Wind Tunnel Wall Correction
Wind Tunnel Wall Correction

Author: B. F. R. Ewald

Publisher:

Published: 1998

Total Pages: 578

ISBN-13:

DOWNLOAD EBOOK

This report was compiled by an international team of wind tunnel wall correction experts. It presents the present state of the art in wind tunnel wall corrections with a special emphasis given to the description of modern wall correction methods based on Computational Fluid Dynamics. This AGARDograph was planned by the AGARD Fluid Dynamics Panel to be a modern sequel of the successful AGARDograph 109 "Subsonic Wind Tunnel Wall Corrections", which was published in 1966. AGARDogaph 109 is still valid and continues to be used to provide wall corrections in many wind tunnels. Nevertheless, in the thirty two years since the publication of AGARDograph 109, much work has been done on the subject, and the influence of the new tool of numerical fluid dynamics was so strong, that a sequel to AGARDograph 109 was considered to be necessary.

Wind Tunnel Wall Corrections for Arbitrary Planforms and Wind Tunnel Cross-Sections
Wind Tunnel Wall Corrections for Arbitrary Planforms and Wind Tunnel Cross-Sections

Author: Chester Arthur Heard

Publisher:

Published: 1977

Total Pages: 0

ISBN-13:

DOWNLOAD EBOOK

A computer program was developed to obtain the wind tunnel wall corrections for wing angle of attack, induced drag, and pitching moment in incompressible flow. The vortex lattice method is used for computation of these correction factors. The program can be applied to wind tunnels of arbitrary cross-sectional shape, and wings of any desired planform, subject to the constraint of straight leading and trailing edges. (Author).

On the Second-order Tunnel-wall-constriction Corrections in Two-dimensional Compressible Flow
On the Second-order Tunnel-wall-constriction Corrections in Two-dimensional Compressible Flow

Author: E. B. Klunker

Publisher:

Published: 1951

Total Pages: 32

ISBN-13:

DOWNLOAD EBOOK

Solutions of the first- and second-order Prandtl-Busemann iteration equations are obtained for the flow past thin, sharp-nose, symmetric, two-dimensional bodies in closed channels. With the use of these solutions an expression is derived for the tunnel-wall interference. The tunnel-wall correction for a parabolic-arc airfoil is calculated to indicate the effects of compressibility, ratio of the tunnel height to the airfoil chord, and airfoil thickness coefficient. It appears that, for cases where the tunnel-wall corrections are significant, both the second-order effects and the variation of the correction along the chord should be considered.

An Investigation of Several Slotted Wind Tunnel Wall Configurations with a High Disk Loading V/STOL Model
An Investigation of Several Slotted Wind Tunnel Wall Configurations with a High Disk Loading V/STOL Model

Author: Travis W. Binion

Publisher:

Published: 1971

Total Pages: 72

ISBN-13:

DOWNLOAD EBOOK

The investigation reported herein is the experimental portion of a unified theoretical and experimental search for a slotted wind tunnel wall configuration with minimal interference for conventional and V/STOL models. It is shown that theory and experiment are in excellent agreement for the classical case provided an appropriate expression is used to relate the wall geometry to the boundary condition. Classical data correction equations are not appropriate for the V/STOL case, however. An additional term, not predicted by theory, is needed to account for changes in the jet wake. Geometric parameters which influence the wall interference quantities are indicated. Wall configurations are shown which will produce interference-free force data to a jet-to-free-stream velocity ratio of 4.5. (Author).

Rectangular-wind-tunnel Blocking Corrections Using the Velocity-ratio Method
Rectangular-wind-tunnel Blocking Corrections Using the Velocity-ratio Method

Author: Rudolph W. Hensel

Publisher:

Published: 1951

Total Pages: 708

ISBN-13:

DOWNLOAD EBOOK

Calculations of the ratios of the velocity increments at test bodies to those at the tunnel walls caused by the solid blocking of these bodies within the walls of a closed rectangular wind tunnel are presented. The boides treated include two-dimensional airfoils; small bodies of revolution; straight, untapered, finite-span wings of varying span; and swept, untapered, finite-span wings of varying span. It is shown that, after wake blocking effects have been removed , the present method furnishes semiempirical blocking corrections for most wind-tunnel models and their components. The test section proportions of the Southern California Cooperative Wind Tunnel at CIT (ratio of height to width equal to 1/square root of 2) are used in the calculations.