NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 100,000 Max Cl/Cd: 33.44 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20712-il-100000-n5.txt Download as CSV file: xf-sc20712-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0712 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7020 0.08011 0.07384 -0.0571 1.0000 0.0443
-12.750 -0.7486 0.07008 0.06362 -0.0631 1.0000 0.0439
-12.500 -0.7830 0.06379 0.05713 -0.0653 1.0000 0.0438
-12.250 -0.8120 0.05921 0.05238 -0.0651 1.0000 0.0438
-12.000 -0.8387 0.05579 0.04880 -0.0632 1.0000 0.0439
-11.750 -0.8611 0.05269 0.04551 -0.0610 1.0000 0.0440
-11.500 -0.8745 0.04928 0.04181 -0.0601 1.0000 0.0444
-11.250 -0.8807 0.04596 0.03810 -0.0592 1.0000 0.0450
-11.000 -0.8791 0.04306 0.03483 -0.0584 1.0000 0.0459
-10.750 -0.8663 0.04170 0.03346 -0.0576 1.0000 0.0469
-10.500 -0.8531 0.04028 0.03195 -0.0570 1.0000 0.0480
-10.250 -0.8392 0.03863 0.03011 -0.0564 1.0000 0.0494
-10.000 -0.8241 0.03671 0.02792 -0.0560 1.0000 0.0510
-9.750 -0.8072 0.03474 0.02560 -0.0555 1.0000 0.0524
-9.500 -0.7887 0.03324 0.02397 -0.0550 1.0000 0.0539
-9.250 -0.7692 0.03223 0.02295 -0.0546 1.0000 0.0556
-9.000 -0.7488 0.03116 0.02177 -0.0542 1.0000 0.0577
-8.750 -0.7278 0.02997 0.02039 -0.0537 1.0000 0.0600
-8.500 -0.7064 0.02881 0.01907 -0.0531 1.0000 0.0620
-8.250 -0.6850 0.02792 0.01825 -0.0527 1.0000 0.0642
-8.000 -0.6625 0.02712 0.01741 -0.0525 1.0000 0.0672
-7.750 -0.6396 0.02631 0.01646 -0.0520 1.0000 0.0703
-7.500 -0.6169 0.02544 0.01560 -0.0517 1.0000 0.0731
-7.250 -0.5930 0.02476 0.01496 -0.0517 1.0000 0.0768
-7.000 -0.5685 0.02414 0.01427 -0.0516 1.0000 0.0814
-6.750 -0.5434 0.02341 0.01360 -0.0518 1.0000 0.0856
-6.500 -0.5174 0.02284 0.01303 -0.0521 1.0000 0.0913
-6.250 -0.4906 0.02226 0.01246 -0.0526 1.0000 0.0979
-6.000 -0.4631 0.02173 0.01196 -0.0533 1.0000 0.1058
-5.750 -0.4346 0.02120 0.01149 -0.0542 1.0000 0.1158
-5.500 -0.4055 0.02072 0.01110 -0.0553 1.0000 0.1295
-5.250 -0.3752 0.02022 0.01074 -0.0566 1.0000 0.1510
-5.000 -0.3427 0.01963 0.01038 -0.0586 1.0000 0.1897
-4.750 -0.3040 0.01872 0.01000 -0.0623 1.0000 0.2775
-4.500 -0.2649 0.01786 0.01010 -0.0659 1.0000 0.4411
-4.250 -0.2486 0.01832 0.01099 -0.0627 0.9998 0.5309
-4.000 -0.2176 0.01873 0.01142 -0.0631 0.9968 0.5790
-3.750 -0.1851 0.01919 0.01182 -0.0638 0.9940 0.6085
-3.500 -0.1529 0.01960 0.01214 -0.0646 0.9909 0.6322
-3.250 -0.1256 0.02015 0.01267 -0.0640 0.9871 0.6485
-3.000 -0.0987 0.02082 0.01334 -0.0630 0.9836 0.6644
-2.750 -0.0760 0.02147 0.01400 -0.0610 0.9794 0.6776
-2.500 -0.0497 0.02192 0.01444 -0.0602 0.9751 0.6902
-2.250 -0.0203 0.02229 0.01479 -0.0602 0.9716 0.6998
-2.000 0.0120 0.02250 0.01497 -0.0610 0.9685 0.7070
-1.750 0.0360 0.02269 0.01518 -0.0600 0.9631 0.7127
