Analysis of a civil aircraft wing transonic shock buffet experiment

Oblique Wing: Future Generation Transonic Aircraft

Numerical Simulation of Transonic Buffet on Swept Wing of Supercritical Airfoils

This paper presents transonic buffet simulations over a swept wing of supercritical airfoils with Unsteady Reynolds-Averaged Navier-Stokes (URANS) and Detached-Eddy Simulation (DES) methods. The NASA SC(2)-0714 airfoil is used as wing profile. Computations are conducted at free-stream Mach numbers from 0.72 to 0.84 for Reynolds number 45.0 × 10 based on aerodynamic chord length. Firstly, 2D NAS...

Modeling, simulation and analysis of a multi degree of freedom aircraft wing model

This paper presented methods to determine the aerodynamic forces that acton an aircraft wing during flight. These methods are initially proposed for asimplified two degree-of-freedoms airfoil model and then are extensivelyapplied for a multi-degree-of-freedom airfoil system. Different airspeedconditions are considered in establishing such methods. The accuracy of thepresented methods is verifie...

Free-To-Roll Analysis of Abrupt Wing Stall on Military Aircraft at Transonic Speeds

LE leading edge Transonic free-to-roll and static wind tunnel tests for four military aircraft – the AV-8B, the F/A-18C, the pre-production F/A-18E, and the F-16C – have been analyzed. These tests were conducted in the NASA Langley 16-Foot Transonic Tunnel as a part of the NASA/Navy/Air Force Abrupt Wing Stall Program. The objectives were to evaluate the utility of the freeto-roll test techniqu...

A Numerical Study of Transonic Buffet on a Supercritical Airfoil

The steady/unsteady flow of the BGK No. 1 supercritical airfoil is investigated by the solution of the Reynolds-Averaged Navier-Stokes equations with a two-equation k-ω turbulence model. The dual-time stepping method is used to march in time. Two steady cases ( 71 . 0 = Ma , 396 . 1 = α and 71 . 0 = Ma , 0 . 9 = α ) and one unsteady case ( 71 . 0 = Ma , 97 . 6 = α ), both with a far-stream 6 10...