A computational study of subsonic flows over a medium range cargo aircraft

Inviscid and viscous flows over CN-235 cargo aircraft are computed at cruise conditions and at angles of attack ranging from 0 deg to 5 deg using CFD-FASTRAN Navier-Stokes solver. Computations are performed on a Pentium III based PC with a 1Gb memory. Grid sensitivity and verification studies are performed on clean-wing and wing-nacelle configurations to determine the effects of the surface grid density, the size of the computational domain and available numerical schemes. Inviscid and viscous flows with available turbulence models over the full aircraft are computed at a range of incidence angles using multi-block structured grids. Computed aerodynamic forces and moments are also compared with semi-empirical and numerical data available in the literature. It is shown that viscous flow solutions provide valuable aerodynamic data, which may be used in determining and/or altering the aerodynamic characteristics of the aircraft. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.


A New method for the calculation of static flight loads of rigid fuselage of rotorcraft
Gül, Seyhan; Yaman, Yavuz; Department of Aerospace Engineering (2016)
The loads acting on a rotorcraft fuselage in pull-up, push-over, and yaw maneuvers and gust conditions are required to be calculated by civil and military standards. For each maneuver and the gust condition, different flight and rotor speeds, mass states, altitudes, and temperatures are required to be analyzed. This may add up to thousands of conditions. Calculation of fuselage loads for all these conditions with transient analysis is not only computationally expensive but it also requires a lot of engineer...
A computational study of a close-coupled delta canard-wing-body configuration
Tuncer, İsmail Hakkı; Vandyken, Robert B (1996-06-20)
Subsonic flowfields over a close-coupled delta canard-wing-body configuration at high angles of attack from 20° to 30' are computed using the OVERFLOW Navier-Stokes solver. Computed flowfields are presented in terms of particle traces, surface streamlines and leeward-side surface pressure distributions for the canard on and off configurations. The interaction between the canard and the wing vortices, wing vortex breakdown and the influence of the canard on vortex breakdown are identified. It is computed tha...
A computational study on the dynamic stall of a flapping airfoil
Tuncer, İsmail Hakkı; Platzer, Max F. (1998-01-01)
© 1998, American Institute of Aeronautics and Astronautics, Inc.The dynamic stall boundaries of a NACA 0012 airfoil oscillating in either the pure plunge mode or in the combined pitch and plunge mode is computed using a thin-layer Navier-Stokes solver. Unsteady flowfields are computed at the free-stream Mach number of 0.3, the Reynolds number of 1 • 106, and the Baldwin-Lomax turbulence model is employed. It is found that the pure plunge oscillation leads to dynamic stall as soon as the non-dimensional plun...
Development of Structural Neural Network Design Tool for Buckling Behaviour of Skin-Stringer Structures Under Combined Compression and Shear Loading
Okul, Aydın; Gürses, Ercan (2018-11-15)
Stiffened panels are commonly used in aircraft structures in order to resist high compression and shear forces with minimum total weight. Minimization of the weight is obtained by combining the optimum design parameters. The panel length, the stringer spacing, the skin thickness, the stringer section type and the stringer dimensions are some of the critical parameters which affect the global buckling allowable of the stiffened panel. The aim of this study is to develop a design tool and carry out a geometri...
A numerical study of solidification and viscous dissipation effects on polymer melt flow in plane channels
Tutar, Mustafa; Karakuş, Ali (Walter de Gruyter GmbH, 2013-04-01)
The combined effects of solidification and viscous dissipation on the hydrodynamic and thermal behavior of polymer melt flow during the injection process in a straight plane channel of constant cross section are numerically studied by considering the shear-rate and temperature-dependent viscosity and transient-phase change behavior. A numerical finite volume method, in conjunction with a modified form of the Cross constitutive equation to account for shear rate, temperature-dependent viscosity changes and a...
Citation Formats
M. Uygun and İ. H. Tuncer, “A computational study of subsonic flows over a medium range cargo aircraft,” 2003, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/57110.