-1.500 0.0740 0.02274 0.01519 -0.0627 0.9595 0.7210
-1.250 0.1067 0.02284 0.01530 -0.0635 0.9559 0.7245
-1.000 0.1338 0.02289 0.01537 -0.0635 0.9501 0.7278
-0.750 0.1667 0.02291 0.01541 -0.0648 0.9454 0.7315
-0.500 0.2061 0.02288 0.01540 -0.0676 0.9419 0.7356
-0.250 0.2427 0.02282 0.01536 -0.0699 0.9358 0.7394
0.000 0.2774 0.02267 0.01529 -0.0710 0.9279 0.7416
0.250 0.3140 0.02236 0.01504 -0.0722 0.9163 0.7441
0.500 0.3591 0.02166 0.01442 -0.0745 0.9004 0.7467
0.750 0.4062 0.02077 0.01359 -0.0770 0.8825 0.7493
1.000 0.4517 0.01993 0.01281 -0.0793 0.8631 0.7519
1.250 0.4875 0.01943 0.01238 -0.0803 0.8390 0.7553
1.500 0.5199 0.01898 0.01200 -0.0803 0.8106 0.7575
1.750 0.5533 0.01852 0.01157 -0.0802 0.7663 0.7597
2.000 0.6043 0.01807 0.01050 -0.0825 0.6050 0.7614
2.250 0.6236 0.01930 0.01061 -0.0805 0.4089 0.7640
2.500 0.6432 0.02045 0.01104 -0.0794 0.2806 0.7671
2.750 0.6677 0.02136 0.01149 -0.0794 0.2035 0.7702
3.000 0.6941 0.02208 0.01193 -0.0796 0.1620 0.7729
3.250 0.7166 0.02269 0.01239 -0.0787 0.1392 0.7747
3.750 0.7643 0.02384 0.01347 -0.0774 0.1115 0.7792
4.000 0.7891 0.02446 0.01408 -0.0770 0.1022 0.7820
4.250 0.8142 0.02519 0.01474 -0.0769 0.0946 0.7851
4.500 0.8424 0.02586 0.01548 -0.0773 0.0876 0.7884
4.750 0.8641 0.02659 0.01617 -0.0762 0.0829 0.7905
5.000 0.8880 0.02731 0.01697 -0.0755 0.0780 0.7928
5.250 0.9124 0.02805 0.01774 -0.0750 0.0737 0.7954
5.500 0.9371 0.02904 0.01868 -0.0748 0.0706 0.7984
5.750 0.9646 0.02996 0.01975 -0.0749 0.0670 0.8016
6.000 0.9910 0.03085 0.02069 -0.0749 0.0637 0.8045
6.250 1.0136 0.03185 0.02165 -0.0742 0.0614 0.8070
6.500 1.0387 0.03303 0.02304 -0.0737 0.0591 0.8097
6.750 1.0634 0.03417 0.02436 -0.0733 0.0566 0.8127
7.000 1.0880 0.03522 0.02547 -0.0731 0.0544 0.8158
7.250 1.1135 0.03655 0.02677 -0.0733 0.0526 0.8187
7.500 1.1356 0.03824 0.02884 -0.0724 0.0510 0.8210
7.750 1.1559 0.03988 0.03078 -0.0713 0.0493 0.8234
8.000 1.1754 0.04130 0.03240 -0.0703 0.0476 0.8262
8.250 1.1950 0.04255 0.03372 -0.0695 0.0463 0.8292
8.500 1.2137 0.04434 0.03564 -0.0688 0.0451 0.8325
8.750 1.2252 0.04715 0.03900 -0.0668 0.0440 0.8355
9.000 1.2320 0.04995 0.04226 -0.0642 0.0432 0.8383
9.250 1.2361 0.05281 0.04552 -0.0615 0.0423 0.8413
9.500 1.2385 0.05555 0.04859 -0.0590 0.0416 0.8444
9.750 1.2409 0.05801 0.05130 -0.0567 0.0408 0.8476
10.000 1.2418 0.06020 0.05368 -0.0542 0.0402 0.8505
10.250 1.2373 0.06214 0.05577 -0.0509 0.0397 0.8534
10.500 1.2347 0.06437 0.05814 -0.0484 0.0393 0.8568
10.750 1.2214 0.06779 0.06179 -0.0458 0.0390 0.8600
11.000 1.1919 0.07301 0.06743 -0.0436 0.0388 0.8628
11.250 1.1618 0.07892 0.07366 -0.0431 0.0388 0.8651
11.500 1.1290 0.08589 0.08093 -0.0447 0.0388 0.8671
11.750 1.0949 0.09453 0.08982 -0.0490 0.0390 0.8688
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