WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)
WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL - NASA/Langley Whitcomb integral supercritical airfoil
Details | Dat file | Parser | |
(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord. Max camber 2.4% at 82.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL 37. 37. 0.0 0.0 .0075 .0176 .0125 .0215 .0250 .0276 .0375 .0316 .0500 .0347 .0750 .0394 .1000 .0428 .1250 .0455 .1500 .0476 .1750 .0493 .2000 .0507 .2500 .0528 .3000 .0540 .3500 .0547 .4000 .0550 .4500 .0548 .5000 .0543 .5500 .0533 .5750 .0527 .6000 .0519 .6250 .0511 .6500 .0501 .6750 .0489 .7000 .0476 .7250 .0460 .7500 .0442 .7750 .0422 .8000 .0398 .8250 .0370 .8500 .0337 .8750 .0300 .9000 .0255 .9250 .0204 .9500 .0144 .9750 .0074 1.0000 -.0008 0.0 0.0 .0075 -.0176 .0125 -.0216 .0250 -.0281 .0375 -.0324 .0500 -.0358 .0750 -.0408 .1000 -.0444 .1250 -.0472 .1500 -.0493 .1750 -.0510 .2000 -.0522 .2500 -.0540 .3000 -.0548 .3500 -.0549 .4000 -.0541 .4500 -.0524 .5000 -.0497 .5500 -.0455 .5750 -.0426 .6000 -.0389 .6250 -.0342 .6500 -.0282 .6750 -.0215 .7000 -.0149 .7250 -.0090 .7500 -.0036 .7750 .0012 .8000 .0053 .8250 .0088 .8500 .0114 .8750 .0132 .9000 .0138 .9250 .0131 .9500 .0106 .9750 .0060 1.0000 -.0013 |
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Polars for WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
whitcomb-il | 50,000 | 9 | 22.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
whitcomb-il | 50,000 | 5 | 19.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
whitcomb-il | 100,000 | 9 | 22.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
whitcomb-il | 100,000 | 5 | 27.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
whitcomb-il | 200,000 | 9 | 30.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
whitcomb-il | 200,000 | 5 | 39.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
whitcomb-il | 500,000 | 9 | 49.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
whitcomb-il | 500,000 | 5 | 59.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
whitcomb-il | 1,000,000 | 9 | 69 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
whitcomb-il | 1,000,000 | 5 | 76.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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