NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il) Reynolds number: 100,000 Max Cl/Cd: 29.83 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20612-il-100000.txt Download as CSV file: xf-sc20612-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5741 0.10171 0.09609 -0.0334 1.0000 0.1811
-10.250 -0.7918 0.06326 0.05684 -0.0540 1.0000 0.0903
-10.000 -0.7915 0.05895 0.05243 -0.0533 1.0000 0.0894
-9.750 -0.7952 0.05473 0.04794 -0.0528 1.0000 0.0891
-9.500 -0.7938 0.05069 0.04356 -0.0524 1.0000 0.0892
-9.250 -0.7869 0.04681 0.03927 -0.0523 1.0000 0.0895
-9.000 -0.7747 0.04316 0.03518 -0.0524 1.0000 0.0898
-8.750 -0.7580 0.03998 0.03149 -0.0525 1.0000 0.0905
-8.500 -0.7400 0.03676 0.02809 -0.0526 1.0000 0.0927
-8.250 -0.7197 0.03517 0.02655 -0.0521 1.0000 0.0960
-8.000 -0.6976 0.03324 0.02435 -0.0520 1.0000 0.0994
-7.750 -0.6736 0.03129 0.02198 -0.0521 1.0000 0.1025
-7.500 -0.6508 0.02936 0.01993 -0.0519 1.0000 0.1068
-7.250 -0.6276 0.02816 0.01870 -0.0515 1.0000 0.1122
-7.000 -0.6022 0.02700 0.01725 -0.0513 1.0000 0.1175
-6.750 -0.5796 0.02557 0.01596 -0.0507 1.0000 0.1238
-6.500 -0.5546 0.02469 0.01494 -0.0504 1.0000 0.1313
-6.250 -0.5311 0.02359 0.01397 -0.0499 1.0000 0.1390
-6.000 -0.5055 0.02290 0.01317 -0.0497 1.0000 0.1483
-5.750 -0.4815 0.02196 0.01244 -0.0492 1.0000 0.1585
-5.500 -0.4560 0.02116 0.01176 -0.0490 1.0000 0.1708
-5.250 -0.4295 0.02038 0.01116 -0.0491 1.0000 0.1879
-5.000 -0.4008 0.01950 0.01059 -0.0498 1.0000 0.2170
-4.750 -0.3572 0.01711 0.01021 -0.0547 1.0000 0.4683
-4.500 -0.3480 0.01841 0.01190 -0.0487 1.0000 0.6002
-4.250 -0.3311 0.01952 0.01293 -0.0453 1.0000 0.6393
-4.000 -0.3205 0.02061 0.01399 -0.0402 1.0000 0.6586
-3.750 -0.3081 0.02154 0.01488 -0.0358 1.0000 0.6757
-3.500 -0.2948 0.02235 0.01564 -0.0317 1.0000 0.6920
-3.250 -0.2806 0.02308 0.01633 -0.0280 1.0000 0.7086
-3.000 -0.2742 0.02379 0.01705 -0.0222 1.0000 0.7206
-2.750 -0.2642 0.02433 0.01758 -0.0175 1.0000 0.7349
-2.500 -0.2512 0.02473 0.01795 -0.0138 1.0000 0.7503
-2.250 -0.2390 0.02507 0.01828 -0.0100 1.0000 0.7665
-2.000 -0.2289 0.02533 0.01854 -0.0056 1.0000 0.7834
-1.750 -0.2203 0.02546 0.01866 -0.0010 1.0000 0.8006
-1.500 -0.2112 0.02545 0.01866 0.0033 1.0000 0.8178
-1.250 -0.1985 0.02534 0.01854 0.0064 1.0000 0.8335
-1.000 -0.1757 0.02534 0.01850 0.0067 1.0000 0.8458
-0.750 -0.1604 0.02499 0.01815 0.0087 1.0000 0.8533
-0.500 -0.1313 0.02507 0.01820 0.0071 1.0000 0.8611
-0.250 -0.1155 0.02476 0.01790 0.0090 1.0000 0.8687
0.000 -0.0867 0.02490 0.01803 0.0074 1.0000 0.8760
0.250 -0.0665 0.02472 0.01788 0.0079 1.0000 0.8809
0.500 -0.0407 0.02480 0.01797 0.0069 1.0000 0.8852
0.750 -0.0063 0.02507 0.01827 0.0041 0.9975 0.8891
1.000 0.0438 0.02538 0.01862 -0.0012 0.9867 0.8927
1.250 0.0906 0.02556 0.01885 -0.0056 0.9747 0.8961
1.500 0.1534 0.02563 0.01899 -0.0126 0.9569 0.8984
1.750 0.2118 0.02525 0.01870 -0.0180 0.9339 0.9004
2.000 0.2756 0.02453 0.01808 -0.0238 0.9131 0.9025
2.250 0.3311 0.02351 0.01719 -0.0275 0.8904 0.9049
2.500 0.3845 0.02205 0.01588 -0.0301 0.8681 0.9073
2.750 0.4372 0.02038 0.01437 -0.0320 0.8449 0.9097
3.000 0.4777 0.01900 0.01312 -0.0321 0.8124 0.9126
3.250 0.5155 0.01781 0.01199 -0.0316 0.7507 0.9151
3.500 0.5477 0.01836 0.01076 -0.0294 0.4014 0.9168
3.750 0.5592 0.02035 0.01152 -0.0273 0.2434 0.9191
4.000 0.5793 0.02134 0.01212 -0.0262 0.2039 0.9216
4.250 0.6033 0.02209 0.01272 -0.0257 0.1814 0.9246
4.500 0.6300 0.02291 0.01342 -0.0258 0.1661 0.9280
4.750 0.6594 0.02389 0.01427 -0.0265 0.1537 0.9311
5.000 0.6892 0.02482 0.01509 -0.0273 0.1429 0.9339
5.250 0.7170 0.02568 0.01605 -0.0274 0.1338 0.9374
5.500 0.7475 0.02711 0.01729 -0.0283 0.1253 0.9409
5.750 0.7767 0.02804 0.01849 -0.0286 0.1184 0.9442
6.000 0.8067 0.02945 0.01982 -0.0296 0.1116 0.9470
6.250 0.8334 0.03093 0.02161 -0.0294 0.1066 0.9505
6.500 0.8600 0.03235 0.02326 -0.0294 0.1019 0.9546
6.750 0.8877 0.03415 0.02502 -0.0301 0.0974 0.9588
7.000 0.9095 0.03625 0.02757 -0.0294 0.0944 0.9632
7.250 0.9309 0.03869 0.03050 -0.0286 0.0925 0.9677
7.500 0.9505 0.04130 0.03355 -0.0279 0.0903 0.9725
7.750 0.9704 0.04367 0.03622 -0.0275 0.0878 0.9782
8.000 0.9939 0.04612 0.03879 -0.0279 0.0857 0.9866
8.250 0.9966 0.05133 0.04483 -0.0258 0.0873 1.0000
8.500 0.9891 0.05807 0.05231 -0.0235 0.0911 1.0000
8.750 0.9892 0.06362 0.05821 -0.0227 0.0937 1.0000
9.000 0.9980 0.06897 0.06368 -0.0230 0.0955 1.0000
9.250 0.8266 0.10048 0.09657 -0.0332 0.1751 1.0000
9.500 0.7707 0.11230 0.10832 -0.0471 0.1674 1.0000
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Polar data table (+)
Polar graphs
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