NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 100,000 Max Cl/Cd: 33.26 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20706-il-100000-n5.txt Download as CSV file: xf-sc20706-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0706 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6050 0.07650 0.07146 -0.0288 1.0000 0.0264
-8.750 -0.6062 0.07127 0.06620 -0.0326 1.0000 0.0259
-8.500 -0.6052 0.06594 0.06080 -0.0361 1.0000 0.0255
-8.250 -0.6006 0.06054 0.05525 -0.0396 1.0000 0.0251
-8.000 -0.5916 0.05503 0.04952 -0.0430 1.0000 0.0247
-7.750 -0.5774 0.04950 0.04366 -0.0463 1.0000 0.0244
-7.500 -0.5578 0.04405 0.03779 -0.0496 1.0000 0.0242
-7.250 -0.5331 0.03894 0.03214 -0.0526 1.0000 0.0242
-7.000 -0.5044 0.03457 0.02714 -0.0552 1.0000 0.0251
-6.750 -0.4736 0.03162 0.02348 -0.0570 1.0000 0.0271
-6.500 -0.4440 0.02784 0.01918 -0.0590 1.0000 0.0281
-6.250 -0.4148 0.02529 0.01626 -0.0599 1.0000 0.0288
-6.000 -0.3861 0.02328 0.01397 -0.0605 1.0000 0.0299
-5.750 -0.3578 0.02161 0.01209 -0.0607 1.0000 0.0316
-5.500 -0.3294 0.02017 0.01049 -0.0609 1.0000 0.0339
-5.250 -0.3012 0.01919 0.00933 -0.0611 1.0000 0.0391
-5.000 -0.2713 0.01793 0.00805 -0.0621 1.0000 0.0449
-4.750 -0.2405 0.01699 0.00700 -0.0630 1.0000 0.0529
-4.500 -0.2088 0.01613 0.00614 -0.0642 1.0000 0.0682
-4.250 -0.1752 0.01518 0.00533 -0.0659 1.0000 0.1063
-4.000 -0.1336 0.01317 0.00481 -0.0708 1.0000 0.4186
-3.750 -0.1087 0.01283 0.00511 -0.0697 1.0000 0.6113
-3.500 -0.0863 0.01293 0.00530 -0.0679 1.0000 0.6765
-3.250 -0.0655 0.01309 0.00548 -0.0657 1.0000 0.7186
-3.000 -0.0450 0.01323 0.00561 -0.0634 1.0000 0.7483
-2.500 -0.0005 0.01336 0.00563 -0.0603 1.0000 0.7868
-2.250 0.0237 0.01337 0.00560 -0.0593 1.0000 0.8002
-2.000 0.0498 0.01336 0.00555 -0.0590 1.0000 0.8116
-1.750 0.0739 0.01334 0.00553 -0.0582 1.0000 0.8212
-1.500 0.0993 0.01332 0.00550 -0.0577 1.0000 0.8305
-1.250 0.1256 0.01332 0.00551 -0.0574 1.0000 0.8404
-1.000 0.1517 0.01332 0.00554 -0.0572 1.0000 0.8500
-0.750 0.1769 0.01330 0.00558 -0.0566 1.0000 0.8587
-0.500 0.2031 0.01332 0.00567 -0.0565 1.0000 0.8680
-0.250 0.2289 0.01333 0.00578 -0.0561 1.0000 0.8782
0.000 0.2530 0.01333 0.00588 -0.0555 1.0000 0.8882
0.250 0.2778 0.01334 0.00603 -0.0550 1.0000 0.8987
0.500 0.3027 0.01336 0.00620 -0.0545 1.0000 0.9099
0.750 0.3266 0.01337 0.00642 -0.0539 1.0000 0.9226
1.000 0.3495 0.01337 0.00662 -0.0530 1.0000 0.9374
1.250 0.4154 0.01249 0.00606 -0.0597 0.9158 0.9387
1.500 0.4920 0.01518 0.00552 -0.0677 0.1377 0.9357
1.750 0.5139 0.01616 0.00610 -0.0666 0.0733 0.9487
2.000 0.5385 0.01690 0.00691 -0.0658 0.0586 0.9660
2.250 0.5666 0.01774 0.00778 -0.0660 0.0464 1.0000
2.500 0.5954 0.01886 0.00901 -0.0663 0.0406 1.0000
2.750 0.6233 0.02053 0.01067 -0.0666 0.0359 1.0000
3.000 0.6538 0.02160 0.01196 -0.0670 0.0314 1.0000
3.250 0.6839 0.02333 0.01386 -0.0673 0.0293 1.0000
3.500 0.7140 0.02528 0.01605 -0.0676 0.0279 1.0000
3.750 0.7431 0.02752 0.01859 -0.0676 0.0270 1.0000
4.000 0.7709 0.03009 0.02155 -0.0675 0.0265 1.0000
4.250 0.7968 0.03305 0.02504 -0.0670 0.0262 1.0000
4.500 0.8195 0.03633 0.02873 -0.0665 0.0253 1.0000
4.750 0.8396 0.04010 0.03310 -0.0654 0.0237 1.0000
5.000 0.8595 0.04392 0.03751 -0.0641 0.0228 1.0000
5.250 0.8757 0.04841 0.04248 -0.0629 0.0228 1.0000
5.500 0.8892 0.05316 0.04766 -0.0619 0.0229 1.0000
5.750 0.9001 0.05810 0.05296 -0.0610 0.0232 1.0000
6.000 0.9082 0.06320 0.05835 -0.0604 0.0235 1.0000
6.250 0.9132 0.06842 0.06380 -0.0599 0.0239 1.0000
6.500 0.9172 0.07343 0.06895 -0.0596 0.0247 1.0000
6.750 0.9156 0.08301 0.07908 -0.0624 0.0293 1.0000
7.000 0.9113 0.08919 0.08537 -0.0645 0.0312 1.0000
7.250 0.9054 0.09458 0.09080 -0.0661 0.0329 1.0000
7.750 0.7570 0.09697 0.09336 -0.0584 0.0296 1.0000
8.000 0.7472 0.10301 0.09937 -0.0611 0.0308 1.0000
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Polar data table (+)
Polar graphs
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