by Aerospace Engineering Dept., Texas A&M University, National Aeronautics and Space Administration, National Technical Information Service, distributor in College Station, Tex, [Washington, DC, Springfield, Va.? .
Written in English
|Series||NASA-CR -- 190570., Texas A&M Research Foundation report -- no. 5802-92-02., NASA contractor report -- NASA CR-190570., Texas A&M Research Foundation report -- no. 5802-92-02.|
|Contributions||El-Banna, Hesham M., United States. National Aeronautics and Space Administration.|
|The Physical Object|
viable and efficient concept for the determination of three-dimensional transonic aerodynamic sensitivity coefficients. In addition, use of symbolic manipulation to evaluate the elements of the sensitivity equation is believed to be an efficient approach to the development of such methods. Deflections of a spoiler modify the airfoil/wing geometry in such a way that the upper surface becomes nearly flat or concave in a vicinity of the spoiler hinge. In the s, numerical studies demonstrated a high sensitivity of transonic flow over airfoils comprising a flat or nearly flat arc to small perturbations. This paper addresses the 3D transonic flow over wings with J airfoil at spanwise sections. The study is focused on the determination of Mach numbers and angles of attack that admit a high sensitivity of the flow field to small by: 6. The problem of determining the integral aerodynamic characteristics of aircraft as a whole in the transonic velocity range is considered. An approximate method of their calculation is developed using the nonlinear transonic theory of small perturbations for three-dimensional flow over a Author: M. A. Naida, A. S. Fonarev.
Aerodynamic design of high speed airfoils and wings is carried out by a new Genetic Algorithm software and applied to novel configurations like the Oblique Flying Wing. The goal is achieved by establishing a flexible input data generator for both direct and inverse design: geometry and flow quality (pressure distribution) is modelled by a set of analytical functions with parameterized by: Transonic Aerodynamics of Airfoils and Wings. Introduction. Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ).File Size: 2MB. The flow coefficient ϕ is a measure of the angle of incidence of the flow and the aerodynamic forces developed are critically dependent upon this parameter. Typical results based on predictions and experiments of the non-dimensional pressure drop p * = Δ p / (ρ ω 2 D t 2) and efficiency are shown in Figure At those speeds the flow domain is termed transonic and contains both subsonic and supersonic flow. Typical aerodynamic characteristics in this domain are shock waves, drag divergence, and transonic buffet. To suppress these adverse effects or postpone them to higher Mach numbers, multiple design measures can be taken.
Aerodynamic sensitivity analysis is performed for the Navier-Stokes equations, coupled with two-equation turbulence. models using a discrete adjoint method and a direct differentiation method. We analyzed the static aeroelasticity of HIRENASD wing in transonic flow field by coupling with the generalized force model by the static equilibrium equation. The results were compared with those of the experimental data and the references, and the comparison shows that the method is Cited by: 1. AEROFOIL AERODYNAMIC CHARACTERISTIC IN TRANSONIC FLOW REGIME Robert Placek*, Marek Miller*, Paweł Ruchała* *Institute of Aviation, Krakowska /, Warsaw, Poland Keywords: wind tunnel, shock wave, roughness, transonic, aerodynamic coefficient. The determination of right wing is the most vital part of plane outline which decides lift compel age, drag constrain Coefficient of lift will be higher at an angle of 25 degree. 2. As the angle of attack increase the amount of lift created Flow and Aerodynamic Forces on an Airfoil.