WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 100,000 Max Cl/Cd: 27.79 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-whitcomb-il-100000-n5.txt Download as CSV file: xf-whitcomb-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7544 0.07879 0.07241 -0.0506 1.0000 0.0443
-11.750 -0.8087 0.06853 0.06191 -0.0557 1.0000 0.0437
-11.500 -0.8435 0.06278 0.05595 -0.0565 1.0000 0.0436
-11.250 -0.8708 0.05866 0.05164 -0.0555 1.0000 0.0436
-11.000 -0.8947 0.05549 0.04831 -0.0532 1.0000 0.0437
-10.750 -0.9148 0.05269 0.04533 -0.0506 1.0000 0.0439
-10.500 -0.9247 0.04954 0.04193 -0.0496 1.0000 0.0444
-10.250 -0.9279 0.04644 0.03852 -0.0490 1.0000 0.0449
-10.000 -0.9253 0.04350 0.03524 -0.0484 1.0000 0.0455
-9.750 -0.9179 0.04076 0.03211 -0.0478 1.0000 0.0463
-9.500 -0.9053 0.03857 0.02966 -0.0472 1.0000 0.0471
-9.250 -0.8890 0.03711 0.02815 -0.0465 1.0000 0.0479
-9.000 -0.8718 0.03578 0.02675 -0.0460 1.0000 0.0491
-8.750 -0.8536 0.03441 0.02523 -0.0456 1.0000 0.0508
-8.500 -0.8344 0.03292 0.02349 -0.0451 1.0000 0.0528
-8.250 -0.8145 0.03153 0.02195 -0.0445 1.0000 0.0545
-8.000 -0.7940 0.03048 0.02092 -0.0440 1.0000 0.0560
-7.750 -0.7727 0.02945 0.01983 -0.0435 1.0000 0.0581
-7.500 -0.7506 0.02846 0.01867 -0.0430 1.0000 0.0609
-7.250 -0.7285 0.02749 0.01768 -0.0426 1.0000 0.0635
-7.000 -0.7057 0.02665 0.01687 -0.0423 1.0000 0.0662
-6.750 -0.6822 0.02586 0.01598 -0.0419 1.0000 0.0699
-6.500 -0.6585 0.02505 0.01518 -0.0417 1.0000 0.0736
-6.250 -0.6340 0.02433 0.01448 -0.0417 1.0000 0.0779
-6.000 -0.6090 0.02364 0.01373 -0.0415 1.0000 0.0831
-5.750 -0.5832 0.02294 0.01311 -0.0418 1.0000 0.0889
-5.500 -0.5570 0.02230 0.01247 -0.0420 1.0000 0.0960
-5.250 -0.5299 0.02169 0.01191 -0.0424 1.0000 0.1051
-5.000 -0.5022 0.02109 0.01141 -0.0430 1.0000 0.1160
-4.750 -0.4741 0.02056 0.01098 -0.0435 1.0000 0.1306
-4.500 -0.4457 0.02008 0.01061 -0.0441 1.0000 0.1499
-4.250 -0.4170 0.01962 0.01033 -0.0448 1.0000 0.1757
-4.000 -0.3872 0.01915 0.01007 -0.0457 1.0000 0.2126
-3.750 -0.3534 0.01851 0.00979 -0.0479 1.0000 0.2721
-3.500 -0.3128 0.01755 0.00965 -0.0519 1.0000 0.4010
-3.250 -0.3120 0.01839 0.01124 -0.0440 1.0000 0.4982
-3.000 -0.3163 0.01982 0.01296 -0.0344 1.0000 0.5477
-2.500 -0.2442 0.02040 0.01328 -0.0388 1.0000 0.6387
-2.000 -0.1914 0.02129 0.01402 -0.0380 1.0000 0.6712
-1.750 -0.1713 0.02176 0.01448 -0.0359 1.0000 0.6831
-1.250 -0.1285 0.02243 0.01512 -0.0326 1.0000 0.7034
-1.000 -0.1138 0.02273 0.01545 -0.0292 1.0000 0.7107
-0.750 -0.0940 0.02302 0.01576 -0.0272 1.0000 0.7215
