A computational study on the dynamic stall of a flapping airfoil

Date

1998-01-01

Author

Tuncer, İsmail Hakkı
Platzer, Max F.

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

102
views

0
downloads

© 1998, American Institute of Aeronautics and Astronautics, Inc.The dynamic stall boundaries of a NACA 0012 airfoil oscillating in either the pure plunge mode or in the combined pitch and plunge mode is computed using a thin-layer Navier-Stokes solver. Unsteady flowfields are computed at the free-stream Mach number of 0.3, the Reynolds number of 1 • 106, and the Baldwin-Lomax turbulence model is employed. It is found that the pure plunge oscillation leads to dynamic stall as soon as the non-dimensional plunge velocity exceeds the approximate value of 0.35. In addition, the power extraction capability of the airfoil operating in the wingmill mode is studied by computing the dynamic stall boundary for a combined pitch and plunge motion at the reduced frequency values of 0.1, 0.25 and 0.5.

URI

https://hdl.handle.net/11511/56191

DOI

https://doi.org/10.2514/6.1998-2519

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

A computational study of flow entrainment over a stationary/flapping airfoil combination in tandem Tuncer, İsmail Hakkı; Platzer, Max F. (1998-01-01) © 1997, American Institute of Aeronautics and Astronautics, Inc.Unsteady flowfields over a stationary/flapping airfoil combination in tandem are computed using a Reynolds averaged Navier-Stokes solver. The stationary leading airfoil has an experimental profile which promotes flow separation at its trailing edge. The effect of the flapping airfoil on the leading airfoil and the flow reattachment at the trailing edge are investigated by varying the amplitude and frequency of the flapping motion. A single defo...
A Computational analysis on rotor-propeller arm interaction in hovering flight Yener, Serkan.; Perçin, Mustafa; Department of Aerospace Engineering (2019) This study presents a computational analysis on the interaction between rotor and different rotor frame-arm geometries in hovering flight. The influence of the frame arm on the aerodynamic performance of the rotor is assessed by using commercially available computational fluid dynamics (CFD) solver software ANSYS Inc. Fluent 17. Numerical results are validated for hovering and forward vertical climb flight conditions with thrust and torque measurements conducted on a 16x4 carbon fiber propeller. The thrust ...
A computational study of subsonic flows over a medium range cargo aircraft Uygun, Murat; Tuncer, İsmail Hakkı (2003-01-01) Inviscid and viscous flows over CN-235 cargo aircraft are computed at cruise conditions and at angles of attack ranging from 0 deg to 5 deg using CFD-FASTRAN Navier-Stokes solver. Computations are performed on a Pentium III based PC with a 1Gb memory. Grid sensitivity and verification studies are performed on clean-wing and wing-nacelle configurations to determine the effects of the surface grid density, the size of the computational domain and available numerical schemes. Inviscid and viscous flows with av...
Numerical and Experimental Analysis of Purely Pitching and Purely Plunging Airfoils in Hover Hızlı, Hasan; Kurtuluş, Dilek Funda (2012-07-06) Numerical and experimental study of two-dimensional purely pitching and purely plunging SD7003 and NACA0012 airfoil sections in hover mode is presented. Main objectives of the study are to provide a better understanding of the aerodynamic phenomena and the vortex topology of flapping wings for application to micro air vehicle (MAV) designs and to compare numerical and experimental results for observing the performance of the experimental setup for future applications. The commercial CFD package program Flue...
A comparative study on tightly coupled visual aided inertial navigation systems for unmanned aerial vehicles İnce, Talha; Saranlı, Afşar; Department of Electrical and Electronics Engineering (2018) An Inertial Navigation System (INS) is a combination of hardware (accelerometers and gyroscopes) and algorithms to calculate the position, orientation and velocity of a mobile platform. Because of the need to integrate the measurements over time, INS is subjected to cumulative error characteristics, hence cannot provide an accurate navigation solution over long durations. Global Positioning System (GPS) is often used for long time-long distance problems aiding INS. GPS relies on external signals received fr...

Citation Formats

İ. H. Tuncer and M. F. Platzer, “A computational study on the dynamic stall of a flapping airfoil,” 1998, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/56191.