NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.9 at α=-2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21010-il-1000000-n5.txt Download as CSV file: xf-sc21010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1010 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
------ -------- --------- --------- -------- -------- --------
-18.750 -0.9985 0.07933 0.07668 -0.0531 0.9999 0.0111
-18.500 -1.0471 0.06653 0.06367 -0.0609 0.9999 0.0110
-18.250 -1.0777 0.05730 0.05426 -0.0671 0.9999 0.0109
-18.000 -1.0969 0.05037 0.04719 -0.0720 0.9999 0.0110
-17.750 -1.1096 0.04486 0.04154 -0.0759 0.9999 0.0110
-17.500 -1.1165 0.04057 0.03713 -0.0787 0.9999 0.0111
-17.250 -1.1221 0.03702 0.03347 -0.0805 0.9999 0.0112
-17.000 -1.1302 0.03412 0.03048 -0.0808 0.9999 0.0112
-16.750 -1.1483 0.03191 0.02819 -0.0781 0.9999 0.0113
-16.500 -1.1436 0.02963 0.02581 -0.0794 0.9992 0.0114
-16.250 -1.1201 0.02741 0.02345 -0.0839 0.9975 0.0115
-16.000 -1.0933 0.02551 0.02142 -0.0883 0.9961 0.0117
-15.750 -1.0643 0.02394 0.01972 -0.0922 0.9950 0.0118
-15.500 -1.0345 0.02265 0.01831 -0.0954 0.9941 0.0119
-15.250 -1.0063 0.02158 0.01714 -0.0976 0.9928 0.0121
-15.000 -0.9777 0.02063 0.01608 -0.0997 0.9913 0.0122
-14.750 -0.9487 0.01937 0.01472 -0.1022 0.9900 0.0125
-14.500 -0.9187 0.01842 0.01369 -0.1043 0.9889 0.0128
-14.250 -0.8881 0.01764 0.01285 -0.1063 0.9880 0.0131
-14.000 -0.8570 0.01695 0.01210 -0.1082 0.9871 0.0134
-13.750 -0.8254 0.01631 0.01141 -0.1101 0.9864 0.0137
-13.500 -0.7934 0.01572 0.01075 -0.1120 0.9857 0.0140
-13.250 -0.7611 0.01515 0.01013 -0.1138 0.9850 0.0143
-13.000 -0.7289 0.01464 0.00955 -0.1156 0.9844 0.0147
-12.750 -0.6967 0.01416 0.00902 -0.1173 0.9837 0.0150
-12.500 -0.6655 0.01372 0.00852 -0.1187 0.9825 0.0153
-12.250 -0.6350 0.01313 0.00789 -0.1200 0.9805 0.0159
-12.000 -0.6039 0.01268 0.00742 -0.1214 0.9785 0.0165
-11.750 -0.5723 0.01229 0.00700 -0.1227 0.9767 0.0171
-11.500 -0.5406 0.01192 0.00660 -0.1241 0.9750 0.0177
-11.250 -0.5085 0.01157 0.00622 -0.1255 0.9735 0.0183
-11.000 -0.4763 0.01126 0.00586 -0.1268 0.9721 0.0188
-10.750 -0.4441 0.01088 0.00547 -0.1283 0.9706 0.0199
-10.500 -0.4142 0.01059 0.00517 -0.1291 0.9677 0.0210
-10.250 -0.3838 0.01033 0.00490 -0.1300 0.9649 0.0222
-10.000 -0.3529 0.01010 0.00464 -0.1309 0.9625 0.0231
-9.750 -0.3214 0.00980 0.00434 -0.1320 0.9603 0.0247
-9.500 -0.2901 0.00956 0.00410 -0.1330 0.9582 0.0262
-9.250 -0.2596 0.00936 0.00388 -0.1338 0.9556 0.0275
-9.000 -0.2293 0.00914 0.00366 -0.1346 0.9523 0.0292
-8.750 -0.1988 0.00893 0.00345 -0.1354 0.9490 0.0312
