NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 50,000 Max Cl/Cd: 23.34 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20606-il-50000.txt Download as CSV file: xf-sc20606-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5835 0.09516 0.08818 0.0111 1.0000 0.3326
-8.000 -0.5736 0.09135 0.08440 0.0124 1.0000 0.3517
-7.750 -0.5777 0.08927 0.08240 0.0139 1.0000 0.3755
-7.500 -0.5730 0.08651 0.07969 0.0163 1.0000 0.4039
-7.250 -0.5430 0.08194 0.07506 0.0190 1.0000 0.4406
-7.000 -0.5331 0.07876 0.07191 0.0210 1.0000 0.4680
-6.500 -0.5194 0.04717 0.03879 -0.0469 1.0000 0.1359
-6.250 -0.4854 0.04166 0.03229 -0.0510 1.0000 0.1237
-6.000 -0.4556 0.03761 0.02773 -0.0527 1.0000 0.1230
-5.750 -0.4247 0.03387 0.02348 -0.0538 1.0000 0.1210
-5.500 -0.3933 0.03066 0.01973 -0.0544 1.0000 0.1205
-5.250 -0.3621 0.02813 0.01660 -0.0546 1.0000 0.1251
-5.000 -0.3349 0.02603 0.01431 -0.0541 1.0000 0.1385
-4.750 -0.3101 0.02394 0.01224 -0.0526 1.0000 0.1510
-4.500 -0.2863 0.02220 0.01055 -0.0511 1.0000 0.1807
-4.250 -0.2607 0.02007 0.00882 -0.0503 1.0000 0.2351
-4.000 -0.2579 0.01753 0.00923 -0.0416 1.0000 0.7054
-3.750 -0.2689 0.01815 0.00986 -0.0287 1.0000 0.8026
-3.500 -0.2760 0.01802 0.00965 -0.0180 1.0000 0.8668
-3.250 -0.1719 0.01696 0.00759 -0.0264 1.0000 1.0000
-3.000 -0.1616 0.01649 0.00696 -0.0247 1.0000 1.0000
-2.750 -0.1512 0.01607 0.00641 -0.0229 1.0000 1.0000
-2.500 -0.1404 0.01570 0.00592 -0.0211 1.0000 1.0000
-2.250 -0.1252 0.01540 0.00548 -0.0200 1.0000 1.0000
-2.000 -0.1039 0.01519 0.00513 -0.0200 1.0000 1.0000
-1.750 -0.0785 0.01506 0.00482 -0.0208 1.0000 1.0000
-1.500 -0.0504 0.01498 0.00461 -0.0219 1.0000 1.0000
-1.250 -0.0210 0.01495 0.00448 -0.0232 1.0000 1.0000
-1.000 0.0092 0.01496 0.00441 -0.0246 1.0000 1.0000
-0.750 0.0397 0.01500 0.00439 -0.0259 1.0000 1.0000
-0.500 0.0703 0.01507 0.00443 -0.0272 1.0000 1.0000
-0.250 0.1008 0.01516 0.00453 -0.0285 1.0000 1.0000
0.000 0.1311 0.01528 0.00469 -0.0297 1.0000 1.0000
0.250 0.1612 0.01542 0.00491 -0.0308 1.0000 1.0000
0.500 0.1911 0.01558 0.00517 -0.0318 1.0000 1.0000
0.750 0.2206 0.01577 0.00549 -0.0327 1.0000 1.0000
1.000 0.2498 0.01598 0.00587 -0.0336 1.0000 1.0000
1.250 0.2787 0.01622 0.00635 -0.0343 1.0000 1.0000
1.500 0.3072 0.01649 0.00686 -0.0351 1.0000 1.0000
1.750 0.3354 0.01679 0.00745 -0.0357 1.0000 1.0000
2.000 0.3633 0.01713 0.00814 -0.0363 1.0000 1.0000
2.250 0.3909 0.01750 0.00900 -0.0369 1.0000 1.0000
2.500 0.4185 0.01793 0.01000 -0.0373 1.0000 1.0000
2.750 0.5413 0.02386 0.01241 -0.0462 0.1559 1.0000
3.000 0.5757 0.02630 0.01472 -0.0467 0.1340 1.0000
3.250 0.6094 0.02866 0.01754 -0.0466 0.1255 1.0000
3.500 0.6395 0.03125 0.02041 -0.0465 0.1161 1.0000
3.750 0.6701 0.03424 0.02391 -0.0460 0.1150 1.0000
4.000 0.6988 0.03775 0.02791 -0.0456 0.1175 1.0000
4.250 0.7272 0.04151 0.03255 -0.0448 0.1258 1.0000
4.500 0.7524 0.04604 0.03744 -0.0445 0.1325 1.0000
4.750 0.7783 0.05087 0.04298 -0.0442 0.1484 1.0000
6.000 0.8155 0.09017 0.08490 -0.0920 0.4246 1.0000
6.250 0.8241 0.09349 0.08819 -0.0878 0.3815 1.0000
6.500 0.8275 0.09706 0.09172 -0.0856 0.3497 1.0000
6.750 0.6612 0.09245 0.08725 -0.0703 0.3779 1.0000
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Polar data table (+)
Polar graphs
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