NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 200,000 Max Cl/Cd: 43.47 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20712-il-200000.txt Download as CSV file: xf-sc20712-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7356 0.07449 0.06999 -0.0643 1.0000 0.0535
-12.500 -0.7446 0.07031 0.06574 -0.0648 1.0000 0.0526
-12.250 -0.7649 0.06568 0.06105 -0.0652 1.0000 0.0521
-12.000 -0.7907 0.06166 0.05695 -0.0643 1.0000 0.0517
-11.750 -0.8195 0.05865 0.05387 -0.0614 1.0000 0.0514
-11.500 -0.8449 0.05533 0.05043 -0.0591 1.0000 0.0511
-11.250 -0.8633 0.05134 0.04621 -0.0582 1.0000 0.0507
-11.000 -0.8743 0.04723 0.04179 -0.0572 1.0000 0.0505
-10.750 -0.8765 0.04324 0.03743 -0.0567 1.0000 0.0506
-10.500 -0.8706 0.03965 0.03344 -0.0565 1.0000 0.0511
-10.250 -0.8584 0.03666 0.03000 -0.0566 1.0000 0.0521
-10.000 -0.8415 0.03419 0.02705 -0.0570 1.0000 0.0533
-9.750 -0.8231 0.03197 0.02481 -0.0568 1.0000 0.0547
-9.500 -0.8024 0.03072 0.02351 -0.0565 1.0000 0.0560
-9.250 -0.7807 0.02935 0.02200 -0.0563 1.0000 0.0575
-9.000 -0.7579 0.02795 0.02038 -0.0563 1.0000 0.0592
-8.750 -0.7334 0.02693 0.01908 -0.0564 1.0000 0.0612
-8.500 -0.7111 0.02530 0.01744 -0.0561 1.0000 0.0634
-8.250 -0.6875 0.02450 0.01665 -0.0560 1.0000 0.0657
-8.000 -0.6627 0.02369 0.01575 -0.0559 1.0000 0.0681
-7.750 -0.6368 0.02308 0.01498 -0.0560 1.0000 0.0708
-7.500 -0.6121 0.02192 0.01386 -0.0559 1.0000 0.0740
-7.250 -0.5865 0.02131 0.01328 -0.0560 1.0000 0.0773
-7.000 -0.5601 0.02077 0.01268 -0.0561 1.0000 0.0810
-6.750 -0.5335 0.01995 0.01190 -0.0564 1.0000 0.0854
-6.500 -0.5062 0.01943 0.01143 -0.0569 1.0000 0.0905
-6.250 -0.4782 0.01901 0.01095 -0.0573 1.0000 0.0959
-6.000 -0.4480 0.01829 0.01037 -0.0586 1.0000 0.1041
-5.750 -0.4167 0.01773 0.00985 -0.0600 1.0000 0.1133
-5.500 -0.3854 0.01734 0.00950 -0.0614 1.0000 0.1251
-5.250 -0.3490 0.01668 0.00904 -0.0642 1.0000 0.1458
-5.000 -0.3055 0.01578 0.00853 -0.0688 1.0000 0.2048
-4.750 -0.2381 0.01401 0.00850 -0.0792 1.0000 0.5359
-4.500 -0.2161 0.01447 0.00908 -0.0778 1.0000 0.5916
-4.250 -0.1936 0.01494 0.00953 -0.0766 1.0000 0.6187
-4.000 -0.1720 0.01543 0.01000 -0.0752 1.0000 0.6362
-3.750 -0.1519 0.01595 0.01051 -0.0735 1.0000 0.6496
-3.500 -0.1359 0.01654 0.01114 -0.0707 1.0000 0.6587
-3.250 -0.1131 0.01700 0.01156 -0.0698 1.0000 0.6704
-3.000 -0.0994 0.01762 0.01223 -0.0665 1.0000 0.6766
-2.750 -0.0691 0.01812 0.01269 -0.0669 0.9976 0.6878
-2.500 -0.0432 0.01897 0.01361 -0.0653 0.9937 0.6956
-2.250 -0.0161 0.01958 0.01424 -0.0645 0.9887 0.7069
-2.000 0.0080 0.02030 0.01500 -0.0626 0.9843 0.7152
-1.750 0.0381 0.02080 0.01551 -0.0626 0.9806 0.7249
-1.500 0.0612 0.02115 0.01589 -0.0610 0.9749 0.7308
