NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 500,000 Max Cl/Cd: 62.65 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20610-il-500000-n5.txt Download as CSV file: xf-sc20610-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9850 0.07857 0.07535 -0.0396 1.0000 0.0133
-15.500 -1.0245 0.06591 0.06240 -0.0485 1.0000 0.0132
-15.250 -1.0453 0.05840 0.05469 -0.0535 1.0000 0.0132
-15.000 -1.0595 0.05280 0.04891 -0.0568 1.0000 0.0133
-14.750 -1.0691 0.04839 0.04434 -0.0589 1.0000 0.0133
-14.500 -1.0753 0.04474 0.04054 -0.0603 1.0000 0.0134
-14.250 -1.0789 0.04163 0.03728 -0.0610 1.0000 0.0135
-14.000 -1.0806 0.03893 0.03444 -0.0613 1.0000 0.0136
-13.750 -1.0808 0.03659 0.03196 -0.0611 1.0000 0.0137
-13.500 -1.0805 0.03455 0.02980 -0.0603 1.0000 0.0138
-13.250 -1.0811 0.03280 0.02793 -0.0588 1.0000 0.0139
-13.000 -1.0837 0.03129 0.02631 -0.0564 1.0000 0.0140
-12.750 -1.0780 0.02974 0.02464 -0.0554 1.0000 0.0142
-12.500 -1.0686 0.02829 0.02307 -0.0548 1.0000 0.0144
-12.250 -1.0562 0.02694 0.02158 -0.0544 1.0000 0.0145
-12.000 -1.0414 0.02571 0.02021 -0.0541 1.0000 0.0148
-11.750 -1.0250 0.02459 0.01897 -0.0537 1.0000 0.0150
-11.500 -1.0072 0.02358 0.01784 -0.0532 1.0000 0.0152
-11.250 -0.9880 0.02270 0.01684 -0.0528 1.0000 0.0154
-11.000 -0.9688 0.02162 0.01569 -0.0526 1.0000 0.0157
-10.750 -0.9481 0.02074 0.01475 -0.0525 1.0000 0.0161
-10.500 -0.9261 0.02001 0.01397 -0.0524 1.0000 0.0165
-10.250 -0.9035 0.01933 0.01322 -0.0523 1.0000 0.0168
-10.000 -0.8753 0.01862 0.01244 -0.0533 0.9994 0.0173
-9.750 -0.8448 0.01792 0.01167 -0.0547 0.9985 0.0178
-9.500 -0.8139 0.01726 0.01094 -0.0562 0.9975 0.0183
-9.250 -0.7825 0.01665 0.01025 -0.0576 0.9965 0.0188
-9.000 -0.7509 0.01600 0.00955 -0.0592 0.9956 0.0195
-8.750 -0.7191 0.01543 0.00896 -0.0607 0.9948 0.0204
-8.500 -0.6869 0.01496 0.00846 -0.0623 0.9941 0.0214
-8.250 -0.6557 0.01451 0.00796 -0.0635 0.9930 0.0226
-8.000 -0.6242 0.01406 0.00748 -0.0648 0.9916 0.0240
-7.750 -0.5926 0.01365 0.00708 -0.0661 0.9904 0.0259
-7.500 -0.5607 0.01330 0.00670 -0.0674 0.9891 0.0279
-7.250 -0.5284 0.01291 0.00631 -0.0688 0.9880 0.0302
-7.000 -0.4958 0.01259 0.00599 -0.0702 0.9870 0.0328
-6.750 -0.4628 0.01229 0.00567 -0.0716 0.9860 0.0354
-6.500 -0.4294 0.01197 0.00537 -0.0732 0.9851 0.0387
-6.250 -0.3959 0.01173 0.00511 -0.0747 0.9843 0.0420
-6.000 -0.3620 0.01142 0.00485 -0.0764 0.9836 0.0467
-5.750 -0.3313 0.01121 0.00463 -0.0772 0.9818 0.0507
-5.500 -0.2996 0.01093 0.00439 -0.0784 0.9800 0.0568
-5.250 -0.2674 0.01070 0.00418 -0.0796 0.9784 0.0629
-5.000 -0.2343 0.01045 0.00397 -0.0810 0.9771 0.0712
-4.750 -0.2005 0.01020 0.00378 -0.0825 0.9759 0.0822
-4.500 -0.1664 0.00995 0.00360 -0.0841 0.9748 0.0979
-4.250 -0.1316 0.00965 0.00341 -0.0860 0.9740 0.1217
-4.000 -0.0963 0.00930 0.00324 -0.0880 0.9733 0.1623
-3.750 -0.0600 0.00887 0.00306 -0.0904 0.9728 0.2233
-3.500 -0.0221 0.00831 0.00285 -0.0933 0.9724 0.3150
-3.250 0.0175 0.00763 0.00263 -0.0966 0.9721 0.4380
-3.000 0.0556 0.00717 0.00260 -0.0993 0.9717 0.5512
-2.750 0.0867 0.00710 0.00264 -0.1000 0.9689 0.5913
-2.500 0.1180 0.00708 0.00266 -0.1007 0.9658 0.6126
-2.250 0.1512 0.00703 0.00268 -0.1016 0.9626 0.6351
-2.000 0.1882 0.00692 0.00259 -0.1033 0.9580 0.6482
-1.750 0.2197 0.00684 0.00250 -0.1038 0.9476 0.6579
-1.500 0.2516 0.00678 0.00248 -0.1043 0.9382 0.6649
