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Tuesday, July 28, 2020 | History

2 edition of comparison of the pitching and plunging response of an oscillating airfoil found in the catalog.

comparison of the pitching and plunging response of an oscillating airfoil

F. O. Carta

comparison of the pitching and plunging response of an oscillating airfoil

by F. O. Carta

  • 238 Want to read
  • 34 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamics

  • Edition Notes

    StatementF.O. Carta ; prepared for Langley Research Center under contract NAS1-14012
    SeriesNASA contractor report -- 3172
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
    The Physical Object
    Paginationiv, [154] p. :
    Number of Pages154
    ID Numbers
    Open LibraryOL14930359M

    a time response example for a flat plate oscillating at M® = with (1) a single pitching d.o.f.; (2) a single plunging d.o.f.; and (3) two d.o.f.s--plunging and pitching. A parallel set of results are also obtained based on subsonic aerodynamic theory for comparison. The agreement is good. dynamic stall of a SD pitching, plunging and combined motions airfoil and found that with increasing the reduced frequency and lag of the shed vortices, the direction of lift hysteresis is reversed. Baik. et al. () carried out an experimental comparison between SD and flat plate model undergoing pitching and plunging motion.

    Full text of "NASA Technical Reports Server (NTRS) The phenomenon of dynamic stall.[vortex shedding phenomenon on oscillating airfoils" See other formats NASA Tochnical Memorandum USAAVRADCOM TR 81 A 6 The Phenomenon o f Dynamic Stall W. J. McCroskey (HAS A-T«-d ) STALL (NASA) TdL I'HEHOrtLHON Ot p HC AOj/HB AOl Dlf HAMiC CSCL OlA . the airfoil does stall, the stall is more severe, and for oscillating airfoils, persists to lower angles of attack than the static stall. As the pitching airfoil passes through the static stall angle there is no discernible change in the viscous or inviscid flow about the airfoil. This is due to the finite time required for the stall events to.

      I’m modeling a 2D oscillating airfoil NACA in a pitching and heaving motion at a Re number of I’m running the simulation with different programs such as CFX, Fluent and StarCCM+. I got problem running my model with CFX. But I got good results with the other programs.   We numerically investigate an incompressible unsteady flow around a two-dimensional pitching airfoil (SD) at high reduced frequency (k ≥ 3) in the laminar regime. This study interrogates the effect of different unsteady parameters, namely, amplitude (A), reduced frequency (k), Reynolds number (Re), and asymmetry parameter (S) for.


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Comparison of the pitching and plunging response of an oscillating airfoil by F. O. Carta Download PDF EPUB FB2

Get this from a library. A comparison of the pitching and plunging response of an oscillating airfoil. [F O Carta; United States.

National Aeronautics and Space Administration. Scientific and Technical Information Branch.; Langley Research Center.]. A comparison of the pitching and plunging response of an oscillating airfoil (NASA contractor report) [Carta, F.

O] on *FREE* shipping on qualifying offers. A comparison of the pitching and plunging response of an oscillating airfoil (NASA contractor report)Author: F. O Carta. The flow-induced vibration (FIV) of an airfoil freely undergoing two-degrees-of-freedom (2-DOF) motions of plunging and pitching is numerically investigated as a function of the reduced velocity and pivot location in a two-dimensional free-stream : Z.

Wang, L. Du, J. Zhao, M. Thompson, X. Sun. An oscillating SC airfoil model was tested for its aerodynamic stability in a rigid body with a single degree of freedom pitch about its quarter chord, and also in a rigid body with single degree of freedom plunge.

The ability of pitching data to model plunging motions was : F. Carta. A series of experiments were conducted on an oscillating airfoil in subsonic flow. The model was oscillated in two types of motions, pitch and plunge, at different velocities, and reduced frequencies.

In addition, steady data were acquired and examined to furnish a baseline for analysis and by: 1. Periodic plunging and pitching was done manually by an appropriate plunge or pitch mechanism from outside the tunnel, and the airfoil profile was observed in side view.

[6] F.O., Carta, A comparison of the pitching and plunging response of an oscillating airfoil, NASA Report (). [7] C., Tyler, Joseph, and J. Gordon, Leishman, Analysis of pitch and plunge effects on unsteady airfoil behavior, Presented at the 47th Annual Forum.

