Boundary-layer Transition Results from the F-16XL-2 Supersonic Laminar Flow Control Experiment PDF Download
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Author: Laurie A. Marshall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 58
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Book Description
A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 multiplied by 10[factor 6], optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.
Author: Laurie A. Marshall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 58
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Book Description
A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 multiplied by 10[factor 6], optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781726233927
Category :
Languages : en
Pages : 56
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Book Description
A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 X 10(exp 6), optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.Marshall, Laurie A.Armstrong Flight Research CenterLAMINAR FLOW; LAMINAR BOUNDARY LAYER; BOUNDARY LAYER TRANSITION; BOUNDARY LAYER CONTROL; SUPERSONIC FLOW; SUCTION; CIVIL AVIATION; SUPERSONIC SPEED; ALTITUDE; MACH NUMBER; SWEPT WINGS; F-16 AIRCRAFT; PRESSURE DISTRIBUTION...
Author: Colin Phillip Coleman
Publisher:
ISBN:
Category :
Languages : en
Pages : 212
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 420
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 426
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 268
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 848
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Book Description
Author: Russell H. Thomas
Publisher:
ISBN:
Category : Aerodynamical noise
Languages : en
Pages : 98
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Book Description
Author: United States. Congress. House. Committee on Appropriations. Subcommittee on VA, HUD, and Independent Agencies
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1068
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Book Description
Author: John E. Lamar
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 170
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Book Description
Geometrical, flight, computational fluid dynamics (CFD), and wind-tunnel studies for the F-16XL-1 airplane are summarized over a wide range of test conditions. Details are as follows: (1) For geometry, the upper surface of the airplane and the numerical surface description compare reasonably well. (2) For flight, CFD, and wind-tunnel surface pressures, the comparisons are generally good at low angles of attack at both subsonic and transonic speeds; however, local differences are present. In addition, the shock location at transonic speeds from wind-tunnel presure contours is near the aileron hinge line and generally is in correlative agreement with flight results.
