A multi-point optimization for transonic airfoil design

Date

1992-01-01

Author

Hager, J.O.
Eyi, Sinan
Lee, K.D.

Metadata

Show full item record

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

Item Usage Stats

123
views

0
downloads

© 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.A two-point, aerodynamic design method is presented which improves the aerodynamic performance of transonic airfoils over a range of the flight envelope. It couples an Euler flow solver and a numerical optimization tool. The major limitation of single-point design is the poor off-design performance. Two-point design is used to extend the optimized performance range over more of the desired flight envelope. The method is applied to several transonic flow design points, and the results are compared to single-point design results. The secondary design-points are chosen by varying the angle-of-attack, and the angle-of-attack and Mach-number. The two-point designs perform better than the single-point design over the design-point range.

URI

https://hdl.handle.net/11511/69382

DOI

https://doi.org/10.2514/6.1992-4681

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

A computational study of flow separation characteristics and wake profiles behind a flapping airfoil Tuncer, İsmail Hakkı (1999-01-01) © 1999 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Unsteady, viscous flowfields over a NACA0012 airfoil oscillated in plunge and/or pitch at various reduced frequency, amplitude and phase shift are computed. Vortical wake formations, boundary layer flows at the leading edge, the formation of leading edge vortices and their downstream convection are presented in terms of unsteady particle traces. Flow separation characteristics and thrust producing wake profiles are identifie...
A Modification to Adaptive Control with Time-varying Learning Rate for Improved Transient Performance Yayla, Metehan; Kutay, Ali Türker (2022-01-01) © 2022, American Institute of Aeronautics and Astronautics Inc. All rights reserved.In this study, we propose a new adaptive weight update law using frequency-limited estimation of the matched uncertainty. Many adaptive parameter adjustment laws try to suppress the effects of uncertainties using forcing terms consisting of tracking error only. However, it has been widely studied that including the uncertainty estimation error in the adaptation law enhances the transient performance significantly. In our pro...
A modeling and simulation tool for safe store separation envelope generation using monte carlo simulations Unal, Kenan; Baran, Özgür Uğraş (2018-01-01) © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.When an air released store is developed or undergoes substantial updates, integration to aircraft is realized through a certification process. One of the most important steps of the certification process is to determine safe separation envelope. For this process there are several approaches: full scale flight tests, computational fluid dynamics (CFD) simulation techniques and wind tunnel captive trajectory tests. Separ...
Analysis of unsteady airfoil interference effects using a zonal Navier-Stokes solver Tuncer, İsmail Hakkı (null; 1995-01-01) © 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 combinat...
A viscous-inviscid interaction method for 2-D unsteady, compressible flows Tuncer, İsmail Hakkı; Platzer, Max F. (1993-01-01) © 1993 American Institute of Aeronautics and Aerodynamics, Inc. All rights reserved.A Navier-Stokes/potential flow interactive solution method suitable for the solution of steady-state and unsteady flowfields around airfoils has been developed. The Navier-Stokes equations are solved in the close proximity of an airfoil and in its wake. The inviscid flowfield surrounding the viscous flow regions is assumed to be irrotational and isentropic. In the inviscid flow region, the potential flow equations, which are...

Citation Formats

J. O. Hager, S. Eyi, and K. D. Lee, “A multi-point optimization for transonic airfoil design,” 1992, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69382.