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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Abstract
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: | 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: | 25 Sep 2012 10:00 |
| Last Modified: | 25 Sep 2012 10:00 |
| URI: | http://nal-ir.nal.res.in/id/eprint/10886 |
Available Versions of this Item
- Wind tunnel on LCA stage V configuration. (deposited 03 Sep 2012 12:11)
- Wind tunnel tests on LCA 6.02 configuration. (deposited 03 Sep 2012 13:40)
- Wind tunnel tests on LCA 6.12 configuration. (deposited 25 Sep 2012 10:00)[Currently Displayed]
- Wind tunnel tests on LCA 6.02 configuration. (deposited 03 Sep 2012 13:40)
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