Krishnamurthy, K (1989) Tests on NAL-114-26-00 symmetric supercritical airfoil in 0.3M Wind tunnel. Project Report. National Aerospace Laboratories, Bangalore.
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Abstract
This report presents the results of the experimental investigation on a NAL-114-36-00 symmetric supercritical airfoil developed at NAL and tested in O.3m wind tunnel over a free stream Mach number range of 0.53 to 0.85 and angle of incidence range of 0° to 4°. Model surface pressures were measured and compared with the theoretical pressure distribution of the same airfoil and also of baseline airfoil NACAO012. Comparison showed that the symmetric supercritical aerofoil was shock free at design Mach number and angle of incidence, matching with theoretical predictions whereas NACA0012 airfoil had strong shock for the same design conditions .
| Item Type: | Monograph (Project Report) |
|---|---|
| Uncontrolled Keywords: | Supercritical airfoil;2D-airfoils;Exp. pressure distribution |
| Subjects: | AERONAUTICS > Aerodynamics |
| Depositing User: | Smt Bhagya Rekha KA |
| Date Deposited: | 19 Dec 2012 04:38 |
| Last Modified: | 19 Dec 2012 04:38 |
| URI: | http://nal-ir.nal.res.in/id/eprint/11396 |
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