Wind tunnel tests on LCA 6.12 configuration

Narayan, KY and Gopinath, N and Seshagiri, SN (1988) Wind tunnel tests on LCA 6.12 configuration. Project Report. National Aerospace Laboratories, Bangalore.

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Tests were conducted in the NAL 1.2m trisonic wind tunnel on a 1/20th scale model of the LCA Stage 6.12 configuration. The tests were carried out in a Mach number range of 0.5 to 1.4 and over an angle of attack range which varied from 5 deg to +28 deg at M = 0.5 to -5 deg to +12 deg at M = 1.4. The test Reynolds number (based on wing mean aerodynamic chord) varied between 4.5 x 10 power 6 to 7.0 x 10 power 6 depending on the Mach number. The results show that this configuration generates a trimmed lift-to-drag ratio of about 5.4 at a lift coefficient of 0.5 and Mach number of 0.7. Deflecting the inboard and outboard leading edge slats by 10 and 15 deg respectively increases the trimmed lift-to-drag ratio by about 5% at the same conditions. The leading edge slats also alleviate pitch-up at Mach number below 0.95.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: LCA;High speed tests
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Smt Bhagya Rekha KA
Date Deposited: 25 Sep 2012 04:30
Last Modified: 25 Sep 2012 04:30

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