NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 100,000 Max Cl/Cd: 35.04 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20606-il-100000-n5.txt Download as CSV file: xf-sc20606-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0606 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5005 0.09589 0.09086 -0.0135 1.0000 0.0314
-10.000 -0.5048 0.09073 0.08574 -0.0152 1.0000 0.0299
-9.000 -0.6189 0.07812 0.07306 -0.0239 1.0000 0.0255
-8.750 -0.6195 0.07242 0.06734 -0.0289 1.0000 0.0250
-8.500 -0.6186 0.06689 0.06174 -0.0330 1.0000 0.0247
-8.250 -0.6151 0.06140 0.05610 -0.0365 1.0000 0.0243
-8.000 -0.6079 0.05593 0.05042 -0.0397 1.0000 0.0240
-7.750 -0.5964 0.05050 0.04468 -0.0425 1.0000 0.0237
-7.500 -0.5803 0.04519 0.03898 -0.0450 1.0000 0.0236
-7.250 -0.5595 0.04016 0.03345 -0.0473 1.0000 0.0236
-7.000 -0.5343 0.03588 0.02853 -0.0492 1.0000 0.0247
-6.750 -0.5071 0.03225 0.02424 -0.0508 1.0000 0.0264
-6.500 -0.4802 0.02883 0.02037 -0.0520 1.0000 0.0272
-6.250 -0.4527 0.02617 0.01726 -0.0527 1.0000 0.0278
-6.000 -0.4254 0.02403 0.01481 -0.0529 1.0000 0.0287
-5.750 -0.3983 0.02223 0.01278 -0.0530 1.0000 0.0300
-5.500 -0.3714 0.02068 0.01104 -0.0529 1.0000 0.0319
-5.250 -0.3444 0.01944 0.00963 -0.0527 1.0000 0.0354
-5.000 -0.3171 0.01825 0.00836 -0.0530 1.0000 0.0412
-4.750 -0.2887 0.01721 0.00724 -0.0533 1.0000 0.0477
-4.500 -0.2597 0.01628 0.00628 -0.0539 1.0000 0.0612
-4.250 -0.2297 0.01535 0.00542 -0.0548 1.0000 0.0850
-4.000 -0.1981 0.01421 0.00470 -0.0564 1.0000 0.1647
-3.750 -0.1654 0.01243 0.00439 -0.0588 1.0000 0.4971
-3.500 -0.1420 0.01223 0.00453 -0.0574 1.0000 0.6199
-3.250 -0.1190 0.01225 0.00463 -0.0558 1.0000 0.6834
-3.000 -0.0989 0.01236 0.00480 -0.0534 1.0000 0.7299
-2.750 -0.0788 0.01247 0.00491 -0.0510 1.0000 0.7638
-2.500 -0.0573 0.01250 0.00489 -0.0492 1.0000 0.7863
-2.250 -0.0356 0.01251 0.00487 -0.0475 1.0000 0.8059
-2.000 -0.0127 0.01249 0.00482 -0.0463 1.0000 0.8219
-1.750 0.0109 0.01245 0.00475 -0.0453 1.0000 0.8346
-1.500 0.0349 0.01240 0.00468 -0.0444 1.0000 0.8456
-1.250 0.0594 0.01235 0.00463 -0.0438 1.0000 0.8567
-1.000 0.0843 0.01230 0.00459 -0.0432 1.0000 0.8677
-0.750 0.1095 0.01226 0.00458 -0.0428 1.0000 0.8787
-0.500 0.1340 0.01222 0.00459 -0.0422 1.0000 0.8898
-0.250 0.1577 0.01217 0.00461 -0.0414 1.0000 0.9018
0.000 0.1815 0.01211 0.00465 -0.0407 1.0000 0.9152
0.250 0.2049 0.01205 0.00469 -0.0399 1.0000 0.9304
0.500 0.2280 0.01198 0.00475 -0.0391 1.0000 0.9492
0.750 0.2467 0.01192 0.00485 -0.0378 1.0000 1.0000
1.000 0.2781 0.01212 0.00522 -0.0391 1.0000 1.0000
1.250 0.3331 0.01207 0.00540 -0.0448 0.9770 1.0000
1.500 0.3967 0.01132 0.00489 -0.0504 0.8815 1.0000
1.750 0.4512 0.01339 0.00458 -0.0537 0.2864 1.0000
2.000 0.4769 0.01506 0.00531 -0.0541 0.1064 1.0000
2.250 0.5051 0.01612 0.00617 -0.0545 0.0686 1.0000
2.500 0.5330 0.01711 0.00710 -0.0548 0.0503 1.0000
2.750 0.5608 0.01823 0.00834 -0.0547 0.0430 1.0000
3.000 0.5875 0.01968 0.00977 -0.0548 0.0368 1.0000
3.250 0.6164 0.02072 0.01100 -0.0549 0.0322 1.0000
3.500 0.6450 0.02231 0.01274 -0.0549 0.0300 1.0000
3.750 0.6736 0.02410 0.01473 -0.0549 0.0285 1.0000
4.000 0.7018 0.02616 0.01704 -0.0548 0.0274 1.0000
4.250 0.7289 0.02859 0.01986 -0.0545 0.0267 1.0000
4.500 0.7545 0.03148 0.02318 -0.0541 0.0263 1.0000
4.750 0.7768 0.03514 0.02732 -0.0535 0.0250 1.0000
5.000 0.8005 0.03800 0.03086 -0.0524 0.0233 1.0000
5.250 0.8202 0.04208 0.03550 -0.0514 0.0229 1.0000
5.500 0.8372 0.04657 0.04049 -0.0504 0.0229 1.0000
5.750 0.8516 0.05138 0.04574 -0.0496 0.0231 1.0000
6.000 0.8635 0.05639 0.05112 -0.0490 0.0233 1.0000
6.250 0.8727 0.06156 0.05661 -0.0487 0.0237 1.0000
6.500 0.8790 0.06681 0.06211 -0.0487 0.0241 1.0000
6.750 0.8824 0.07209 0.06759 -0.0489 0.0245 1.0000
7.000 0.8824 0.07743 0.07302 -0.0492 0.0251 1.0000
7.250 0.8795 0.08742 0.08343 -0.0548 0.0300 1.0000
7.500 0.8726 0.09361 0.08968 -0.0581 0.0317 1.0000
7.750 0.8662 0.09944 0.09551 -0.0619 0.0333 1.0000
8.250 0.8703 0.11147 0.10754 -0.0600 0.0490 1.0000
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Polar data table (+)
Polar graphs
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