NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il) Reynolds number: 100,000 Max Cl/Cd: 31.92 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20612-il-100000-n5.txt Download as CSV file: xf-sc20612-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0612 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6974 0.09217 0.08596 -0.0448 1.0000 0.0434
-13.000 -0.7531 0.07729 0.07090 -0.0552 1.0000 0.0429
-12.750 -0.7912 0.06875 0.06215 -0.0602 1.0000 0.0427
-12.500 -0.8214 0.06263 0.05581 -0.0625 1.0000 0.0427
-12.250 -0.8472 0.05788 0.05082 -0.0630 1.0000 0.0428
-12.000 -0.8705 0.05418 0.04690 -0.0617 1.0000 0.0430
-11.750 -0.8912 0.05104 0.04353 -0.0596 1.0000 0.0432
-11.500 -0.9045 0.04759 0.03970 -0.0586 1.0000 0.0437
-11.250 -0.8993 0.04571 0.03775 -0.0575 1.0000 0.0444
-11.000 -0.8906 0.04426 0.03625 -0.0565 1.0000 0.0452
-10.750 -0.8819 0.04263 0.03450 -0.0556 1.0000 0.0463
-10.500 -0.8725 0.04076 0.03242 -0.0546 1.0000 0.0476
-10.250 -0.8620 0.03861 0.02996 -0.0538 1.0000 0.0490
-10.000 -0.8492 0.03639 0.02735 -0.0529 1.0000 0.0504
-9.750 -0.8330 0.03479 0.02564 -0.0521 1.0000 0.0516
-9.500 -0.8155 0.03368 0.02452 -0.0513 1.0000 0.0531
-9.250 -0.7973 0.03255 0.02328 -0.0507 1.0000 0.0552
-9.000 -0.7783 0.03125 0.02175 -0.0500 1.0000 0.0576
-8.750 -0.7589 0.02999 0.02037 -0.0492 1.0000 0.0597
-8.500 -0.7390 0.02901 0.01942 -0.0485 1.0000 0.0617
-8.250 -0.7183 0.02811 0.01844 -0.0479 1.0000 0.0646
-8.000 -0.6968 0.02722 0.01734 -0.0473 1.0000 0.0681
-7.750 -0.6759 0.02631 0.01654 -0.0467 1.0000 0.0709
-7.500 -0.6540 0.02556 0.01577 -0.0462 1.0000 0.0744
-7.250 -0.6313 0.02488 0.01493 -0.0457 1.0000 0.0787
-7.000 -0.6089 0.02410 0.01426 -0.0455 1.0000 0.0826
-6.750 -0.5854 0.02350 0.01364 -0.0453 1.0000 0.0878
-6.500 -0.5616 0.02285 0.01298 -0.0451 1.0000 0.0929
-6.250 -0.5370 0.02228 0.01245 -0.0452 1.0000 0.0990
-6.000 -0.5118 0.02173 0.01190 -0.0453 1.0000 0.1055
-5.750 -0.4856 0.02118 0.01141 -0.0457 1.0000 0.1135
-5.500 -0.4585 0.02065 0.01093 -0.0463 1.0000 0.1228
-5.250 -0.4307 0.02016 0.01050 -0.0470 1.0000 0.1351
-5.000 -0.4017 0.01964 0.01012 -0.0480 1.0000 0.1540
-4.750 -0.3711 0.01906 0.00973 -0.0495 1.0000 0.1865
-4.500 -0.3362 0.01821 0.00934 -0.0523 1.0000 0.2617
-4.250 -0.2967 0.01711 0.00919 -0.0563 1.0000 0.4251
-4.000 -0.2807 0.01750 0.01014 -0.0530 1.0000 0.5286
-3.750 -0.2580 0.01790 0.01061 -0.0517 0.9998 0.5781
-3.500 -0.2248 0.01829 0.01093 -0.0527 0.9965 0.6116
-3.250 -0.1895 0.01872 0.01127 -0.0541 0.9936 0.6381
-3.000 -0.1609 0.01923 0.01175 -0.0538 0.9893 0.6554
-2.750 -0.1322 0.01983 0.01234 -0.0534 0.9852 0.6722
-2.500 -0.1032 0.02049 0.01299 -0.0528 0.9813 0.6891
-2.250 -0.0852 0.02114 0.01370 -0.0495 0.9752 0.6988
-2.000 -0.0537 0.02146 0.01398 -0.0500 0.9717 0.7103
-1.750 -0.0258 0.02169 0.01421 -0.0497 0.9680 0.7158
-1.500 0.0052 0.02175 0.01424 -0.0507 0.9632 0.7225
