NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 500,000 Max Cl/Cd: 64.91 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20610-il-500000.txt Download as CSV file: xf-sc20610-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7071 0.09426 0.09166 -0.0313 1.0000 0.0239
-12.750 -0.8095 0.06383 0.06092 -0.0530 1.0000 0.0223
-12.500 -0.8484 0.05514 0.05200 -0.0584 1.0000 0.0220
-12.250 -0.8824 0.04889 0.04551 -0.0600 1.0000 0.0218
-12.000 -0.9133 0.04464 0.04106 -0.0583 1.0000 0.0217
-11.750 -0.9381 0.04079 0.03696 -0.0563 1.0000 0.0216
-11.500 -0.9485 0.03680 0.03264 -0.0557 1.0000 0.0216
-11.250 -0.9480 0.03354 0.02905 -0.0548 1.0000 0.0217
-11.000 -0.9400 0.03088 0.02609 -0.0541 1.0000 0.0219
-10.750 -0.9271 0.02863 0.02357 -0.0536 1.0000 0.0222
-10.500 -0.9110 0.02673 0.02143 -0.0531 1.0000 0.0225
-10.250 -0.8924 0.02515 0.01965 -0.0527 1.0000 0.0228
-10.000 -0.8721 0.02393 0.01824 -0.0524 1.0000 0.0232
-9.750 -0.8515 0.02245 0.01656 -0.0521 1.0000 0.0237
-9.500 -0.8306 0.02090 0.01494 -0.0519 1.0000 0.0244
-9.250 -0.8078 0.02005 0.01405 -0.0517 1.0000 0.0250
-9.000 -0.7844 0.01929 0.01324 -0.0515 1.0000 0.0256
-8.750 -0.7604 0.01854 0.01242 -0.0514 1.0000 0.0263
-8.500 -0.7357 0.01783 0.01163 -0.0514 1.0000 0.0271
-8.250 -0.7106 0.01719 0.01092 -0.0514 1.0000 0.0280
-8.000 -0.6846 0.01643 0.01007 -0.0516 1.0000 0.0289
-7.750 -0.6575 0.01557 0.00922 -0.0523 1.0000 0.0305
-7.500 -0.6308 0.01516 0.00881 -0.0526 1.0000 0.0322
-7.250 -0.6038 0.01484 0.00845 -0.0529 1.0000 0.0341
-7.000 -0.5738 0.01415 0.00775 -0.0540 1.0000 0.0370
-6.750 -0.5457 0.01386 0.00747 -0.0545 1.0000 0.0399
-6.500 -0.5159 0.01342 0.00700 -0.0554 1.0000 0.0434
-6.250 -0.4866 0.01310 0.00671 -0.0562 1.0000 0.0473
-6.000 -0.4588 0.01295 0.00653 -0.0566 1.0000 0.0506
-5.750 -0.4242 0.01248 0.00611 -0.0585 0.9995 0.0567
-5.500 -0.3897 0.01233 0.00592 -0.0602 0.9984 0.0612
-5.250 -0.3535 0.01191 0.00556 -0.0625 0.9977 0.0697
-5.000 -0.3176 0.01161 0.00531 -0.0646 0.9968 0.0793
-4.750 -0.2814 0.01133 0.00508 -0.0667 0.9959 0.0925
-4.500 -0.2443 0.01098 0.00486 -0.0691 0.9952 0.1177
-4.250 -0.2054 0.01040 0.00464 -0.0723 0.9951 0.1943
-4.000 -0.1631 0.00945 0.00436 -0.0767 0.9958 0.3536
-3.750 -0.1203 0.00860 0.00429 -0.0809 0.9970 0.5501
-3.500 -0.0850 0.00860 0.00442 -0.0825 0.9958 0.6099
-3.250 -0.0496 0.00867 0.00452 -0.0841 0.9946 0.6341
-3.000 -0.0158 0.00875 0.00461 -0.0853 0.9927 0.6506
-2.750 0.0169 0.00882 0.00469 -0.0863 0.9902 0.6630
-2.500 0.0515 0.00891 0.00474 -0.0877 0.9880 0.6737
-2.250 0.0877 0.00896 0.00485 -0.0893 0.9857 0.6820
-2.000 0.1277 0.00904 0.00496 -0.0915 0.9835 0.6941
-1.750 0.1628 0.00895 0.00490 -0.0926 0.9765 0.7021