For an airfoil undergoing both pitching motion and plunging motion, the boundary condition is given by (2) w a t = U ∞ α + x − a c / 2 α ̇ − h ̇ where U ∞ is the free-stream velocity, α is the angle of attack, h is the vertical displacement and a is the coordinate of pitching.

a) Pitching system b) Plunging system Fig. Pitching and plunging oscillation systems 3 Results and Discussion An extensive experimental investigation was conducted on an oscillating airfoil in two different modes, pitching and plunging, over a range of reduced frequencies, k= and various oscillation amplitudes.

The airfoil. Carta [4] and Ericsson [5] had conducted an experiment on comparatively studying the effects of pitching and plunging motions of an oscillating airfoil in and Their experimental data show that pitching and plunging motions have similar effects on the aerodynamic characteristics of the airfoil for low angle of attack (about 2 degrees).

Measurements of the unsteady flow structure and force time history of pitching and plunging SD and flat plate airfoils at low Reynolds numbers are presented. The airfoils were pitched and plunged in the effective angle of attack range of °–° (shallow-stall kinematics) and −6° to 22° (deep-stall kinematics).

The shallow-stall kinematics results for the SD airfoil show. A Comparison of the Pitching and Plunging Response of an Oscillating Airfoil F.

Carta United Technologies Research Center East Hartford, Connecticut Prepared for Langley Research Center under Contract NAS N/LS/X National Aeronautics and SpaceAdministration Scientific and Technical Information Branch We present a mapping of power-extraction efficiency for a single oscillating airfoil in the frequency and pitching-amplitude domain: 0.

ow over a sinusoidally oscillating NACA airfoil. Free-stream Mach number and were used in their compressible Reynolds averaged Navier-Stokes ow solver. They found that the freestream Mach number has an important e ect on the force predicted for both pitching and plunging oscillations.

Carta, F.A.: A Comparison of the pitching and plunging response of an oscillating airfoil. M., Rasi Marzabadi, F.: Comparison of pitching and plunging effects on the surface pressure variation of a wind turbine blade section.

Journal of Wind Energy, 12(3), – () CrossRef Google Scholar. C-language environment coupled with the Fluent-Macros. Forced motion of an airfoil can be of three types; plunging, pitching and apping (combination of plunging and pitching).

The schematic of these motion are shown in Fig. Pithing and plunging motion can be modeled as; Plunging: h(t) = h cos(2ˇft+ ˚ h) Pitching: (t) = sin(2ˇft) (3) where.

Modeling Transverse Gusts Using Pitching, Plunging, and Surging Airfoil Motions used oscillating wings upstream of a model to simulate a vortical gust. Kerstens et al.

[1] used Figure 1 shows a comparison of a generic gust and an exemplary three-degree-of-freedom(3-DOF)gust-replicatingmotionusedinthis.

Vortical patterns in the wake of an oscillating airfoil. Manoochehr M. Koochesfahani; Numerical investigations into the asymmetric effects on the aerodynamic response of a pitching airfoil.

Journal of Fluids and Structures, Vol. 39 Experimental Study of Governing Parameters in Pitching and Plunging Airfoil at Low Reynolds Number. II. Methods and Techniques.

Unsteady lift, pitching moment, and phase-averaged particle image velocimetry (PIV) measurements were conducted at R e = 20, for a NACA airfoil plunging with sinusoidal motion normal to the freestream flow direction; see Fig. different geometric angles of attack were tested (i.e., α = 0, 5, 9, 15, and 20 deg).).

These were selected to be. Experimental studies of the flow topology, leading-edge vortex dynamics and unsteady force produced by pitching and plunging flat-plate aerofoils in forward flight at Reynolds numbers in the range –20 are described. We consider the effects of varying frequency and plunge amplitude for the same effective angle-of-attack time history.

The Ames oscillating airfoil experiment was run in the 1 1 by 1 1 ft transonic wind tunnel. A m chord x m span wing with an NACA 64A airfoil section was installed in the test section between two splitter plates as shown in Fig.

1. The model was driven into a pitching or plunging motion by a servocontrolled hydraulic actuation.developed on an oscillating airfoil using multiple hot-film sensors, Experiments in Fluids, 25 (), [2] Carta, F. A., A Comparison of the Pitching and Plunging Response of an Oscillating Airfoil, NASA CR, [3] Ericson, L.E., and Reding, J.P., Unsteady Flow Concepts for.C.

Maresca, D. Favier, and J. Rebont, “ Unsteady aerodynamics of an airfoil at high angle of incidence performing various linear oscillations in a uniform stream,” J. Am. Helicopter Soc. 26, 40 (). Google Scholar; F. O. Carta, “A comparison of the pitching and plunging response of an oscillating airfoil,” NASA Contract.