-8.500 -0.1683 0.00876 0.00327 -0.1361 0.9459 0.0332
-8.250 -0.1375 0.00857 0.00307 -0.1369 0.9430 0.0358
-8.000 -0.1071 0.00838 0.00290 -0.1376 0.9396 0.0386
-7.750 -0.0768 0.00823 0.00274 -0.1383 0.9358 0.0412
-7.500 -0.0461 0.00805 0.00258 -0.1390 0.9322 0.0466
-7.250 -0.0154 0.00787 0.00243 -0.1398 0.9291 0.0543
-7.000 0.0153 0.00771 0.00231 -0.1405 0.9259 0.0637
-6.750 0.0460 0.00755 0.00219 -0.1413 0.9221 0.0740
-6.500 0.0768 0.00738 0.00208 -0.1420 0.9181 0.0895
-6.250 0.1075 0.00722 0.00198 -0.1427 0.9143 0.1058
-6.000 0.1383 0.00708 0.00188 -0.1435 0.9107 0.1239
-5.750 0.1695 0.00690 0.00180 -0.1443 0.9069 0.1499
-5.500 0.2010 0.00669 0.00171 -0.1453 0.9033 0.1869
-5.250 0.2328 0.00646 0.00163 -0.1463 0.9001 0.2353
-5.000 0.2646 0.00625 0.00157 -0.1474 0.8970 0.2864
-4.750 0.2964 0.00603 0.00153 -0.1484 0.8930 0.3400
-4.500 0.3275 0.00588 0.00151 -0.1492 0.8876 0.3876
-4.250 0.3576 0.00581 0.00150 -0.1497 0.8815 0.4129
-4.000 0.3877 0.00573 0.00149 -0.1501 0.8718 0.4439
-3.750 0.4169 0.00571 0.00148 -0.1502 0.8583 0.4638
-3.500 0.4455 0.00574 0.00146 -0.1502 0.8389 0.4802
-3.250 0.4744 0.00576 0.00147 -0.1503 0.8198 0.4979
-3.000 0.5032 0.00581 0.00148 -0.1504 0.7985 0.5164
-2.750 0.5313 0.00591 0.00152 -0.1503 0.7668 0.5350
-2.500 0.5571 0.00626 0.00159 -0.1497 0.6935 0.5490
-2.250 0.5789 0.00720 0.00186 -0.1485 0.5361 0.5575
-2.000 0.6019 0.00811 0.00217 -0.1478 0.3905 0.5673
-1.750 0.6276 0.00866 0.00238 -0.1475 0.3031 0.5761
-1.500 0.6535 0.00916 0.00259 -0.1472 0.2293 0.5855
-1.250 0.6801 0.00956 0.00278 -0.1470 0.1723 0.5949
-1.000 0.7070 0.00991 0.00297 -0.1468 0.1302 0.6055
-0.750 0.7343 0.01019 0.00316 -0.1467 0.1010 0.6164
-0.500 0.7617 0.01045 0.00334 -0.1465 0.0811 0.6265
-0.250 0.7892 0.01067 0.00352 -0.1464 0.0676 0.6366
0.000 0.8166 0.01091 0.00371 -0.1462 0.0543 0.6469
0.250 0.8439 0.01114 0.00391 -0.1460 0.0463 0.6573
0.500 0.8713 0.01135 0.00412 -0.1458 0.0413 0.6666
0.750 0.8986 0.01157 0.00432 -0.1456 0.0377 0.6741
1.000 0.9258 0.01178 0.00454 -0.1453 0.0349 0.6811
1.250 0.9527 0.01203 0.00477 -0.1450 0.0318 0.6878
1.500 0.9798 0.01223 0.00499 -0.1448 0.0303 0.6937
1.750 1.0066 0.01246 0.00523 -0.1444 0.0285 0.7000
2.000 1.0331 0.01274 0.00549 -0.1440 0.0265 0.7058
2.250 1.0598 0.01297 0.00576 -0.1437 0.0254 0.7116
2.500 1.0862 0.01322 0.00602 -0.1433 0.0241 0.7180
2.750 1.1124 0.01350 0.00631 -0.1428 0.0226 0.7236
3.000 1.1382 0.01380 0.00662 -0.1423 0.0212 0.7294
3.250 1.1643 0.01407 0.00692 -0.1418 0.0203 0.7347
3.500 1.1900 0.01437 0.00724 -0.1413 0.0193 0.7394
