.

Comparison of computational and experimental results for a supercritical airfoil

Comparison of computational and experimental results for a supercritical airfoil

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  • 21 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, VA .
Written in English

    Subjects:
  • Mach number.,
  • Navier-Stokes equation.,
  • Supercritical airfoils.,
  • Transonic flow.,
  • Transonic wind tunnels.,
  • Wind tunnel models.

  • Edition Notes

    StatementMelissa B. Rivers and Richard A. Wahls.
    SeriesNASA technical memorandum -- 4601.
    ContributionsWahls, Richard A., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15410279M

    comparison. All results are corrected to a condition for boundary transition at the 8% chord station. As indicated by figure 5 the supercritical airfoil is structurally equivalent to a NACA 6-series airfoil of a somewhat greater thickness-to-chord ~atio. Therefore the data for the 11%-thick supercriticalFile Size: KB. ttjfoil(lo and a slotted supercritical 1 airfoil are shan for comparison. AJ.l results / I TWO-DIMENSIONAL AIRFOIL MOUNTED IN THE I I I FIGURE 3 1 1 i The integral supercritical airfoil experiences' a small drag increase starting at a Mach number of j about and an abrupt drag rise associated with!File Size: 2MB.

    A more recent comparison (ref. 17) of the trim drag measurements for a wide-body transonic model with conventional and supercritical wings at a Mach number of indicated that the trim drag for the supercritical wing configuration was not signif- icantly higher than that for the conventional wide- . An airfoil considered unconventional when tested in the early s by NASA at the Dryden Flight Research Center is now universally recognized by the aviation industry as a wing design that increases flying efficiency and helps lower fuel costs. Called the supercritical airfoil, the design has led to development of the supercritical wings (SCW)File Size: KB.

    A comparison of high lift systems derived from supercritical airfoils with high lift systems derived from conventional airfoils is presented. The high lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: (1) a single slotted flap, (2) a double slotted flap and a leading edge slat, and (3) a triple slotted flap and a leading edge slat.   Abstract. This paper presents a one-equation transition model for flows over airfoils and wings of transport aircraft. The transition model is based on a transport equation for an intermittency variable \(\gamma \).It is a simplification of the local correlation based \(\gamma \)-\(\textit{Re}_\theta \) transition model and is designated \(\gamma \) transition : Michael Fehrs.


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Comparison of computational and experimental results for a supercritical airfoil Download PDF EPUB FB2

A computational investigation was performed to study the flow over a supercritical airfoil model. Solutions were obtained for steady-state transonic flow conditions using a thin-layer Navier-Stokes flow solver. The results from this computational study were compared with time-averaged experimen-tal data obtained over a wide Reynolds number range.

ow evor a supercritical airfoil model. Solutions were btainedo for steady-state transonic ow conditions using a thin-laeyr Nvier-Stokaes ow solver. The results from this computational study were compared with time-aeragedv experimen-tal data obtained evor a wide Reynolds umber range at transonic speeds in the Langley Meter ran-T.

Solutions were obtained for steady-state transonic ow conditions using a thin-layer Navier-Stokes ow solver. The results from this computational study were compared with time-averaged experimental data obtained over a wide Reynolds number range at transonic speeds in the Langley Meter Transonic Cryogenic Tunnel.

A computational investigation was performed to study the ow over a supercritical airfoil model. Solutions were obtained for steady-state transonic ow conditions using a. Get this from a library. Comparison of computational and experimental results for a supercritical airfoil.

[Melissa B Rivers; Richard A Wahls; Langley Research Center.]. AIREX: Comparison of computational and experimental results for a supercritical airfoil A computational investigation was performed to study the flow over a supercritical airfoil model. Solutions were obtained for steady-state transonic flow conditions using a.

Comparison of computational and experimental studies for a joined-wing aircraft. Supercritical Airfoil Design for Future High-Altitude Long-Endurance Concepts. Comparison of Experimental Surface and Flow Field Measurements to Computational Results of the Juncture Flow Model (JFM).