-1.250 0.0399 0.02181 0.01428 -0.0523 0.9592 0.7285
-1.000 0.0730 0.02191 0.01440 -0.0532 0.9557 0.7325
-0.750 0.1008 0.02192 0.01442 -0.0533 0.9487 0.7365
-0.500 0.1388 0.02187 0.01438 -0.0558 0.9441 0.7406
-0.250 0.1805 0.02176 0.01428 -0.0591 0.9389 0.7453
0.000 0.2119 0.02166 0.01424 -0.0596 0.9305 0.7475
0.250 0.2498 0.02148 0.01411 -0.0614 0.9231 0.7497
0.500 0.2893 0.02117 0.01386 -0.0634 0.9132 0.7519
0.750 0.3382 0.02040 0.01315 -0.0663 0.8969 0.7541
1.000 0.3792 0.01968 0.01249 -0.0678 0.8765 0.7570
1.250 0.4167 0.01911 0.01198 -0.0689 0.8536 0.7603
1.500 0.4543 0.01859 0.01149 -0.0700 0.8239 0.7635
1.750 0.4864 0.01817 0.01110 -0.0697 0.7860 0.7654
2.000 0.5225 0.01778 0.01060 -0.0700 0.7177 0.7675
2.250 0.5570 0.01802 0.01002 -0.0698 0.5428 0.7694
2.500 0.5755 0.01914 0.01025 -0.0681 0.3842 0.7718
2.750 0.5971 0.02011 0.01064 -0.0674 0.2727 0.7744
3.000 0.6221 0.02094 0.01104 -0.0674 0.2027 0.7774
3.250 0.6491 0.02163 0.01148 -0.0678 0.1630 0.7806
3.500 0.6715 0.02220 0.01193 -0.0668 0.1424 0.7827
3.750 0.6949 0.02274 0.01244 -0.0660 0.1284 0.7850
4.000 0.7192 0.02330 0.01298 -0.0654 0.1176 0.7876
4.250 0.7435 0.02398 0.01358 -0.0650 0.1095 0.7905
4.500 0.7703 0.02453 0.01420 -0.0651 0.1015 0.7934
4.750 0.7971 0.02528 0.01488 -0.0653 0.0953 0.7962
5.000 0.8225 0.02586 0.01553 -0.0650 0.0890 0.7983
5.250 0.8452 0.02658 0.01621 -0.0642 0.0842 0.8005
5.500 0.8699 0.02728 0.01702 -0.0637 0.0794 0.8031
5.750 0.8947 0.02803 0.01780 -0.0634 0.0751 0.8060
6.000 0.9203 0.02897 0.01871 -0.0633 0.0714 0.8089
6.250 0.9477 0.02986 0.01977 -0.0635 0.0672 0.8117
6.500 0.9736 0.03082 0.02074 -0.0635 0.0642 0.8142
6.750 0.9970 0.03189 0.02184 -0.0629 0.0616 0.8164
7.000 1.0208 0.03296 0.02316 -0.0622 0.0585 0.8189
7.250 1.0441 0.03398 0.02427 -0.0617 0.0560 0.8219
7.500 1.0683 0.03519 0.02548 -0.0615 0.0542 0.8252
7.750 1.0927 0.03690 0.02746 -0.0613 0.0523 0.8283
8.000 1.1143 0.03849 0.02936 -0.0606 0.0501 0.8310
8.250 1.1335 0.03974 0.03078 -0.0595 0.0483 0.8335
8.500 1.1529 0.04093 0.03203 -0.0586 0.0470 0.8365
8.750 1.1708 0.04285 0.03417 -0.0576 0.0459 0.8398
9.000 1.1837 0.04564 0.03747 -0.0560 0.0447 0.8431
9.250 1.1939 0.04845 0.04073 -0.0542 0.0436 0.8462
9.500 1.2002 0.05093 0.04355 -0.0518 0.0427 0.8490
9.750 1.2068 0.05309 0.04597 -0.0497 0.0418 0.8519
10.000 1.2136 0.05503 0.04809 -0.0478 0.0410 0.8551
10.250 1.2215 0.05679 0.04996 -0.0462 0.0403 0.8584
10.500 1.2205 0.05928 0.05264 -0.0438 0.0397 0.8616
10.750 1.1963 0.06314 0.05696 -0.0393 0.0394 0.8645
11.000 1.1706 0.06773 0.06196 -0.0363 0.0392 0.8675
11.250 1.1421 0.07312 0.06770 -0.0350 0.0391 0.8705
11.500 1.1100 0.07970 0.07459 -0.0358 0.0392 0.8733
11.750 1.0741 0.08815 0.08332 -0.0397 0.0393 0.8756
12.000 1.0331 0.09974 0.09516 -0.0476 0.0396 0.8771
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