Numerical investigation of subsonic flow over a typical missile forebody

Date

1996-01-01

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

139
views

0
downloads

© 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 for aerodynamic missile design purposes at low angles of attack.

URI

https://hdl.handle.net/11511/57578

DOI

https://doi.org/10.2514/6.1996-189

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

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....
Experimental design and statistical modeling methodology for wind tunnel aerodynamics of an agile missile to improve the simulation accuracy and performance Savas, Ozgun; Topbas, Eren; Unal, Kenan; Karaca, H. Deniz; Kutay, Ali Türker (2018-01-01) © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Wind tunnel testing is an essential procedure to investigate the aerodynamics forces and moments. In this paper, a methodology is presented to perform such test in an efficient way. Experimental design process is carried out before the testing in order to cover the flight regime as much as possible with the least possible number of tests. After the determination of the test matrix and conducting the wind-on tests, the ...
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...
Computational modelling and analysis of porous bleed holes at supersonic speeds Akar, Gökhan; Eyi, Sinan (2020-01-01) © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Shock Wave / Boundary Layer Interaction is an important issue that should be taken into account when studying inlet design. Bleed holes have traditionally been used to remove the lower momentum part of the boundary layer to avoid separation from adverse Shock Wave / Boundary Layer Interaction. In this study, modeling of porous bleed holes investigated in computational fluid dynamics on a flat plate with and without an ...
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...

Citation Formats

İ. H. Tuncer and M. F. Platzer, “Numerical investigation of subsonic flow over a typical missile forebody,” 1996, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/57578.