NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.52 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20610-il-1000000-n5.txt Download as CSV file: xf-sc20610-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0610 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0838 0.09460 0.09202 -0.0298 1.0000 0.0103
-17.500 -1.1531 0.07636 0.07349 -0.0406 1.0000 0.0101
-17.250 -1.1864 0.06566 0.06258 -0.0475 1.0000 0.0101
-17.000 -1.2071 0.05807 0.05481 -0.0525 1.0000 0.0101
-16.750 -1.2202 0.05247 0.04907 -0.0558 1.0000 0.0101
-16.500 -1.2295 0.04795 0.04441 -0.0581 1.0000 0.0102
-16.250 -1.2338 0.04438 0.04073 -0.0597 1.0000 0.0103
-16.000 -1.2357 0.04130 0.03755 -0.0607 1.0000 0.0103
-15.750 -1.2355 0.03861 0.03475 -0.0614 1.0000 0.0104
-15.500 -1.2330 0.03629 0.03234 -0.0618 1.0000 0.0105
-15.250 -1.2293 0.03420 0.03015 -0.0619 1.0000 0.0106
-15.000 -1.2248 0.03229 0.02815 -0.0618 1.0000 0.0107
-14.750 -1.2200 0.03057 0.02633 -0.0613 1.0000 0.0107
-14.500 -1.2157 0.02905 0.02472 -0.0603 1.0000 0.0108
-14.250 -1.2145 0.02773 0.02333 -0.0583 1.0000 0.0109
-14.000 -1.2109 0.02649 0.02201 -0.0565 1.0000 0.0110
-13.750 -1.2007 0.02528 0.02071 -0.0559 1.0000 0.0111
-13.500 -1.1875 0.02415 0.01950 -0.0555 1.0000 0.0112
-13.250 -1.1718 0.02311 0.01837 -0.0554 1.0000 0.0113
-13.000 -1.1542 0.02214 0.01731 -0.0553 1.0000 0.0114
-12.750 -1.1355 0.02127 0.01637 -0.0551 1.0000 0.0116
-12.500 -1.1159 0.02048 0.01550 -0.0548 1.0000 0.0117
-12.250 -1.0954 0.01975 0.01469 -0.0546 1.0000 0.0118
-12.000 -1.0666 0.01899 0.01386 -0.0560 0.9994 0.0120
-11.750 -1.0374 0.01829 0.01308 -0.0574 0.9987 0.0121
-11.500 -1.0079 0.01765 0.01237 -0.0587 0.9980 0.0122
-11.250 -0.9786 0.01680 0.01145 -0.0602 0.9972 0.0125
-11.000 -0.9486 0.01610 0.01070 -0.0616 0.9965 0.0128
-10.750 -0.9180 0.01552 0.01008 -0.0630 0.9958 0.0132
-10.500 -0.8869 0.01500 0.00953 -0.0644 0.9952 0.0136
-10.250 -0.8555 0.01453 0.00903 -0.0659 0.9946 0.0140
-10.000 -0.8238 0.01406 0.00852 -0.0673 0.9941 0.0143
-9.750 -0.7935 0.01362 0.00804 -0.0684 0.9931 0.0147
-9.500 -0.7631 0.01320 0.00759 -0.0695 0.9920 0.0150
-9.250 -0.7322 0.01282 0.00717 -0.0706 0.9909 0.0154
-9.000 -0.7008 0.01238 0.00670 -0.0719 0.9898 0.0160
-8.750 -0.6692 0.01199 0.00631 -0.0732 0.9888 0.0168
-8.500 -0.6373 0.01164 0.00596 -0.0745 0.9879 0.0177
-8.250 -0.6051 0.01132 0.00562 -0.0758 0.9871 0.0187
-8.000 -0.5727 0.01100 0.00529 -0.0771 0.9863 0.0199
-7.750 -0.5402 0.01069 0.00500 -0.0785 0.9856 0.0217
-7.500 -0.5076 0.01043 0.00473 -0.0798 0.9850 0.0234
