Boundary-Layer Transition Results from the F-16xl-2 Supersonic Laminar Flow Control Experiment PDF Download

Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723819070
Category : Science
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