Srilatha, KR and Ramamoorthy, P (1989) Performance of NAL- MSNLF-136 airfoil with boundary layer tripped at 5 and 10 of the chord. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
Recently NAL has designed a natural laminar flow airfoil NAL--MSNLF-136 for use on a-genergl aviation aircraft for the design copditions M - 0.6, R - 10 x 10 and C -0.4. In order to validate this airfoil in the NA l' x 'I' tunnh , performance calculations have been carried out with 5% and 10% boundary, layer trippings. It is generally seen that while the lift co-efficients decrease the drag co-efficients increase relative to the natural flow case
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Design;Airfoil;Laminar flow;General aviation |
| Subjects: | AERONAUTICS > Aircraft Propulsion and Power |
| Division/Department: | Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division |
| Depositing User: | Ms Indrani V |
| Date Deposited: | 13 Jul 2006 |
| Last Modified: | 24 May 2010 09:44 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1929 |
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