29th Aerospace Sciences Meeting 1991
DOI: 10.2514/6.1991-188
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CFD validation of a supersonic laminar flow control concept

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Cited by 10 publications
(2 citation statements)
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“…According to Woan et al 1991, Anderson & Bohn-Meyer 1992, and Norris 1994, the suction glove on the F-16XL Ship 1 was designed for a Mach n umber of 1.6, altitude of 44000 ft, angle of attack o f 2 o , momentum thickness Reynolds number on the attachment line of less than 114, and a unit Reynolds numb e r o f 2 : 53 10 6 ft. Suction was limited to the rst 25 chord and attachment-line CF disturbances were the primary focus of the LFC experiment Figure 5.…”
Section: High-speed Civil Transportmentioning
confidence: 99%
“…According to Woan et al 1991, Anderson & Bohn-Meyer 1992, and Norris 1994, the suction glove on the F-16XL Ship 1 was designed for a Mach n umber of 1.6, altitude of 44000 ft, angle of attack o f 2 o , momentum thickness Reynolds number on the attachment line of less than 114, and a unit Reynolds numb e r o f 2 : 53 10 6 ft. Suction was limited to the rst 25 chord and attachment-line CF disturbances were the primary focus of the LFC experiment Figure 5.…”
Section: High-speed Civil Transportmentioning
confidence: 99%
“…One could replace the existing wing of the test aircraft and build a new wing, such as in the X-21 program where a Douglas B-66 aircraft was modified with a new laminar flow swept wing (Fowell & Antonatos 1965). A second option is to install a wing glove over the existing wing as in the F-16XL experiments (Woan et al 1991), B-757 flight tests (Collier 1993), and the NASA Jetstar flight tests (Fischer et al 1983, Maddalon & Braslow 1990, to name a few. In these cases the new airfoil shape was built up over the existing wing.…”
Section: Experimental Requirementsmentioning
confidence: 99%