Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns)
Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag - NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil
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(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil Max thickness 12% at 30.9% chord. Max camber 3.5% at 37.1% chord Source NASA Source dat file The dat file is in Selig format |
Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag 0.99839 0.01595 0.98664 0.01580 0.95215 0.01710 0.89696 0.02355 0.82387 0.03690 0.80438 0.04073 0.77779 0.04590 0.75000 0.05124 0.72114 0.05668 0.69134 0.06218 0.66072 0.06768 0.62941 0.07312 0.59755 0.07840 0.56526 0.08341 0.53270 0.08800 0.50000 0.09201 0.46730 0.09530 0.43474 0.09777 0.40245 0.09936 0.37059 0.10000 0.33928 0.09971 0.30866 0.09846 0.27886 0.09632 0.25000 0.09339 0.22221 0.08978 0.19562 0.08553 0.17033 0.08072 0.14645 0.07539 0.12408 0.06963 0.10332 0.06345 0.08427 0.05691 0.06699 0.05017 0.05156 0.04318 0.03806 0.03575 0.02653 0.02897 0.01704 0.02201 0.00961 0.01424 0.00428 0.00784 0.00107 0.00353 0.00000 0.00000 0.00107 -0.00520 0.00428 -0.00882 0.00961 -0.01205 0.01704 -0.01502 0.02653 -0.01800 0.03806 -0.02062 0.05156 -0.02237 0.06699 -0.02406 0.08427 -0.02524 0.10332 -0.02598 0.12408 -0.02642 0.14645 -0.02653 0.17033 -0.02631 0.19562 -0.02584 0.22221 -0.02512 0.25000 -0.02419 0.27886 -0.02308 0.30866 -0.02184 0.33928 -0.02047 0.37059 -0.01904 0.40245 -0.01754 0.43474 -0.01602 0.46730 -0.01451 0.50000 -0.01301 0.53270 -0.01156 0.56526 -0.01017 0.59755 -0.00885 0.62941 -0.00761 0.66072 -0.00646 0.69134 -0.00542 0.72114 -0.00448 0.75000 -0.00364 0.77779 -0.00291 0.80438 -0.00227 0.82005 -0.00194 0.89553 0.00255 0.95184 0.00908 0.98662 0.01411 0.99839 0.01595 |
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Polars for Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| prandtl-d-root-ns | 50,000 | 9 | 22.8 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 100,000 | 9 | 51.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 200,000 | 9 | 76.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 500,000 | 9 | 102.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 1,000,000 | 9 | 117.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 2,000,000 | 9 | 119.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 5,000,000 | 9 | 128.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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