-1.250 0.1057 0.02125 0.01596 -0.0651 0.9718 0.7394
-1.000 0.1322 0.02144 0.01620 -0.0641 0.9661 0.7428
-0.750 0.1664 0.02149 0.01628 -0.0648 0.9588 0.7480
-0.500 0.2171 0.02124 0.01602 -0.0695 0.9503 0.7546
-0.250 0.2744 0.02052 0.01533 -0.0744 0.9410 0.7574
0.000 0.3114 0.01997 0.01483 -0.0753 0.9291 0.7596
0.250 0.3589 0.01922 0.01413 -0.0781 0.9193 0.7620
0.500 0.4130 0.01829 0.01326 -0.0822 0.9111 0.7646
0.750 0.4568 0.01759 0.01262 -0.0848 0.9011 0.7674
1.000 0.5113 0.01662 0.01171 -0.0893 0.8915 0.7709
1.250 0.5473 0.01596 0.01111 -0.0901 0.8739 0.7735
1.500 0.5765 0.01541 0.01060 -0.0892 0.8489 0.7755
1.750 0.6076 0.01493 0.01012 -0.0886 0.8078 0.7780
2.000 0.6408 0.01474 0.00948 -0.0883 0.6840 0.7804
2.250 0.6501 0.01630 0.00964 -0.0844 0.4323 0.7830
2.500 0.6650 0.01788 0.01020 -0.0829 0.2490 0.7858
2.750 0.6899 0.01893 0.01071 -0.0831 0.1699 0.7888
3.000 0.7094 0.01951 0.01112 -0.0815 0.1424 0.7908
3.250 0.7312 0.02012 0.01160 -0.0803 0.1253 0.7930
3.500 0.7561 0.02064 0.01209 -0.0799 0.1128 0.7953
3.750 0.7820 0.02127 0.01269 -0.0797 0.1030 0.7980
4.000 0.8088 0.02215 0.01342 -0.0800 0.0948 0.8011
4.250 0.8407 0.02268 0.01401 -0.0811 0.0887 0.8041
4.500 0.8634 0.02331 0.01457 -0.0801 0.0836 0.8058
4.750 0.8882 0.02407 0.01538 -0.0795 0.0794 0.8077
5.000 0.9144 0.02471 0.01606 -0.0791 0.0756 0.8100
5.250 0.9415 0.02563 0.01689 -0.0793 0.0721 0.8124
5.500 0.9705 0.02663 0.01800 -0.0797 0.0689 0.8150
5.750 1.0009 0.02753 0.01899 -0.0804 0.0660 0.8178
6.000 1.0286 0.02838 0.01983 -0.0806 0.0634 0.8203
6.250 1.0536 0.02997 0.02142 -0.0802 0.0609 0.8226
6.500 1.0772 0.03078 0.02249 -0.0792 0.0589 0.8253
6.750 1.1028 0.03201 0.02391 -0.0789 0.0570 0.8281
7.000 1.1292 0.03324 0.02524 -0.0789 0.0553 0.8309
7.250 1.1569 0.03470 0.02669 -0.0795 0.0536 0.8338
7.500 1.1774 0.03690 0.02918 -0.0785 0.0521 0.8364
7.750 1.1938 0.03859 0.03129 -0.0764 0.0508 0.8390
8.000 1.2099 0.04091 0.03398 -0.0746 0.0497 0.8420
8.250 1.2244 0.04361 0.03704 -0.0728 0.0490 0.8452
8.500 1.2362 0.04676 0.04057 -0.0709 0.0484 0.8482
8.750 1.2404 0.05058 0.04484 -0.0681 0.0482 0.8506
9.000 1.2344 0.05510 0.04987 -0.0641 0.0484 0.8527
9.250 1.2189 0.06038 0.05565 -0.0596 0.0488 0.8548
9.500 1.1927 0.06618 0.06190 -0.0547 0.0497 0.8569
9.750 1.1637 0.07075 0.06676 -0.0499 0.0503 0.8594
10.000 1.1377 0.07565 0.07189 -0.0470 0.0509 0.8617
10.250 1.1141 0.08082 0.07724 -0.0458 0.0515 0.8638
10.500 1.0948 0.08587 0.08242 -0.0456 0.0519 0.8657
10.750 1.0845 0.09067 0.08729 -0.0459 0.0523 0.8677
11.000 0.9436 0.08985 0.08659 -0.0308 0.0526 0.8621
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Polar data table (+)
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