NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.25 at α=-1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc21010-il-1000000.txt Download as CSV file: xf-sc21010-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8842 0.07398 0.07159 -0.0572 0.9999 0.0148
-17.000 -0.9250 0.06216 0.05957 -0.0654 0.9999 0.0147
-16.750 -0.9487 0.05422 0.05146 -0.0711 0.9999 0.0147
-16.500 -0.9657 0.04806 0.04514 -0.0755 0.9999 0.0147
-16.250 -0.9782 0.04336 0.04031 -0.0783 0.9999 0.0148
-16.000 -0.9899 0.03971 0.03655 -0.0794 0.9999 0.0149
-15.750 -1.0068 0.03695 0.03369 -0.0781 0.9999 0.0149
-15.500 -1.0320 0.03498 0.03166 -0.0740 0.9999 0.0149
-15.250 -1.0384 0.03275 0.02933 -0.0735 0.9999 0.0150
-15.000 -1.0223 0.03060 0.02702 -0.0767 0.9992 0.0151
-14.750 -0.9929 0.02860 0.02484 -0.0816 0.9979 0.0153
-14.500 -0.9681 0.02467 0.02059 -0.0873 0.9965 0.0156
-14.250 -0.9384 0.02266 0.01843 -0.0910 0.9956 0.0160
-14.000 -0.9069 0.02148 0.01716 -0.0938 0.9949 0.0163
-13.750 -0.8747 0.02053 0.01614 -0.0963 0.9943 0.0166
-13.500 -0.8423 0.01966 0.01519 -0.0987 0.9938 0.0170
-13.250 -0.8120 0.01882 0.01427 -0.1005 0.9924 0.0174
-13.000 -0.7804 0.01802 0.01337 -0.1025 0.9912 0.0178
-12.750 -0.7479 0.01727 0.01254 -0.1045 0.9901 0.0182
-12.500 -0.7150 0.01661 0.01180 -0.1065 0.9890 0.0186
-12.250 -0.6818 0.01610 0.01121 -0.1084 0.9881 0.0189
-12.000 -0.6474 0.01475 0.00978 -0.1113 0.9875 0.0198
-11.750 -0.6135 0.01422 0.00922 -0.1134 0.9868 0.0205
-11.500 -0.5793 0.01373 0.00870 -0.1154 0.9861 0.0212
-11.250 -0.5448 0.01326 0.00819 -0.1174 0.9856 0.0219
-11.000 -0.5101 0.01284 0.00772 -0.1194 0.9850 0.0227
-10.750 -0.4748 0.01226 0.00707 -0.1217 0.9846 0.0235
-10.500 -0.4393 0.01169 0.00649 -0.1240 0.9843 0.0249
-10.250 -0.4044 0.01136 0.00616 -0.1259 0.9839 0.0262
-10.000 -0.3695 0.01109 0.00586 -0.1278 0.9835 0.0275
-9.750 -0.3354 0.01060 0.00535 -0.1297 0.9825 0.0295
-9.500 -0.3038 0.01030 0.00506 -0.1308 0.9804 0.0313
-9.250 -0.2705 0.01006 0.00479 -0.1323 0.9790 0.0331
-9.000 -0.2362 0.00968 0.00439 -0.1340 0.9778 0.0355
-8.750 -0.2022 0.00938 0.00411 -0.1357 0.9766 0.0382
-8.500 -0.1685 0.00917 0.00388 -0.1372 0.9753 0.0405
-8.250 -0.1338 0.00883 0.00355 -0.1389 0.9742 0.0451
-8.000 -0.1001 0.00861 0.00334 -0.1404 0.9728 0.0487
-7.750 -0.0663 0.00833 0.00310 -0.1419 0.9714 0.0563
-7.500 -0.0352 0.00809 0.00292 -0.1428 0.9687 0.0672
-7.250 -0.0040 0.00786 0.00275 -0.1437 0.9657 0.0839
-7.000 0.0281 0.00760 0.00259 -0.1448 0.9631 0.1070
-6.750 0.0599 0.00737 0.00244 -0.1459 0.9606 0.1312
-6.500 0.0925 0.00708 0.00230 -0.1471 0.9583 0.1701
-6.250 0.1248 0.00674 0.00217 -0.1484 0.9554 0.2283
-6.000 0.1567 0.00642 0.00207 -0.1496 0.9519 0.2914
-5.750 0.1886 0.00615 0.00199 -0.1507 0.9486 0.3535
-5.500 0.2197 0.00597 0.00194 -0.1515 0.9456 0.3976
-5.250 0.2505 0.00586 0.00192 -0.1521 0.9427 0.4322
-5.000 0.2803 0.00578 0.00190 -0.1526 0.9389 0.4573
-4.750 0.3102 0.00570 0.00189 -0.1530 0.9348 0.4827
-4.500 0.3396 0.00565 0.00186 -0.1532 0.9304 0.5027
-4.250 0.3690 0.00561 0.00185 -0.1533 0.9253 0.5192
-4.000 0.3977 0.00554 0.00183 -0.1533 0.9176 0.5376
-3.750 0.4261 0.00550 0.00180 -0.1532 0.9087 0.5523
-3.500 0.4542 0.00547 0.00175 -0.1529 0.8973 0.5652
-3.250 0.4829 0.00545 0.00175 -0.1529 0.8866 0.5783
-3.000 0.5117 0.00545 0.00175 -0.1529 0.8761 0.5923
-2.750 0.5402 0.00546 0.00175 -0.1528 0.8633 0.6062
-2.500 0.5686 0.00548 0.00177 -0.1527 0.8470 0.6176
-2.250 0.5971 0.00552 0.00178 -0.1526 0.8308 0.6269
