Wind Tunnel Interference Factors for High-lift Wings in Closed Wind Tunnels PDF Download
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Author: Robert Glenn Joppa
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 119
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Book Description
Author: Robert Glenn Joppa
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 119
Get Book Here
Book Description
Author: Robert Glenn Joppa
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 132
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Book Description
A problem associated with the wind tunnel testing of very slow flying aircraft is the correction of observed pitching moments to free air conditions. The most significant effects of such corrections are to be found at moderate downwash angles typical of the landing approach. The wind tunnel walls induce interference velocities at the tail different from those induced at the wing, and these induced velocities also alter the trajectory of the trailing vortex system. The relocated vortex system induces different velocities at the tail from those experienced in free air. The effect of the relocated vortex and the walls is to cause important changes in the measured pitching moments in the wind tunnel.
Author: Robert Glenn Joppa
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 132
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Book Description
Author: Ray H. Wright
Publisher:
ISBN:
Category : Interference (Aerodynamics)
Languages : en
Pages : 28
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Book Description
A theory is presented for the boundary-induced upwash interference on a sweptback wing mounted in a rectangular wind-tunnel test section with closed top and bottom walls and slotted side walls. The interference factor can be computed at any point in the test section. In an example, the interference with slotted side walls is compared with that with slotted top and bottom walls.
Author: Ray H. Wright
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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Book Description
A theory is presented for the boundary-induced up-wash interference on a sweptback lifting wing mounted at the center of a rectangular wind-tunnel test section with slotted top and bottom walls and closed side walls. A sample calculation for a wing spanning 0.7 of the width of a square tunnel shows the span-wise variation in the interference characteristic of this type of test section. For this example, the wing sweep did not have a large effect on the interference.
Author: Benferd L. Schilling
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 66
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Book Description
Author: Marie H. Tuttle
Publisher:
ISBN:
Category : Interference (Aerodynamics)
Languages : en
Pages : 58
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Book Description
Author: Marie H. Tuttle
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
Author: Ray H. Wright
Publisher:
ISBN:
Category : Interference (Aerodynamics)
Languages : en
Pages : 92
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Book Description
A wind-tunnel test section with closed upper wall, slotted side walls, and open lower boundary was found theoretically to produce zero tunnel-boundary lift interference on a small wing with horizontal wake mounted at the center of the test section. For this test section the variation of the interference with angle of the vortex wake behind a high-lift-coefficient model was not large. Because of the small slot widths required for zero interference and of the effects of boundary layer, the theory is regarded as unreliable for predicting the slot widths required; however, the variation of the interference with the slot width for widths somewhat greater than those needed for zero interference was found to be small. The interference in the region likely to be occupied by the tall of a model was investigated in some detail and was found to change with slot width and with wake angle more strongly than did the interference at the lifting element. A limited investigation of the lift interference in a test section with closed upper wall and slotted side and lower boundaries was made to obtain the theoretically indicated slot width required for zero lift interference at a center-mounted wing with the wake horizontal.
Author: Ray H. Wright
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 42
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Book Description
An approximation method has been developed for calculating the spanwise distribution of wind-tunnel-boundary upwash interference on lift of wings in rectangular perforated-wall test sections. This method is applied to square test sections with an assumed effective permeability constant of 0.6. A problem of considerable difficulty in practical application of the method presented is the estimation of an effective permeability constant. Because of the variation of the upwash interference with Mach number and of the influence of boundary layer on the effective permeability factor, the boundary interference in a perforated-wall wind-tunnel test section at high subsonic Mach numbers is likely to be of the nature of that in an open-throat tunnel.