-1.250 0.2830 0.00675 0.00241 -0.1047 0.9246 0.6727
-1.000 0.3122 0.00672 0.00237 -0.1045 0.9014 0.6783
-0.750 0.3402 0.00677 0.00233 -0.1040 0.8678 0.6828
-0.500 0.3675 0.00689 0.00229 -0.1035 0.8215 0.6872
-0.250 0.3924 0.00723 0.00228 -0.1024 0.7373 0.6907
0.000 0.4120 0.00818 0.00248 -0.1006 0.5679 0.6932
0.250 0.4348 0.00903 0.00272 -0.0997 0.4229 0.6952
0.500 0.4598 0.00967 0.00293 -0.0993 0.3178 0.6975
0.750 0.4860 0.01019 0.00311 -0.0991 0.2370 0.6999
1.000 0.5126 0.01064 0.00329 -0.0990 0.1743 0.7025
1.250 0.5400 0.01101 0.00346 -0.0990 0.1311 0.7050
1.500 0.5673 0.01129 0.00365 -0.0989 0.1071 0.7069
1.750 0.5946 0.01156 0.00384 -0.0987 0.0877 0.7088
2.000 0.6222 0.01180 0.00404 -0.0986 0.0758 0.7106
2.250 0.6498 0.01205 0.00424 -0.0985 0.0669 0.7126
2.500 0.6772 0.01232 0.00447 -0.0984 0.0591 0.7147
2.750 0.7049 0.01254 0.00469 -0.0984 0.0538 0.7173
3.000 0.7323 0.01283 0.00493 -0.0982 0.0484 0.7199
3.250 0.7602 0.01305 0.00517 -0.0982 0.0451 0.7221
3.500 0.7871 0.01332 0.00542 -0.0980 0.0410 0.7238
3.750 0.8141 0.01358 0.00571 -0.0977 0.0379 0.7255
4.000 0.8410 0.01386 0.00599 -0.0975 0.0349 0.7274
4.250 0.8677 0.01419 0.00632 -0.0972 0.0323 0.7294
4.500 0.8946 0.01448 0.00664 -0.0970 0.0300 0.7315
4.750 0.9211 0.01483 0.00698 -0.0967 0.0278 0.7337
5.000 0.9476 0.01520 0.00738 -0.0964 0.0261 0.7361
5.250 0.9741 0.01557 0.00777 -0.0961 0.0245 0.7386
5.500 0.9999 0.01596 0.00818 -0.0957 0.0230 0.7405
5.750 1.0253 0.01641 0.00868 -0.0952 0.0218 0.7424
6.000 1.0509 0.01682 0.00915 -0.0947 0.0207 0.7443
6.250 1.0763 0.01726 0.00963 -0.0942 0.0198 0.7465
6.500 1.1015 0.01773 0.01014 -0.0937 0.0191 0.7487
6.750 1.1260 0.01830 0.01074 -0.0931 0.0184 0.7511
7.000 1.1502 0.01893 0.01142 -0.0924 0.0179 0.7534
7.250 1.1747 0.01950 0.01207 -0.0918 0.0174 0.7557
7.500 1.1983 0.02011 0.01277 -0.0911 0.0170 0.7575
7.750 1.2217 0.02075 0.01351 -0.0902 0.0166 0.7594
8.000 1.2448 0.02141 0.01427 -0.0894 0.0163 0.7616
8.250 1.2677 0.02210 0.01504 -0.0886 0.0159 0.7639
8.500 1.2902 0.02282 0.01584 -0.0877 0.0156 0.7663
8.750 1.3122 0.02357 0.01668 -0.0867 0.0153 0.7688
9.000 1.3336 0.02438 0.01755 -0.0858 0.0150 0.7712
9.250 1.3532 0.02535 0.01862 -0.0845 0.0147 0.7731
9.500 1.3718 0.02645 0.01984 -0.0831 0.0144 0.7751
9.750 1.3913 0.02737 0.02093 -0.0818 0.0142 0.7774
10.000 1.4095 0.02841 0.02213 -0.0803 0.0140 0.7799
10.250 1.4266 0.02955 0.02343 -0.0787 0.0138 0.7825
10.500 1.4425 0.03078 0.02482 -0.0770 0.0136 0.7851
10.750 1.4570 0.03208 0.02629 -0.0751 0.0134 0.7874
11.000 1.4694 0.03345 0.02785 -0.0730 0.0133 0.7894
11.250 1.4799 0.03491 0.02950 -0.0706 0.0131 0.7916
11.500 1.4882 0.03643 0.03121 -0.0680 0.0130 0.7941
11.750 1.4926 0.03803 0.03299 -0.0649 0.0128 0.7969
12.000 1.4913 0.03963 0.03475 -0.0609 0.0127 0.7998
12.250 1.4898 0.04152 0.03681 -0.0575 0.0126 0.8025
12.500 1.4866 0.04361 0.03910 -0.0542 0.0125 0.8046
12.750 1.4818 0.04595 0.04162 -0.0513 0.0124 0.8068
13.000 1.4737 0.04879 0.04466 -0.0487 0.0124 0.8092
13.250 1.4638 0.05202 0.04808 -0.0468 0.0123 0.8117
13.500 1.4504 0.05601 0.05227 -0.0458 0.0123 0.8141
13.750 1.4337 0.06089 0.05737 -0.0460 0.0122 0.8164
14.000 1.4097 0.06774 0.06445 -0.0483 0.0122 0.8182
14.250 1.3745 0.07852 0.07555 -0.0552 0.0123 0.8195
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