NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 200,000 Max Cl/Cd: 44.09 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20710-il-200000.txt Download as CSV file: xf-sc20710-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5937 0.09407 0.09015 -0.0414 1.0000 0.0748
-10.750 -0.6335 0.08606 0.08214 -0.0477 1.0000 0.0750
-10.500 -0.6637 0.08219 0.07828 -0.0476 1.0000 0.0750
-10.250 -0.6925 0.07859 0.07463 -0.0479 1.0000 0.0751
-10.000 -0.7146 0.07511 0.07097 -0.0487 1.0000 0.0753
-9.750 -0.7187 0.06734 0.06331 -0.0487 1.0000 0.0767
-9.500 -0.7046 0.06508 0.06115 -0.0468 1.0000 0.0780
-9.250 -0.7025 0.06229 0.05834 -0.0461 1.0000 0.0792
-9.000 -0.7393 0.03497 0.02853 -0.0560 1.0000 0.0441
-8.750 -0.7175 0.03184 0.02507 -0.0567 1.0000 0.0444
-8.500 -0.6942 0.02952 0.02253 -0.0572 1.0000 0.0451
-8.250 -0.6701 0.02787 0.02074 -0.0575 1.0000 0.0463
-8.000 -0.6451 0.02661 0.01933 -0.0578 1.0000 0.0484
-7.750 -0.6185 0.02514 0.01758 -0.0581 1.0000 0.0505
-7.500 -0.5912 0.02395 0.01610 -0.0584 1.0000 0.0521
-7.250 -0.5654 0.02184 0.01394 -0.0586 1.0000 0.0548
-7.000 -0.5388 0.02099 0.01307 -0.0588 1.0000 0.0579
-6.750 -0.5113 0.02041 0.01236 -0.0590 1.0000 0.0622
-6.500 -0.4832 0.01920 0.01117 -0.0596 1.0000 0.0669
-6.250 -0.4550 0.01863 0.01059 -0.0600 1.0000 0.0721
-6.000 -0.4256 0.01782 0.00977 -0.0607 1.0000 0.0780
-5.750 -0.3962 0.01729 0.00930 -0.0615 1.0000 0.0850
-5.500 -0.3645 0.01659 0.00862 -0.0628 1.0000 0.0929
-5.250 -0.3336 0.01618 0.00821 -0.0639 1.0000 0.1030
-5.000 -0.2963 0.01535 0.00754 -0.0667 1.0000 0.1213
-4.750 -0.2539 0.01441 0.00695 -0.0708 1.0000 0.1752
-4.500 -0.1881 0.01241 0.00688 -0.0809 1.0000 0.5642
-4.250 -0.1652 0.01277 0.00732 -0.0794 1.0000 0.6213
-4.000 -0.1433 0.01319 0.00774 -0.0778 1.0000 0.6504
-3.750 -0.1242 0.01370 0.00826 -0.0755 1.0000 0.6699
-3.500 -0.1061 0.01424 0.00880 -0.0729 1.0000 0.6850
-3.250 -0.0861 0.01470 0.00923 -0.0709 1.0000 0.6974
-3.000 -0.0646 0.01512 0.00963 -0.0693 1.0000 0.7089
-2.750 -0.0508 0.01565 0.01021 -0.0658 1.0000 0.7165
-2.500 -0.0321 0.01614 0.01070 -0.0635 1.0000 0.7286
-2.250 -0.0192 0.01669 0.01129 -0.0597 1.0000 0.7382
-2.000 -0.0047 0.01715 0.01179 -0.0564 1.0000 0.7480
-1.750 0.0198 0.01748 0.01210 -0.0558 1.0000 0.7589
-1.500 0.0327 0.01778 0.01245 -0.0523 1.0000 0.7643
-1.250 0.0609 0.01806 0.01272 -0.0528 1.0000 0.7744
-1.000 0.0753 0.01826 0.01297 -0.0498 1.0000 0.7789
-0.750 0.0984 0.01848 0.01322 -0.0492 1.0000 0.7853
-0.500 0.1297 0.01866 0.01341 -0.0505 0.9992 0.7910
-0.250 0.1723 0.01879 0.01359 -0.0534 0.9935 0.7945
0.000 0.2218 0.01880 0.01364 -0.0578 0.9849 0.7984
0.250 0.2901 0.01838 0.01326 -0.0655 0.9699 0.8018
0.500 0.3535 0.01763 0.01257 -0.0721 0.9528 0.8052
0.750 0.4021 0.01682 0.01186 -0.0752 0.9391 0.8070
1.000 0.4534 0.01591 0.01106 -0.0788 0.9262 0.8091
1.250 0.4997 0.01488 0.01014 -0.0810 0.9057 0.8116
1.500 0.5416 0.01401 0.00935 -0.0825 0.8736 0.8141
1.750 0.5952 0.01350 0.00805 -0.0852 0.6521 0.8161
2.000 0.6033 0.01571 0.00858 -0.0818 0.3349 0.8197
2.250 0.6174 0.01727 0.00912 -0.0797 0.1580 0.8221
2.500 0.6390 0.01800 0.00961 -0.0785 0.1209 0.8244
2.750 0.6633 0.01862 0.01016 -0.0779 0.1044 0.8270
3.000 0.6887 0.01935 0.01081 -0.0776 0.0939 0.8301
3.250 0.7175 0.01998 0.01140 -0.0781 0.0853 0.8335
3.500 0.7444 0.02073 0.01217 -0.0780 0.0787 0.8364
3.750 0.7684 0.02122 0.01264 -0.0772 0.0728 0.8387
4.000 0.7939 0.02220 0.01362 -0.0768 0.0675 0.8411
4.250 0.8215 0.02286 0.01433 -0.0768 0.0627 0.8437
4.500 0.8500 0.02430 0.01571 -0.0773 0.0584 0.8463
4.750 0.8804 0.02521 0.01680 -0.0778 0.0548 0.8490
5.000 0.9079 0.02604 0.01771 -0.0778 0.0514 0.8513
5.250 0.9327 0.02722 0.01892 -0.0772 0.0492 0.8538
5.500 0.9583 0.02966 0.02155 -0.0768 0.0475 0.8566
5.750 0.9838 0.03128 0.02352 -0.0761 0.0465 0.8597
6.000 1.0091 0.03344 0.02607 -0.0756 0.0454 0.8627
6.250 1.0319 0.03561 0.02860 -0.0747 0.0441 0.8656
6.500 1.0500 0.03785 0.03119 -0.0730 0.0431 0.8683
6.750 1.0634 0.04181 0.03570 -0.0706 0.0436 0.8709
7.000 1.0722 0.04674 0.04117 -0.0679 0.0451 0.8735
7.250 1.0802 0.05164 0.04641 -0.0659 0.0466 0.8760
8.250 1.0471 0.08575 0.08213 -0.0560 0.0695 0.8842
8.500 1.0202 0.08876 0.08552 -0.0530 0.0691 0.8869
8.750 0.9823 0.09279 0.08980 -0.0508 0.0687 0.8897
9.000 0.9461 0.09955 0.09675 -0.0537 0.0684 0.8922
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Polar data table (+)
Polar graphs
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