NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 100,000 Max Cl/Cd: 38.19 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20706-il-100000.txt Download as CSV file: xf-sc20706-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5835 0.09867 0.09355 -0.0119 1.0000 0.0961
-9.250 -0.5981 0.09551 0.09052 -0.0157 1.0000 0.0991
-9.000 -0.6165 0.09049 0.08560 -0.0272 1.0000 0.1001
-8.750 -0.5972 0.08766 0.08278 -0.0155 1.0000 0.1042
-8.500 -0.5942 0.08413 0.07929 -0.0167 1.0000 0.1090
-8.250 -0.6117 0.07703 0.07190 -0.0386 1.0000 0.1141
-8.000 -0.5935 0.07377 0.06897 -0.0274 1.0000 0.1182
-7.750 -0.5915 0.06767 0.06261 -0.0389 1.0000 0.1286
-7.500 -0.5785 0.06490 0.06002 -0.0334 1.0000 0.1333
-7.250 -0.5671 0.06011 0.05511 -0.0377 1.0000 0.1453
-7.000 -0.5523 0.05612 0.05099 -0.0399 1.0000 0.1595
-6.750 -0.5361 0.05277 0.04760 -0.0407 1.0000 0.1766
-6.500 -0.5202 0.04986 0.04467 -0.0409 1.0000 0.2047
-6.250 -0.4368 0.03394 0.02641 -0.0594 1.0000 0.0838
-6.000 -0.3986 0.02899 0.02064 -0.0615 1.0000 0.0696
-5.750 -0.3651 0.02565 0.01676 -0.0626 1.0000 0.0664
-5.500 -0.3334 0.02318 0.01386 -0.0631 1.0000 0.0663
-5.250 -0.3032 0.02168 0.01199 -0.0632 1.0000 0.0720
-5.000 -0.2744 0.01964 0.00990 -0.0633 1.0000 0.0778
-4.750 -0.2452 0.01829 0.00846 -0.0632 1.0000 0.0857
-4.500 -0.2144 0.01680 0.00718 -0.0641 1.0000 0.1051
-4.250 -0.1629 0.01296 0.00573 -0.0709 1.0000 0.5264
-4.000 -0.1487 0.01330 0.00642 -0.0658 1.0000 0.6943
-3.750 -0.1375 0.01378 0.00687 -0.0604 1.0000 0.7471
-3.500 -0.1282 0.01415 0.00722 -0.0546 1.0000 0.7858
-3.250 -0.1207 0.01432 0.00737 -0.0487 1.0000 0.8158
-3.000 -0.1144 0.01431 0.00734 -0.0427 1.0000 0.8453
-2.750 -0.1081 0.01409 0.00710 -0.0369 1.0000 0.8742
-2.500 -0.0995 0.01368 0.00665 -0.0321 1.0000 0.9012
-2.250 -0.0887 0.01312 0.00604 -0.0280 1.0000 0.9283
-2.000 -0.0727 0.01247 0.00532 -0.0254 1.0000 0.9549
-1.750 -0.0454 0.01198 0.00476 -0.0256 1.0000 0.9790
-1.500 -0.0189 0.01170 0.00445 -0.0261 1.0000 1.0000
-1.250 0.0164 0.01172 0.00440 -0.0287 1.0000 1.0000
-1.000 0.0521 0.01177 0.00440 -0.0314 1.0000 1.0000
-0.750 0.0879 0.01185 0.00446 -0.0339 1.0000 1.0000
-0.500 0.1234 0.01195 0.00457 -0.0363 1.0000 1.0000
-0.250 0.1586 0.01207 0.00473 -0.0387 1.0000 1.0000
0.000 0.1934 0.01221 0.00494 -0.0409 1.0000 1.0000
0.250 0.2277 0.01237 0.00519 -0.0429 1.0000 1.0000
0.500 0.2616 0.01255 0.00548 -0.0448 1.0000 1.0000
0.750 0.2949 0.01275 0.00583 -0.0466 1.0000 1.0000
1.000 0.3277 0.01297 0.00626 -0.0483 1.0000 1.0000
1.250 0.3600 0.01322 0.00672 -0.0498 1.0000 1.0000
1.500 0.3917 0.01349 0.00726 -0.0511 1.0000 1.0000
1.750 0.4659 0.01220 0.00666 -0.0581 0.8858 1.0000
2.000 0.5360 0.01767 0.00800 -0.0639 0.0948 1.0000
2.250 0.5660 0.01920 0.00947 -0.0643 0.0792 1.0000
2.500 0.5981 0.02093 0.01123 -0.0648 0.0721 1.0000
2.750 0.6312 0.02376 0.01411 -0.0656 0.0685 1.0000
3.000 0.6633 0.02523 0.01603 -0.0656 0.0634 1.0000
3.250 0.6950 0.02792 0.01915 -0.0655 0.0636 1.0000
3.500 0.7248 0.03136 0.02300 -0.0653 0.0665 1.0000
3.750 0.7553 0.03566 0.02807 -0.0640 0.0797 1.0000
4.500 0.8411 0.05344 0.04850 -0.0619 0.1750 1.0000
4.750 0.8580 0.05655 0.05163 -0.0611 0.1535 1.0000
5.000 0.8730 0.06043 0.05563 -0.0607 0.1390 1.0000
5.500 0.8929 0.06879 0.06452 -0.0612 0.1156 1.0000
5.750 0.8161 0.06294 0.05921 -0.0503 0.1183 1.0000
6.000 0.8241 0.06741 0.06372 -0.0496 0.1121 1.0000
6.250 0.8299 0.07370 0.06994 -0.0488 0.1089 1.0000
6.500 0.8037 0.07926 0.07579 -0.0518 0.1058 1.0000
6.750 0.7863 0.08441 0.08097 -0.0532 0.1039 1.0000
7.000 0.7704 0.08989 0.08646 -0.0560 0.1023 1.0000
7.250 0.7651 0.09483 0.09139 -0.0574 0.0994 1.0000
7.500 0.7872 0.09946 0.09599 -0.0518 0.0953 1.0000
7.750 0.7662 0.10530 0.10182 -0.0572 0.0951 1.0000
8.000 0.7456 0.11073 0.10720 -0.0625 0.0943 1.0000
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Polar data table (+)
Polar graphs
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