Wind-tunnel-flight Correlation of Shock-induced Separated Flow PDF Download
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Author: Donald L. Loving
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 20
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Book Description
Author: Donald L. Loving
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 20
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Book Description
Author: Charles D. Harris
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 964
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1288
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 920
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Book Description
Author: J. F. Cahill
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 88
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Book Description
Author: Russell J. Donnelly
Publisher: Springer Science & Business Media
ISBN: 1461222303
Category : Science
Languages : en
Pages : 483
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Book Description
Scientists have learned to use liquid and gaseous helium to overcome the limitations imposed by the usual wind and water tunnels for testing the performance of aircraft or the behavior of the atmosphere. This book covers fundamental studies of the turbulence problem, practical applications of turbulence, superfluid turbulence, cryogenic turbulence research, and new types of miniature flow instrumentation, all which are crucial for high Reynolds number research. This state-of-the-art presentation will interest physicists in fluid dynamics, engineers working with turbulent flows, and naval and aerospace engineers testing realistic parameter ranges.
Author: E. M. Kraft
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 84
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Book Description
The wind tunnel boundary interference at transonic speeds on a thin airfoil in a two-dimensional perforated-wall wind tunnel was determined. The interference was found by applying an integral equation method to the nonlinear transonic small disturbance equation including embedded supersonic regions with shock waves. The kernels of the ensuing integral equation were replaced by series approximations, and the integrals were evaluated in closed form. The iterative technique used to calculate the interference from the integral equation method is shown to converge rapidly, and the computing time for the integral equation method is typically an order of magnitude less than present numerical methods. As a special case, the integral equation method for a thin airfoil in free air was also examined. It was found that the introduction of a novel influence function yields, for the first time, a self-contained integral equation for a lifting airfoil. In addition, a systematic study of the classical assumption used to simplify the integral equation shows that the integral method can provide solutions in good agreement with results from the numerical methods.
Author:
Publisher:
ISBN:
Category : Aerothermodynamics
Languages : en
Pages : 320
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Book Description
Author: C. F. Lo
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 74
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Book Description
The transonic scaling effect of shock wave/boundary-layer interaction on a quasi, two-dimensional C-141 airfoil was investigated. Data were obtained from the AEDC Propulsion Wind Tunnel Facility Aerodynamic Wind Tunnel (4T) and Propulsion Wind Tunnel (16T) and from the NASA Marshall Space FLIGHT Center High Reynolds Number Tunnel with 6-in.- and 24-in.-chord airfoils for a range 0.70 to 0.85. In addition to the investigation of the effect of Reynolds number on the airfoil pressure distribution, the effect of fixed boundary-layer transition was evaluated using grit-type transition strips on the airfoil surface. The significant parameters affecting the shock wave/boundary-layer interaction are identified. The data indicate that simulation of higher Reynolds number data on the C-141 airfoil model is feasible by use of a fixed-boundary-layer-transition strip. (Author).