-2.000 0.6250 0.00560 0.00181 -0.1523 0.8082 0.6372
-1.750 0.6531 0.00569 0.00186 -0.1522 0.7844 0.6472
-1.500 0.6800 0.00590 0.00193 -0.1517 0.7431 0.6572
-1.250 0.7036 0.00645 0.00208 -0.1506 0.6435 0.6667
-1.000 0.7231 0.00768 0.00250 -0.1491 0.4611 0.6756
-0.750 0.7450 0.00867 0.00289 -0.1481 0.3174 0.6846
-0.500 0.7690 0.00940 0.00319 -0.1475 0.2192 0.6928
-0.250 0.7937 0.01000 0.00348 -0.1469 0.1457 0.7008
0.000 0.8196 0.01046 0.00374 -0.1465 0.1017 0.7081
0.250 0.8458 0.01082 0.00399 -0.1461 0.0753 0.7154
0.750 0.8989 0.01147 0.00450 -0.1454 0.0491 0.7289
1.000 0.9259 0.01172 0.00476 -0.1451 0.0446 0.7353
1.250 0.9525 0.01202 0.00503 -0.1447 0.0405 0.7410
1.500 0.9790 0.01230 0.00533 -0.1443 0.0377 0.7467
1.750 1.0057 0.01255 0.00559 -0.1439 0.0356 0.7526
2.000 1.0316 0.01291 0.00594 -0.1434 0.0329 0.7579
2.250 1.0575 0.01323 0.00631 -0.1429 0.0311 0.7634
2.500 1.0839 0.01350 0.00658 -0.1424 0.0295 0.7693
2.750 1.1097 0.01381 0.00690 -0.1419 0.0278 0.7745
3.000 1.1342 0.01430 0.00742 -0.1411 0.0259 0.7798
3.250 1.1602 0.01458 0.00772 -0.1406 0.0249 0.7850
3.500 1.1857 0.01490 0.00807 -0.1400 0.0238 0.7895
3.750 1.2106 0.01527 0.00845 -0.1393 0.0227 0.7940
4.000 1.2328 0.01603 0.00925 -0.1381 0.0214 0.7987
4.250 1.2580 0.01636 0.00962 -0.1374 0.0209 0.8034
4.500 1.2822 0.01676 0.01008 -0.1366 0.0203 0.8081
4.750 1.3062 0.01720 0.01056 -0.1357 0.0197 0.8136
5.000 1.3300 0.01763 0.01102 -0.1348 0.0191 0.8188
5.250 1.3534 0.01807 0.01150 -0.1338 0.0185 0.8234
5.500 1.3742 0.01886 0.01232 -0.1324 0.0178 0.8282
5.750 1.3943 0.01979 0.01332 -0.1309 0.0173 0.8326
6.000 1.4168 0.02028 0.01389 -0.1298 0.0170 0.8365
6.250 1.4387 0.02084 0.01453 -0.1286 0.0167 0.8407
6.500 1.4601 0.02147 0.01523 -0.1273 0.0164 0.8453
6.750 1.4810 0.02211 0.01593 -0.1259 0.0160 0.8495
7.000 1.5012 0.02276 0.01666 -0.1245 0.0157 0.8541
7.250 1.5210 0.02344 0.01740 -0.1229 0.0154 0.8593
7.500 1.5403 0.02411 0.01814 -0.1214 0.0151 0.8640
7.750 1.5583 0.02487 0.01897 -0.1196 0.0149 0.8686
8.000 1.5750 0.02575 0.01991 -0.1176 0.0146 0.8737
8.250 1.5882 0.02699 0.02126 -0.1151 0.0143 0.8786
8.500 1.5939 0.02923 0.02371 -0.1116 0.0140 0.8838
8.750 1.6068 0.03016 0.02477 -0.1090 0.0139 0.8895
9.000 1.6187 0.03098 0.02571 -0.1063 0.0137 0.8957
9.250 1.6273 0.03181 0.02666 -0.1030 0.0136 0.9033
9.500 1.6346 0.03289 0.02789 -0.0997 0.0135 0.9132
9.750 1.6398 0.03407 0.02925 -0.0962 0.0133 0.9327
10.000 1.6434 0.03534 0.03068 -0.0926 0.0132 1.0001
10.250 1.6483 0.03688 0.03235 -0.0896 0.0131 1.0001
10.500 1.6515 0.03857 0.03418 -0.0865 0.0129 1.0001
10.750 1.6533 0.04042 0.03616 -0.0835 0.0128 1.0001
11.000 1.6542 0.04236 0.03824 -0.0807 0.0127 1.0001
11.250 1.6533 0.04452 0.04054 -0.0779 0.0125 1.0001
11.500 1.6498 0.04705 0.04321 -0.0753 0.0124 1.0001
11.750 1.6463 0.04960 0.04590 -0.0730 0.0123 1.0001
12.000 1.6400 0.05262 0.04906 -0.0709 0.0123 1.0001
12.250 1.6319 0.05598 0.05257 -0.0692 0.0122 1.0001
12.500 1.6218 0.05973 0.05648 -0.0679 0.0121 1.0001
12.750 1.6107 0.06389 0.06079 -0.0673 0.0120 1.0001
13.000 1.5956 0.06891 0.06597 -0.0674 0.0120 1.0001
13.250 1.5786 0.07466 0.07189 -0.0686 0.0120 1.0001
13.500 1.5553 0.08218 0.07961 -0.0713 0.0119 1.0001
13.750 1.5247 0.09214 0.08980 -0.0765 0.0120 1.0001
14.000 1.4815 0.10622 0.10417 -0.0855 0.0120 1.0001
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Polar data table (+)
Polar graphs
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