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:

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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.

High Speed Problems of Aircraft and Experimental Methods
High Speed Problems of Aircraft and Experimental Methods

Author: Allen F. Donovan

Publisher: Princeton University Press

Published: 2015-12-08

Total Pages: 1021

ISBN-13: 140087503X

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Volume VIII of the High Speed Aerodynamics and Jet Propulsion series. This volume includes: performance calculation at high speed; stability and control of high speed aircraft; aeroelasticity and flutter; model testing; transonic wind tunnels; supersonic tunnels; hypersonic experimental facilities; low density wind tunnels; shock tube; wind tunnel measurements; instrumented models in free flight; piloted aircraft testing; free flight range methods. Originally published in 1961. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.

Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4
Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4

Author: Paul G. Fournier

Publisher:

Published: 1953

Total Pages: 34

ISBN-13:

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The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.

Method for Calculating Effects of Dissociation on Flow Variables in the Relaxation Zone Behind Normal Shock Waves
Method for Calculating Effects of Dissociation on Flow Variables in the Relaxation Zone Behind Normal Shock Waves

Author: John S. Evans

Publisher:

Published: 1956

Total Pages: 668

ISBN-13:

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Because the chemical reaction rates needed to predict the dependence of degree of dissociation on distance behind the shock are not known, order-of-magnitude estimates of their values have been used in a numerical example, the purpose of which is to illustrate the use of reaction-rate equations to predict relaxation time and distance behind the shock front.

Wind-tunnel Investigation to Determine the Horizontal- and Vertical-tail Contributions to the Static Lateral Stability Characteristics of a Complete-model Swept-wing Configuration at High Subsonic Speeds
Wind-tunnel Investigation to Determine the Horizontal- and Vertical-tail Contributions to the Static Lateral Stability Characteristics of a Complete-model Swept-wing Configuration at High Subsonic Speeds

Author: James W. Wiggins

Publisher:

Published: 1956

Total Pages: 692

ISBN-13:

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An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. The results indicate that, in a general, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.

Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives
Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives

Author: James W. Wiggins

Publisher:

Published: 1954

Total Pages: 56

ISBN-13:

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An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.