Analysis of unsteady airfoil interference effects using a zonal Navier-Stokes solver

Date

1995-01-01

Author

Tuncer, İsmail Hakkı

Metadata

Show full item record

Item Usage Stats

37
views

0
downloads

© 1995, by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Unsteady aerodynamic interference effects and thrust generation on a flapping/stationary airfoil combination in tandem are studied parametrically. A zonal Navier-Stokes solver is employed to compute the unsteady flowfield. The computational domain is discretized with overlapping uniform grids generated around each airfoil. The thrust generation and the propulsive efficiency of the flapping/stationary airfoil combination is found to be a strong function of reduced frequency and the amplitude of the flapping motion of the leading airfoil. The maximum propulsive efficiency of a NACA0012 airfoil combination has been computed to be 70% at a reduced frequency of 0.75 and a flapping amplitude of 0.20 chord lengths when the airfoils are separated by about two chord lengths.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=0040737455&origin=inward
https://hdl.handle.net/11511/79748

DOI

https://doi.org/10.2514/6.1995-307

Conference Name

33rd Aerospace Sciences Meeting and Exhibit, 1995

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Analysis of hypersonic flow using three dimensional Navier-Stokes equations Özgün, Muharrem; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The purpose of this study is to develop an accurate and efficient CFD code that can be used in hypersonic flows. The flow analysis is based on the three dimensional Navier-Stokes equations. These equations are solved by using Newton’s method. The analytical method is used to calculate the Jacobian matrix. Flow parameters and convective heat transfer are analyzed on Apollo AS-202 Command Module. Especially, temperature...
Analysis and design optimization of three dimensional nozzles Yildizlar, B.; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The aim of this study is to develop analysis and design optimization method for three dimensional nozzles. For analysis, three dimensional Euler equations are solved using both Newton and Newton-GMRES methods and their performances are compared. The Jacobian matrix needed for Newton method is evaluated analytically. Newton-GMRES method is a matrix free solution technique hence it does not require the Jacobian matrix e...
Analysis and adjoint design optimization of hypersonic blunt bodies Piskin, Tugba; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The main purpose of this study is to analyze hypersonic flow field around the blunt bodies and to design of that bodies in order to obtain minimum pressure drag. Modeling of non-equilibrium must be done properly. In this study, non-equilibriums of thermal and chemical modes are considered. Translational and rotational energy modes are assumed that energy exchange between these modes is so fast. Vibrational and electro...
Numerical investigation of subsonic flow over a typical missile forebody Tuncer, İsmail Hakkı; Platzer, Max F. (1996-01-01) © 1996, American Institute of Aeronautics and Astronautics, Inc. All Rights Reserved.The NASA-Ames developed Navier-Stokes solver OVERFLOW and the panel code PMARC are applied to the computation of the flow over a typical missile forebody. The flowfields at low angles of attack from 0° to 14° are investigated. The surface pressures along the missile forebody predicted by OVERFLOW and PMARC agree well up to 10°. This favorable agreement suggests that the panel codes may be a computationally efficient tool fo...
Efficiency improvement in sensitivity evaluation in aerodynamic shape optimization Eyi, Sinan (1996-01-01) © 1996 by the American Institute of Aeronautics and Astronautics, Inc. All rights resewed.The paper presents two methods that improve the accuracy and reduce the computational cost in evaluating finite-difference sensitivities for aerodynamic shape optimization. The first method is a modified finite-difference approach that improves the accuracy of sensitivities at a reduced cost using an improved iteration strategy. The second method finds the optimum perturbation size based on an asymptotic error formula....

Citation Formats

İ. H. Tuncer, “Analysis of unsteady airfoil interference effects using a zonal Navier-Stokes solver,” 1995, Accessed: 00, 2021. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=0040737455&origin=inward.