CFL3D Papers CFL3D User’s Manual “Comparison of Computational and Experimental Results for a Supercritical Airfoil,” NASA TM, Robinson, B. and Yeh, D., “Toward Certification for CFD Codes for Aft End/Nozzle Configurations,” AIAA  Since the Mach Number you deal is over a super-critical aerofoil such as VA 2, you should be considering density based solver rather than pressure based solver in order to accommodate compressibility effects.

The experimental section characteristics of the S airfoil for a Reynolds number of × 10 6 and a Mach number of w ith transition free are compar ed with those of the S   That makes sense.

The laminar cd =the k-epsilon cd = The experimental is in between. Assumed Enhanced Wall Treatment would resolve this, wrong assumption. Why not compare calculated cd to experimental results with a 'trip wire'. Then you're sure that the experiment is fully turbulent, such that turbulence model is ok.

For example. Supercritical Airfoil Technology in Compressor Cascades: Comparison of Theoretical and Experimental Results H. Stephens Pratt & Whitney Aircraft Group, East Hartford, by: 4. Stephens, "Application of supercritical airfoil technology to compressor cascades: Comparison of theoretical and experimental results," A.I.A.A.

PaperR. Whitcomb and L. Clark, "An airfoil shape for efficient flight at supercritical Mach numbers," NASA TM X, Cited by: EXPERIMENTAL AND CFD ANALYSIS OF AIRFOIL AT LOW REYNOLDS NUMBER Chandrakant Sagat1*, Pravin Mane 1 and B S Gawali The determination of lift and drag of airfoil from wind tunnel measurements is discussed for incompressible flow.

Calculated the upper and lower surface pressure and velocity of an airfoil is essential for calculating the forces on Size: 1MB. Figure 10 shows the comparison of the numerical results with the experimental investigation of Jacquin et al.

() for two cases: before buffet onset at α = 3 • and in a buffet case at α = 3. Supercritical Airfoil and Wing Design Supercritical Airfoil and Wing Design Sobieczky, H; Seebass, A R The need for higher efficiency has forced the operating conditions of modern transport aircraft into the high subsonic speed regime.

For turbojet-powered aircraft, which enjoy a propulsive efficiency proportional to the flight Mach number, the overall aircraft efficiency. Flows over a typical supercritical airfoil XY are numerically investigated for different Reynolds numbers in this paper; the two-dimensional Navier-Stokes equations are solved with structure grids by utilizing the Spalart-Allmaras (S-A) turbulence model.

Computational results of RAE airfoil compare well with wind tunnel by: 5. The original article “Experimental and numerical study of the unsteady wake of a supercritical airfoil in a compressible flow.” featured in Vol. 11 of Journal of Aerospace Technology and Management show the use of hot wire sensors in measuring the wake of a supercritical airfoil in a compressible flow in a transonic wind tunnel.

supercritical airfoil. Numerical analysis has been carried using Ansys A grid independence study has been carried out and the results have been compared with experimental results.

The Mach number contour and velocity contour show the effect of shock wave on the flow over airfoil. Keywords— Supercritical Airfoil, Transonic FlowAuthor: Dhruva Koti, M Ayesha Khan. A supercritical airfoil is an airfoil designed, primarily, to delay the onset of wave drag in the transonic speed range.

Supercritical airfoils are characterized by their flattened upper surface. CFD Analysis of Supercritical Airfoil with Different Camber ndan1, a2, number. Here, a comparison is made between the supercritical airfoil and cambered airfoil.

The New Results on Numerical and Experimental Fluid Mechanics Volume .(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord.

Max camber % at % chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL Experimental investigations were carried out to study the wake profile of a supercritical airfoil at Mach numbers of and in a pitching motion.

Both static and dynamic tests were conducted in a Author: Behnaz Boroumand Beheshtii, Mahmoud Mani.