Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 25
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Book Description
Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Book Description
Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
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Author: Reino J. Salmi
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ISBN:
Category :
Languages : en
Pages : 36
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Author: Harold Mirels
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ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
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Book Description
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 9
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Book Description
Results of recent wind-tunnel pressure-distribution tests on a large-scale boundary-layer-control model with a 49 degree sweptback wing have indicated that blowing air at low blowing rates over highly deflected trailing-edge flaps does not produce any unusual flap-load or wing-load problems at low speed. Blowing at very high momentum rates, however, produces large increased in flap loads and extremely high local negative pressures over the flap leading edge.
Author: Roy H. Lange
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Author: Jones F. Cahill
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 36
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Book Description
Pressure distributions over a retracted leading-edge slat on a 40 degree sweptback wing are presented for a series of angles of attack up to maximum lift at Mach numbers of 0.1, 0.4, 0.6, 0.7, 0.8, 0.85, and 0.9. These data were obtained in the Langley low-turbulence pressure tunnel at a constant Reynolds number of approximately 3,000,000. The Reynolds number was maintained approximately constant through the Mach number range by varying the stagnation pressure.
Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 134
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Author: Zachary T. Applin
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1152
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Book Description
