AERODYNAMIC DESIGN VIA OPTIMIZATION

Date

1992-11-01

Author

LEE, KD
Eyi, Sinan

Metadata

Show full item record

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

Item Usage Stats

79
views

0
downloads

An aerodynamic design optimization method is presented that generates an airfoil, producing a specified surface pressure distribution at a transonic speed. The design procedure is based on the coupled Euler and boundary-layer technology to include the rotational viscous physics which characterizes transonic flows. A least-square optimization technique is used to minimize pressure discrepancies between the target and designed airfoils. The method is demonstrated with several examples at transonic speeds. The design optimization process converges quickly, that makes the method attractive for practical engineering applications.

Subject Keywords

Aerospace Engineering

URI

https://hdl.handle.net/11511/35154

Journal

JOURNAL OF AIRCRAFT

DOI

https://doi.org/10.2514/3.46278

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Aerodynamic design and optimization of horizontal axis wind turbines by using bem theory and genetic algorithm Ceyhan, Özlem; Tuncer, İsmail Hakkı; Department of Aerospace Engineering (2008) An aerodynamic design and optimization tool for wind turbines is developed by using both Blade Element Momentum (BEM) Theory and Genetic Algorithm. Turbine blades are optimized for the maximum power production for a given wind speed, a rotational speed, a number of blades and a blade radius. The optimization variables are taken as a fixed number of sectional airfoil profiles, chord lengths, and twist angles along the blade span. The airfoil profiles and their aerodynamic data are taken from an airfoil datab...
2-POINT TRANSONIC AIRFOIL DESIGN USING OPTIMIZATION FOR IMPROVED OFF-DESIGN PERFORMANCE HAGER, JO; Eyi, Sinan; LEE, KD (American Institute of Aeronautics and Astronautics (AIAA), 1994-09-01) A two-point, aerodynamic design method is presented that 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 sing...
High-lift design optimization using Navier-Stokes equations Eyi, Sinan; Rogers, SE; Kwak, D (American Institute of Aeronautics and Astronautics (AIAA), 1996-05-01) This article presents a design optimization method for maximizing lift without increasing the drag of multielement airfoils at takeoff and landing configurations. It uses an incompressible Navier-Stokes dow solver (INS2D), a chimera overlaid grid system (PEGSUS), and a constrained numerical optimizer (DOT). Aerodynamic sensitivity derivatives are obtained using finite differencing. The method is first validated with single-clement airfoil designs and then applied to three-element airfoil designs. Reliable d...
Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing Gulsacan, Burak; Sencan, Gizem; Yavuz, Mehmet Metin (American Institute of Aeronautics and Astronautics (AIAA), 2018-12-01) The effect of thickness-to-chord (t/C) ratio on flow structure of a delta wing with sweep angle of 35 deg is characterized in a low-speed wind tunnel using laser-illuminated smoke visualization, particle image velocimetry, and surface pressure measurements. Four different t/C ratios varying from 4.75 to 19% are tested at angles of attack, 4, 6, 8, and 10 deg, for Reynolds numbers Re =1 x 10(4) and 3.5 x 10(4). The results indicate that the effect of thicknessto-chord ratio on flow structure is quite substan...
Near-surface topology of unmanned combat air vehicle planform: Reynolds number dependence Elkhoury, M; Yavuz, Mehmet Metin; Rockwell, D (American Institute of Aeronautics and Astronautics (AIAA), 2005-09-01) The Reynolds number dependence of the near-surface flow structure and topology on a representative unmanned combat air vehicle planform is characterized using a technique of high-image-density particle image velocimetry, to complement classical dye visualization. Patterns of streamline topology, including bifurcation lines, as well as contours of streamwise and transverse velocity, surface-normal vorticity, and Reynolds stress correlation, all immediately adjacent to the surface of the planform, provide qua...

Citation Formats

K. LEE and S. Eyi, “AERODYNAMIC DESIGN VIA OPTIMIZATION,” JOURNAL OF AIRCRAFT, pp. 1012–1019, 1992, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/35154.