-7.250 -0.4746 0.01014 0.00447 -0.0813 0.9845 0.0260
-7.000 -0.4415 0.00990 0.00423 -0.0827 0.9840 0.0284
-6.750 -0.4081 0.00964 0.00399 -0.0842 0.9835 0.0312
-6.500 -0.3781 0.00943 0.00379 -0.0849 0.9813 0.0338
-6.250 -0.3466 0.00921 0.00359 -0.0859 0.9796 0.0365
-6.000 -0.3147 0.00900 0.00340 -0.0870 0.9782 0.0398
-5.750 -0.2826 0.00881 0.00322 -0.0881 0.9768 0.0428
-5.500 -0.2500 0.00860 0.00305 -0.0893 0.9755 0.0477
-5.250 -0.2175 0.00841 0.00289 -0.0905 0.9743 0.0528
-5.000 -0.1846 0.00821 0.00273 -0.0917 0.9732 0.0601
-4.750 -0.1514 0.00801 0.00258 -0.0931 0.9721 0.0681
-4.500 -0.1191 0.00782 0.00244 -0.0942 0.9704 0.0782
-4.250 -0.0883 0.00763 0.00232 -0.0950 0.9675 0.0920
-4.000 -0.0567 0.00744 0.00220 -0.0959 0.9650 0.1096
-3.750 -0.0240 0.00718 0.00207 -0.0972 0.9626 0.1405
-3.500 0.0097 0.00690 0.00194 -0.0987 0.9599 0.1799
-3.250 0.0436 0.00657 0.00181 -0.1003 0.9563 0.2326
-3.000 0.0766 0.00620 0.00167 -0.1017 0.9497 0.3022
-2.750 0.1110 0.00577 0.00151 -0.1035 0.9397 0.3876
-2.500 0.1449 0.00534 0.00136 -0.1051 0.9282 0.4830
-2.250 0.1772 0.00509 0.00133 -0.1062 0.9185 0.5550
-2.000 0.2067 0.00504 0.00133 -0.1064 0.9032 0.5938
-1.750 0.2354 0.00506 0.00134 -0.1063 0.8835 0.6172
-1.500 0.2632 0.00516 0.00132 -0.1060 0.8521 0.6254
-1.250 0.2891 0.00541 0.00133 -0.1053 0.7837 0.6332
-1.000 0.3136 0.00593 0.00140 -0.1045 0.6752 0.6405
-0.750 0.3374 0.00672 0.00159 -0.1038 0.5221 0.6458
-0.500 0.3628 0.00737 0.00177 -0.1034 0.3954 0.6518
-0.250 0.3896 0.00784 0.00190 -0.1033 0.3086 0.6576
0.000 0.4169 0.00820 0.00204 -0.1033 0.2438 0.6616
0.250 0.4442 0.00855 0.00217 -0.1032 0.1879 0.6660
0.500 0.4719 0.00886 0.00230 -0.1032 0.1446 0.6701
0.750 0.5000 0.00910 0.00242 -0.1032 0.1173 0.6733
1.000 0.5280 0.00931 0.00255 -0.1032 0.0965 0.6759
1.250 0.5561 0.00950 0.00269 -0.1032 0.0811 0.6780
1.500 0.5842 0.00969 0.00283 -0.1032 0.0695 0.6804
1.750 0.6123 0.00988 0.00297 -0.1032 0.0610 0.6829
2.000 0.6405 0.01006 0.00312 -0.1032 0.0547 0.6853
2.250 0.6684 0.01026 0.00328 -0.1031 0.0485 0.6874
2.500 0.6966 0.01043 0.00343 -0.1031 0.0449 0.6892
2.750 0.7244 0.01063 0.00360 -0.1031 0.0404 0.6911
3.000 0.7523 0.01081 0.00378 -0.1030 0.0378 0.6933
3.250 0.7800 0.01101 0.00398 -0.1029 0.0348 0.6958
3.500 0.8076 0.01122 0.00418 -0.1028 0.0322 0.6982
3.750 0.8352 0.01143 0.00438 -0.1027 0.0299 0.7005
4.000 0.8626 0.01168 0.00461 -0.1025 0.0272 0.7026
4.250 0.8900 0.01190 0.00484 -0.1023 0.0255 0.7045
4.500 0.9172 0.01216 0.00508 -0.1022 0.0233 0.7064
