Wind tunnel tests on LCA 6.02 configuration

Narayan, KY and Gopinath, N and Seshagiri, SN (1988) Wind tunnel tests on LCA 6.02 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 6.02 configuration. The tests were carried out in a Mach number range of 0.5 to 1.6 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 = 1.6. The test Reynolds number (based on wing mean aerodynamic chord) varied between 4.8 to 10.28 millions depending on the Mach number. The tests Included : (i) determination of the longitudinal characteristics of the configuration and (ii) determination of longitudinal, lateral and directional control powers.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: LCA;High speed tests
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Smt Bhagya Rekha KA
Date Deposited: 03 Sep 2012 08:10
Last Modified: 25 Sep 2012 04:30

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