This paper presents the parameterization and optimization of two well-known airfoils. The aerodynamic shape investigation includes subsonic (NREL S-821) transonic airfoils (RAE-2822). class transformation is employed for parametrization while genetic algorithm used purposes. absolute scheme process carried out minimization drag coefficient maximization lift to ratio. In-house MATLAB code incorp...

Abstract In the early era of aviation, Frederick Lanchester was both an inventor and a theoretician driven by need for theory flight that would reduce guesswork in designing new aircraft. His book Aerodynamics 1907 laid down foundations such theory. The with contributions from others, notably Ludwig Prandtl, refined to become basis sleek designs WWII aircraft brought about little guesswork. New...

To achieve multi-objective aerodynamics design optimization for a 1.5-stage transonic compressor, platform incorporating blade parameterization methods, BPNN surrogate model, and the NSGA-II method was developed. The stagger angle distribution of three rows selected as variable, with isentropic efficiency at new condition stall margin set goal functions. Results demonstrated that, without alter...

The aerodynamic design of modern civil aircraft requires a true sense intelligence since it good understanding transonic aerodynamics and sufficient experience. Reinforcement learning is an artificial general that can learn sophisticated skills by trial error, rather than simply extracting features or making predictions from data. present paper uses deep reinforcement-learning algorithm to the ...

We establish the existence and stability of multidimensional steady transonic flows with transonic shocks through an infinite nozzle of arbitrary cross-sections, including a slowly varying de Laval nozzle. The transonic flow is governed by the inviscid potential flow equation with supersonic upstream flow at the entrance, uniform subsonic downstream flow at the exit at infinity, and the slip bo...

Abstract In the present study, a nonlinear system identification approach based on long short-term memory (LSTM) neural network is applied for prediction of transonic buffet aerodynamics. The as reduced-order modeling (ROM) technique an efficient computation time-varying integral quantities such aerodynamic force and moment coefficients. Therefore, procedure well generalization ROM are presente...

A hypervelocity imperfect gas nozzle with a shared wave-elimination contour is designed by the residual correction method, allowing test Mach number to be varied changing throat contours. Owing effects, classical method of characteristics boundary layer does not produce uniform flow field, resulting in significant deviation from target number. In this work, computational fluid dynamics solver u...

We study the uniqueness of solutions with a transonic shock in a duct in a class of transonic shock solutions, which are not necessarily small perturbations of the background solution, for steady potential flow. We prove that, for given uniform supersonic upstream flow in a straight duct, there exists a unique uniform pressure at the exit of the duct such that a transonic shock solution exists ...

In this paper, we present a monitoring program of loss control prevention for airlines to enhance aviation safety and operational efficiency. The assessments dynamic stability characteristics based on the approaches oscillatory motion eigenvalue modes jet transport aircraft response sudden plunging motions are demonstrated. A twin-jet encountering severe clear-air turbulence in transonic flight...

The objective of the current work is to define a design optimization methodology in aerodynamics, which all numerical components are based on unique geometrical representation, consistent with Computer-Aided Design (CAD) standards. In particular, parameterized by Non-Uniform Rational B-Splines (NURBS), computational domain automatically constructed using rational Bézier elements extracted from ...