4.750 0.9443 0.01242 0.00535 -0.1019 0.0214 0.7083
5.000 0.9712 0.01268 0.00562 -0.1017 0.0198 0.7103
5.250 0.9979 0.01299 0.00593 -0.1014 0.0184 0.7125
5.500 1.0245 0.01328 0.00625 -0.1011 0.0175 0.7148
5.750 1.0511 0.01358 0.00658 -0.1008 0.0168 0.7173
6.000 1.0775 0.01390 0.00691 -0.1005 0.0161 0.7195
6.250 1.1037 0.01425 0.00727 -0.1001 0.0155 0.7214
6.500 1.1295 0.01464 0.00769 -0.0997 0.0148 0.7234
6.750 1.1550 0.01506 0.00815 -0.0992 0.0144 0.7255
7.000 1.1808 0.01542 0.00856 -0.0988 0.0141 0.7276
7.250 1.2063 0.01581 0.00900 -0.0983 0.0139 0.7298
7.500 1.2315 0.01623 0.00947 -0.0977 0.0136 0.7321
7.750 1.2565 0.01667 0.00995 -0.0972 0.0133 0.7344
8.000 1.2813 0.01712 0.01045 -0.0966 0.0131 0.7366
8.250 1.3058 0.01758 0.01096 -0.0960 0.0128 0.7385
8.500 1.3301 0.01806 0.01149 -0.0953 0.0125 0.7406
8.750 1.3541 0.01855 0.01204 -0.0947 0.0123 0.7427
9.000 1.3775 0.01912 0.01265 -0.0939 0.0120 0.7449
9.250 1.4001 0.01977 0.01337 -0.0930 0.0117 0.7472
9.500 1.4216 0.02055 0.01425 -0.0919 0.0115 0.7496
9.750 1.4433 0.02126 0.01503 -0.0909 0.0113 0.7518
10.000 1.4653 0.02188 0.01573 -0.0899 0.0112 0.7540
10.250 1.4868 0.02254 0.01647 -0.0888 0.0111 0.7560
10.500 1.5077 0.02323 0.01726 -0.0877 0.0110 0.7581
10.750 1.5279 0.02396 0.01810 -0.0865 0.0109 0.7603
11.000 1.5472 0.02475 0.01899 -0.0851 0.0108 0.7626
11.250 1.5658 0.02558 0.01992 -0.0837 0.0107 0.7651
11.500 1.5836 0.02644 0.02088 -0.0821 0.0106 0.7677
11.750 1.6003 0.02736 0.02190 -0.0804 0.0105 0.7701
12.000 1.6160 0.02830 0.02296 -0.0786 0.0104 0.7722
12.250 1.6302 0.02931 0.02409 -0.0766 0.0103 0.7744
12.500 1.6429 0.03037 0.02527 -0.0744 0.0102 0.7766
12.750 1.6536 0.03144 0.02646 -0.0719 0.0101 0.7790
13.000 1.6605 0.03261 0.02775 -0.0689 0.0100 0.7815
13.250 1.6628 0.03378 0.02904 -0.0651 0.0099 0.7841
13.500 1.6657 0.03514 0.03051 -0.0617 0.0099 0.7865
13.750 1.6684 0.03659 0.03208 -0.0586 0.0098 0.7887
14.000 1.6705 0.03815 0.03376 -0.0557 0.0097 0.7912
14.250 1.6708 0.03994 0.03568 -0.0530 0.0096 0.7938
14.500 1.6701 0.04190 0.03777 -0.0505 0.0095 0.7963
14.750 1.6673 0.04420 0.04020 -0.0482 0.0095 0.7987
15.000 1.6619 0.04690 0.04302 -0.0463 0.0094 0.8008
15.250 1.6533 0.05016 0.04642 -0.0449 0.0094 0.8025
15.500 1.6424 0.05400 0.05042 -0.0442 0.0093 0.8044
15.750 1.6267 0.05890 0.05550 -0.0447 0.0093 0.8062
16.000 1.6059 0.06535 0.06214 -0.0469 0.0093 0.8079
16.250 1.5745 0.07502 0.07205 -0.0525 0.0093 0.8094
16.500 1.4951 0.09826 0.09571 -0.0686 0.0094 0.8089
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