Rectangular Wind Tunnel Blocking Corrections Using The Velocity Ratio Method
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| Author | : Rudolph W. Hensel |
| Publisher | : |
| Total Pages | : 708 |
| Release | : 1951 |
| Genre | : Mathematical analysis |
| ISBN | : |
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.
| Author | : Allen F. Donovan |
| Publisher | : Princeton University Press |
| Total Pages | : 1021 |
| Release | : 2015-12-08 |
| Genre | : Science |
| ISBN | : 140087503X |
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.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1026 |
| Release | : 1958 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 568 |
| Release | : 1951 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Paul G. Fournier |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1953 |
| Genre | : Airplanes |
| ISBN | : |
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.
| Author | : James W. Wiggins |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1954 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : Paul G. Fournier |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1953 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : John S. Evans |
| Publisher | : |
| Total Pages | : 668 |
| Release | : 1956 |
| Genre | : Air flow |
| ISBN | : |
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.
| Author | : James W. Wiggins |
| Publisher | : |
| Total Pages | : 692 |
| Release | : 1956 |
| Genre | : Airplanes |
| ISBN | : |
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.
| Author | : James W. Wiggins |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1954 |
| Genre | : Airplanes |
| ISBN | : |
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.
