Narayan, KY and Gopinath, N and Seshagiri, SN (1988) Wind tunnel tests on LCA 6.02 configuration. Project Report. National Aerospace Laboratories, Bangalore.
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:||Proj.Doc/Technical Report (Project Report)|
|Uncontrolled Keywords:||LCA;High speed tests|
|Subjects:||AERONAUTICS > Aerodynamics|
|Division/Department:||Aerodynamics, Aerodynamics , Aerodynamics|
|Depositing User:||Smt Bhagya Rekha KA|
|Date Deposited:||03 Sep 2012 13:40|
|Last Modified:||25 Sep 2012 10:00|
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- Wind tunnel on LCA stage V configuration. (deposited 03 Sep 2012 12:11)
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