Wave drag optimization of high speed aircraft

Download

index.pdf

Date

2015

Author

Çıtak, Can

Metadata

Show full item record

Item Usage Stats

248
views

125
downloads

Supersonic flight has been the subject of the last half century. Both military and civil projects have been running on to design aircraft that will fly faster than the speed of sound. Developing technology and increasing experience leads to faster, more fuel – efficient, longer ranged aircraft designs. These vehicles have the advantage of shortening travelling times in the civilian role and performing missions with greater success in the military role. Aerodynamic design is the main argument of high speed aircraft improvement. Having less supersonic drag force, which is greater than double of the subsonic case for conventional aircraft, is the ultimate goal of the aircraft designers for supersonic design. Optimizing aerodynamic characteristics of supersonic air vehicles by reducing wave drag is the main purpose of this thesis. A computational tool using computational fluid dynamics, analytical and numerical methods is developed in order to meet this goal. Firstly, wave drag coefficient solver algorithm is generated on a MATLAB interface. Then, the solver is validated with different geometries by using computational fluid dynamics simulations at various speeds. ANSYS Fluent is used for flow simulations. Next, gradient-based constrained optimization algorithm is employed to minimize the wave drag coefficient of a supersonic aircraft design. In addition, test cases are selected to observe the success of the wave drag coefficient optimization program for different situations. Finally, fighter aircraft geometry is optimized with respect to engine size constraints.

Subject Keywords

Drag (Aerodynamics)., Supersonic planes., Aerodynamics, Supersonic., Computational fluid dynamics.

URI

http://etd.lib.metu.edu.tr/upload/12618475/index.pdf
https://hdl.handle.net/11511/24410

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Aerodynamic parameter estimation of a supersonic missile with rapid speed variation by using kalman filtering Bayoğlu, Tuğba; Kutay, Ali Türker; Department of Aerospace Engineering (2016) This study aims to develop an approach for the aerodynamic parameter estimation problem for supersonic air to air missile with rapid speed variation, as well as large variation of aerodynamic parameters with respect to Mach number. In literature, most of the estimation techniques require that estimator is time independent. Therefore, most of the aerodynamic parameter estimation methods are applied for air vehicles which have control over their speed or which can operate at relatively constant Mach number so...
Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator Mehmet Ozan, Nalcı; Kayran, Altan (null; 2014-06-16) In this study, aeroservoelastic modeling and analysis of a missile control surface which is operated and controlled by a power limited, nonlinear electromechanical actuator is performed. Linear models of the control fin structure and aerodynamics together with the nonlinear servo-actuation system are built and integrated. The resulting aeroservoelastic system is analyzed both in time and frequency domain. Structural model of the control fin is based on the finite element model of the fin. Aerodynamic model ...
Multi-fidelity aerodynamic dataset generation of a fighter aircraft Kurt, Huseyin Burak; Millidere, Murat; Gomec, Fazıl Selcuk; Uğur, Ömür (2021-01-01) High-fidelity aerodynamic dataset generation is one of the most significant components of the aircraft flight simulation, and, it is a time consuming and costly process. Data fusion techniques suggest that, instead of using high fidelity data for entire aerodynamic dataset, an incorporating combination of high-fidelity and low-fidelity data is a more cost-effective one. The objective of data fusion is to obtain high-fidelity dataset accuracy by combining less amount of high-fidelity dataset and more amount ...
Time domain simulations of radiation from ducted fans with liners Özyörük, Yusuf; Long, L.N. (2001-01-01) Over the last few decades, noise related concerns have played a major role in the development of aircraft engines. The previously dominant jet noise mechanisms are now being replaced by tonal and broadband noise from the fan and interactions from the fan wakes and the downstream stator. Alternately, engine inlet and exhaust ducts are being fitted with sophisticated liner materials that aid in damping fan related noise. In this paper, the authors investigate the radiation problem from the engine inlets with ...
Aeroservoelastic analysis and robust controller synthesis for flutter suppression of air vehicle control actuation systems Akmeşe, Alper; Platin, Bülent Emre; Department of Mechanical Engineering (2006) Flutter is one of the most important phenomena in which aerodynamic surfaces become unstable in certain flight conditions. Since the 1930’s many studies were conducted in the areas of flutter prediction in design stage, research of design methods for flutter prevention, derivation and confirmation of flutter flight envelopes via tests, and in similar subjects for aircraft wings. With the use of controllers in 1960’s, studies on the active flutter suppression began. First the classical controllers were used....

Citation Formats

C. Çıtak, “Wave drag optimization of high speed aircraft,” M.S. - Master of Science, Middle East Technical University, 2015.