NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 100,000 Max Cl/Cd: 26.7 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20412-il-100000.txt Download as CSV file: xf-sc20412-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6045 0.10990 0.10422 -0.0167 1.0000 0.1722
-10.250 -0.5742 0.10823 0.10250 -0.0131 1.0000 0.1772
-10.000 -0.8191 0.06488 0.05849 -0.0464 1.0000 0.0932
-9.750 -0.8185 0.06022 0.05372 -0.0462 1.0000 0.0918
-9.500 -0.8231 0.05553 0.04879 -0.0458 1.0000 0.0904
-9.250 -0.8253 0.05095 0.04387 -0.0452 1.0000 0.0892
-9.000 -0.8214 0.04702 0.03955 -0.0446 1.0000 0.0893
-8.750 -0.8124 0.04368 0.03581 -0.0440 1.0000 0.0907
-8.500 -0.7994 0.04061 0.03226 -0.0435 1.0000 0.0923
-8.250 -0.7825 0.03790 0.02907 -0.0430 1.0000 0.0936
-8.000 -0.7642 0.03497 0.02586 -0.0426 1.0000 0.0957
-7.750 -0.7437 0.03325 0.02418 -0.0420 1.0000 0.0992
-7.500 -0.7222 0.03161 0.02237 -0.0413 1.0000 0.1028
-7.250 -0.6998 0.02997 0.02041 -0.0407 1.0000 0.1061
-7.000 -0.6779 0.02819 0.01850 -0.0400 1.0000 0.1103
-6.750 -0.6560 0.02692 0.01727 -0.0392 1.0000 0.1150
-6.500 -0.6331 0.02579 0.01601 -0.0384 1.0000 0.1202
-6.250 -0.6110 0.02451 0.01471 -0.0374 1.0000 0.1260
-6.000 -0.5888 0.02354 0.01382 -0.0365 1.0000 0.1328
-5.750 -0.5663 0.02256 0.01281 -0.0355 1.0000 0.1406
-5.500 -0.5441 0.02169 0.01206 -0.0346 1.0000 0.1505
-5.250 -0.5219 0.02077 0.01129 -0.0338 1.0000 0.1620
-5.000 -0.4989 0.01992 0.01061 -0.0332 1.0000 0.1786
-4.750 -0.4749 0.01900 0.00992 -0.0328 1.0000 0.2051
-4.500 -0.4467 0.01735 0.00903 -0.0343 1.0000 0.2814
-4.250 -0.4315 0.01681 0.01043 -0.0307 1.0000 0.5789
-4.000 -0.4126 0.01798 0.01152 -0.0275 1.0000 0.6394
-3.750 -0.3996 0.01916 0.01266 -0.0228 1.0000 0.6647
-3.500 -0.3873 0.02019 0.01365 -0.0181 1.0000 0.6834
-3.250 -0.3746 0.02105 0.01448 -0.0137 1.0000 0.7002
-3.000 -0.3610 0.02177 0.01515 -0.0097 1.0000 0.7164
-2.750 -0.3473 0.02240 0.01573 -0.0059 1.0000 0.7328
-2.500 -0.3332 0.02294 0.01624 -0.0023 1.0000 0.7490
-2.250 -0.3260 0.02340 0.01671 0.0033 1.0000 0.7608
-2.000 -0.3143 0.02368 0.01696 0.0073 1.0000 0.7747
-1.750 -0.3035 0.02390 0.01717 0.0114 1.0000 0.7903
-1.500 -0.2938 0.02405 0.01731 0.0158 1.0000 0.8072
-1.250 -0.2843 0.02409 0.01735 0.0201 1.0000 0.8249
-1.000 -0.2735 0.02400 0.01725 0.0237 1.0000 0.8417
-0.750 -0.2604 0.02379 0.01702 0.0266 1.0000 0.8558
-0.500 -0.2434 0.02355 0.01676 0.0282 1.0000 0.8670
-0.250 -0.2212 0.02343 0.01661 0.0282 1.0000 0.8763
0.000 -0.2020 0.02314 0.01631 0.0290 1.0000 0.8824
0.250 -0.1782 0.02304 0.01619 0.0285 1.0000 0.8883
0.500 -0.1529 0.02299 0.01614 0.0276 1.0000 0.8934
0.750 -0.1304 0.02287 0.01604 0.0274 0.9998 0.8981
1.000 -0.0811 0.02310 0.01627 0.0222 0.9899 0.9019
1.250 -0.0294 0.02336 0.01655 0.0165 0.9788 0.9051
1.500 0.0191 0.02344 0.01668 0.0117 0.9670 0.9079
1.750 0.0684 0.02336 0.01665 0.0073 0.9519 0.9105
2.000 0.1304 0.02296 0.01633 0.0014 0.9298 0.9122
2.250 0.1938 0.02229 0.01576 -0.0041 0.9103 0.9141
2.500 0.2522 0.02153 0.01512 -0.0087 0.8931 0.9160
2.750 0.3037 0.02055 0.01427 -0.0115 0.8716 0.9175
3.000 0.3495 0.01950 0.01334 -0.0130 0.8471 0.9191
3.250 0.3886 0.01846 0.01240 -0.0131 0.8164 0.9208
3.500 0.4232 0.01747 0.01146 -0.0122 0.7712 0.9229
3.750 0.4494 0.01683 0.01070 -0.0101 0.6809 0.9258
4.000 0.4625 0.01776 0.01009 -0.0058 0.3996 0.9288
4.250 0.4747 0.01932 0.01064 -0.0037 0.2635 0.9319
4.500 0.4952 0.02023 0.01117 -0.0028 0.2174 0.9349
4.750 0.5178 0.02105 0.01170 -0.0023 0.1924 0.9382
5.000 0.5440 0.02187 0.01236 -0.0023 0.1748 0.9412
5.250 0.5719 0.02271 0.01309 -0.0027 0.1608 0.9440
5.500 0.6009 0.02357 0.01400 -0.0033 0.1497 0.9467
5.750 0.6296 0.02459 0.01495 -0.0037 0.1406 0.9496
6.000 0.6580 0.02544 0.01584 -0.0041 0.1322 0.9531
6.250 0.6870 0.02672 0.01718 -0.0046 0.1252 0.9570
6.500 0.7152 0.02773 0.01833 -0.0050 0.1186 0.9610
6.750 0.7440 0.02940 0.01997 -0.0057 0.1128 0.9649
7.000 0.7710 0.03077 0.02177 -0.0058 0.1082 0.9691
7.250 0.7991 0.03211 0.02320 -0.0064 0.1030 0.9736
7.500 0.8266 0.03458 0.02577 -0.0073 0.0991 0.9788
7.750 0.8508 0.03683 0.02862 -0.0072 0.0965 0.9851
8.000 0.8736 0.03932 0.03159 -0.0073 0.0932 0.9949
8.250 0.8953 0.04164 0.03416 -0.0075 0.0904 1.0000
8.500 0.9147 0.04479 0.03762 -0.0076 0.0893 1.0000
8.750 0.9361 0.04806 0.04102 -0.0082 0.0879 1.0000
9.000 0.9500 0.05287 0.04609 -0.0085 0.0869 1.0000
9.250 0.9560 0.05742 0.05110 -0.0079 0.0866 1.0000
9.500 0.9639 0.06186 0.05592 -0.0077 0.0872 1.0000
10.000 0.7211 0.11038 0.10622 -0.0350 0.1653 1.0000
10.250 0.6163 0.10699 0.10299 -0.0111 0.1755 1.0000
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Polar data table (+)
Polar graphs
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