-1.500 0.2062 0.00879 0.00476 -0.0956 0.9731 0.7083
-1.250 0.2451 0.00866 0.00468 -0.0974 0.9685 0.7132
-1.000 0.2885 0.00839 0.00443 -0.1002 0.9622 0.7192
-0.750 0.3288 0.00806 0.00412 -0.1022 0.9533 0.7234
-0.500 0.3629 0.00787 0.00397 -0.1029 0.9437 0.7262
-0.250 0.3912 0.00782 0.00395 -0.1025 0.9310 0.7291
0.000 0.4205 0.00776 0.00390 -0.1024 0.9157 0.7322
0.250 0.4495 0.00772 0.00384 -0.1022 0.8954 0.7354
0.500 0.4785 0.00771 0.00375 -0.1020 0.8668 0.7381
0.750 0.5050 0.00778 0.00366 -0.1012 0.8111 0.7399
1.000 0.5238 0.00853 0.00369 -0.0987 0.6434 0.7415
1.250 0.5409 0.00984 0.00405 -0.0967 0.4337 0.7433
1.500 0.5627 0.01083 0.00438 -0.0958 0.2810 0.7452
1.750 0.5867 0.01162 0.00467 -0.0953 0.1726 0.7474
2.000 0.6126 0.01218 0.00494 -0.0950 0.1162 0.7498
2.250 0.6401 0.01255 0.00519 -0.0950 0.0927 0.7523
2.500 0.6681 0.01289 0.00545 -0.0951 0.0795 0.7548
2.750 0.6949 0.01324 0.00575 -0.0949 0.0696 0.7566
3.000 0.7219 0.01347 0.00599 -0.0946 0.0638 0.7582
3.250 0.7479 0.01390 0.00642 -0.0942 0.0578 0.7599
3.500 0.7751 0.01414 0.00668 -0.0940 0.0535 0.7619
3.750 0.8007 0.01468 0.00718 -0.0935 0.0482 0.7642
4.000 0.8283 0.01490 0.00744 -0.0934 0.0450 0.7669
4.250 0.8553 0.01530 0.00781 -0.0932 0.0413 0.7696
4.500 0.8817 0.01582 0.00835 -0.0930 0.0382 0.7718
4.750 0.9077 0.01616 0.00872 -0.0925 0.0355 0.7734
5.000 0.9309 0.01702 0.00959 -0.0916 0.0329 0.7752
5.250 0.9571 0.01738 0.01002 -0.0912 0.0314 0.7771
5.500 0.9829 0.01780 0.01048 -0.0907 0.0297 0.7793
5.750 1.0084 0.01832 0.01100 -0.0903 0.0284 0.7817
6.000 1.0309 0.01960 0.01231 -0.0894 0.0270 0.7842
6.250 1.0570 0.02020 0.01300 -0.0890 0.0264 0.7870
6.500 1.0812 0.02092 0.01383 -0.0882 0.0257 0.7890
6.750 1.1050 0.02173 0.01475 -0.0874 0.0250 0.7909
7.000 1.1288 0.02258 0.01570 -0.0866 0.0244 0.7931
7.250 1.1525 0.02343 0.01664 -0.0859 0.0238 0.7956
7.500 1.1760 0.02438 0.01766 -0.0852 0.0233 0.7982
7.750 1.1988 0.02555 0.01890 -0.0845 0.0228 0.8009
8.000 1.2174 0.02816 0.02172 -0.0832 0.0221 0.8031
8.250 1.2384 0.02908 0.02286 -0.0820 0.0218 0.8051
8.500 1.2572 0.03064 0.02468 -0.0805 0.0215 0.8073
8.750 1.2737 0.03260 0.02694 -0.0788 0.0212 0.8097
9.000 1.2872 0.03501 0.02969 -0.0767 0.0210 0.8123
9.250 1.2962 0.03800 0.03306 -0.0742 0.0208 0.8149
9.500 1.2981 0.04186 0.03735 -0.0710 0.0206 0.8173
9.750 1.2869 0.04699 0.04300 -0.0664 0.0207 0.8193
10.000 1.2608 0.05320 0.04973 -0.0609 0.0208 0.8212
10.250 1.2266 0.05833 0.05522 -0.0547 0.0211 0.8235
10.500 1.1914 0.06361 0.06077 -0.0504 0.0212 0.8260
10.750 1.1566 0.06970 0.06710 -0.0490 0.0214 0.8283
11.000 1.1235 0.07695 0.07453 -0.0511 0.0216 0.8305
11.250 1.0867 0.08794 0.08571 -0.0592 0.0218 0.8322
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