3.750 1.2154 0.01469 0.00757 -0.1407 0.0184 0.7442
4.000 1.2403 0.01508 0.00797 -0.1400 0.0174 0.7493
4.250 1.2656 0.01540 0.00833 -0.1394 0.0170 0.7546
4.500 1.2905 0.01574 0.00872 -0.1387 0.0164 0.7601
4.750 1.3151 0.01610 0.00912 -0.1380 0.0158 0.7666
5.000 1.3394 0.01649 0.00953 -0.1372 0.0153 0.7722
5.250 1.3634 0.01690 0.00997 -0.1363 0.0148 0.7777
5.500 1.3868 0.01737 0.01047 -0.1354 0.0142 0.7828
5.750 1.4100 0.01785 0.01099 -0.1344 0.0138 0.7871
6.000 1.4333 0.01827 0.01147 -0.1335 0.0136 0.7910
6.250 1.4563 0.01872 0.01198 -0.1324 0.0133 0.7954
6.500 1.4788 0.01920 0.01251 -0.1313 0.0130 0.7999
6.750 1.5009 0.01969 0.01306 -0.1302 0.0127 0.8045
7.000 1.5226 0.02020 0.01363 -0.1290 0.0124 0.8096
7.250 1.5439 0.02074 0.01422 -0.1277 0.0122 0.8148
7.500 1.5647 0.02130 0.01482 -0.1264 0.0119 0.8192
7.750 1.5848 0.02190 0.01548 -0.1249 0.0117 0.8236
8.000 1.6039 0.02256 0.01621 -0.1233 0.0114 0.8283
8.250 1.6216 0.02335 0.01706 -0.1214 0.0112 0.8327
8.500 1.6378 0.02418 0.01798 -0.1193 0.0110 0.8366
8.750 1.6546 0.02485 0.01874 -0.1173 0.0109 0.8410
9.000 1.6704 0.02556 0.01953 -0.1152 0.0108 0.8456
9.250 1.6848 0.02630 0.02037 -0.1128 0.0107 0.8501
9.500 1.6973 0.02708 0.02125 -0.1101 0.0106 0.8554
9.750 1.7074 0.02791 0.02217 -0.1070 0.0105 0.8609
10.000 1.7183 0.02878 0.02314 -0.1042 0.0103 0.8655
10.250 1.7292 0.02967 0.02414 -0.1015 0.0102 0.8701
10.500 1.7391 0.03067 0.02523 -0.0987 0.0101 0.8747
10.750 1.7484 0.03172 0.02639 -0.0960 0.0099 0.8795
11.000 1.7571 0.03282 0.02759 -0.0933 0.0098 0.8852
11.500 1.7709 0.03535 0.03035 -0.0878 0.0096 0.8998
11.750 1.7766 0.03669 0.03184 -0.0851 0.0095 0.9142
12.000 1.7787 0.03811 0.03341 -0.0819 0.0094 1.0001
12.250 1.7825 0.03980 0.03520 -0.0795 0.0093 1.0001
12.500 1.7852 0.04165 0.03715 -0.0771 0.0093 1.0001
12.750 1.7867 0.04366 0.03927 -0.0748 0.0092 1.0001
13.000 1.7864 0.04591 0.04164 -0.0726 0.0091 1.0001
13.250 1.7849 0.04836 0.04420 -0.0707 0.0090 1.0001
13.500 1.7809 0.05120 0.04716 -0.0689 0.0090 1.0001
13.750 1.7749 0.05438 0.05047 -0.0674 0.0089 1.0001
14.000 1.7666 0.05798 0.05420 -0.0663 0.0088 1.0001
14.250 1.7554 0.06220 0.05856 -0.0657 0.0088 1.0001
14.500 1.7418 0.06708 0.06360 -0.0658 0.0087 1.0001
14.750 1.7250 0.07286 0.06953 -0.0669 0.0087 1.0001
15.000 1.7055 0.07962 0.07648 -0.0691 0.0087 1.0001
15.250 1.6814 0.08792 0.08497 -0.0729 0.0087 1.0001
15.500 1.6508 0.09828 0.09553 -0.0787 0.0087 1.0001
15.750 1.6113 0.11133 0.10883 -0.0866 0.0087 1.0001
16.000 1.5524 0.12951 0.12730 -0.0980 0.0088 1.0001
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