-0.500 -0.0713 0.02334 0.01609 -0.0260 1.0000 0.7344
-0.250 -0.0610 0.02349 0.01631 -0.0217 1.0000 0.7412
0.000 -0.0312 0.02363 0.01645 -0.0226 0.9996 0.7494
0.250 0.0189 0.02383 0.01667 -0.0270 0.9887 0.7526
0.500 0.0672 0.02387 0.01674 -0.0308 0.9764 0.7550
0.750 0.1145 0.02373 0.01664 -0.0344 0.9633 0.7574
1.000 0.1635 0.02339 0.01635 -0.0382 0.9482 0.7596
1.250 0.2095 0.02290 0.01594 -0.0414 0.9321 0.7618
1.500 0.2466 0.02232 0.01544 -0.0429 0.9102 0.7640
1.750 0.2857 0.02169 0.01491 -0.0447 0.8850 0.7658
2.000 0.3106 0.02121 0.01452 -0.0436 0.8481 0.7675
2.250 0.4264 0.02038 0.01218 -0.0564 0.4853 0.7672
2.500 0.4510 0.02129 0.01233 -0.0559 0.3401 0.7684
2.750 0.4770 0.02192 0.01250 -0.0559 0.2510 0.7694
3.000 0.5026 0.02246 0.01271 -0.0558 0.1936 0.7708
3.250 0.5285 0.02294 0.01299 -0.0556 0.1565 0.7724
3.500 0.5552 0.02343 0.01332 -0.0557 0.1311 0.7737
3.750 0.5824 0.02395 0.01370 -0.0559 0.1142 0.7747
4.000 0.6099 0.02445 0.01416 -0.0562 0.1017 0.7758
4.250 0.6375 0.02498 0.01469 -0.0563 0.0924 0.7772
4.500 0.6651 0.02561 0.01527 -0.0567 0.0852 0.7786
4.750 0.6937 0.02621 0.01589 -0.0571 0.0792 0.7797
5.000 0.7220 0.02694 0.01657 -0.0576 0.0745 0.7805
5.250 0.7514 0.02762 0.01732 -0.0582 0.0697 0.7813
5.500 0.7804 0.02845 0.01808 -0.0589 0.0665 0.7822
5.750 0.8077 0.02930 0.01904 -0.0589 0.0632 0.7832
6.000 0.8335 0.03006 0.01990 -0.0586 0.0601 0.7841
6.250 0.8596 0.03093 0.02074 -0.0586 0.0578 0.7849
6.500 0.8869 0.03211 0.02203 -0.0587 0.0559 0.7854
6.750 0.9137 0.03328 0.02344 -0.0587 0.0536 0.7860
7.000 0.9393 0.03432 0.02460 -0.0586 0.0515 0.7866
7.250 0.9645 0.03538 0.02568 -0.0586 0.0500 0.7872
7.500 0.9889 0.03698 0.02748 -0.0583 0.0488 0.7880
7.750 1.0111 0.03894 0.02983 -0.0576 0.0476 0.7890
8.000 1.0314 0.04100 0.03227 -0.0568 0.0465 0.7900
8.250 1.0505 0.04299 0.03456 -0.0559 0.0454 0.7909
8.500 1.0694 0.04472 0.03651 -0.0551 0.0443 0.7915
8.750 1.0882 0.04632 0.03824 -0.0545 0.0434 0.7921
9.000 1.1051 0.04823 0.04028 -0.0538 0.0426 0.7927
9.250 1.1074 0.05195 0.04466 -0.0512 0.0419 0.7932
9.500 1.1056 0.05592 0.04916 -0.0486 0.0415 0.7937
9.750 1.0976 0.06019 0.05391 -0.0458 0.0412 0.7941
10.000 1.0817 0.06468 0.05882 -0.0427 0.0411 0.7946
10.250 1.0579 0.06929 0.06378 -0.0397 0.0410 0.7951
10.500 1.0294 0.07492 0.06972 -0.0384 0.0411 0.7957
10.750 0.9944 0.08219 0.07729 -0.0399 0.0413 0.7961
11.000 0.9491 0.09414 0.08950 -0.0483 0.0418 0.7964
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Polar data table (+)
Polar graphs
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