NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 1,000,000 Max Cl/Cd: 49.7 at α=0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20404-il-1000000.txt Download as CSV file: xf-sc20404-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0404 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6708 0.09484 0.09326 0.0183 1.0000 0.0054
-8.250 -0.6686 0.09061 0.08904 0.0156 1.0000 0.0055
-8.000 -0.6666 0.08628 0.08473 0.0125 1.0000 0.0056
-7.750 -0.6603 0.08115 0.07962 0.0068 1.0000 0.0057
-7.500 -0.6487 0.07477 0.07323 -0.0024 1.0000 0.0058
-7.250 -0.6348 0.06840 0.06681 -0.0103 1.0000 0.0059
-7.000 -0.6190 0.06238 0.06070 -0.0164 1.0000 0.0061
-6.750 -0.6009 0.05663 0.05484 -0.0213 1.0000 0.0064
-6.500 -0.5802 0.05120 0.04927 -0.0251 1.0000 0.0069
-6.250 -0.5561 0.04653 0.04443 -0.0276 1.0000 0.0076
-4.750 -0.3904 0.01727 0.01315 -0.0366 1.0000 0.0062
-4.500 -0.3568 0.01224 0.00750 -0.0370 1.0000 0.0055
-4.250 -0.3287 0.01191 0.00708 -0.0370 1.0000 0.0077
-4.000 -0.3008 0.01151 0.00661 -0.0370 1.0000 0.0084
-3.750 -0.2713 0.00951 0.00441 -0.0376 1.0000 0.0101
-3.500 -0.2420 0.00863 0.00344 -0.0379 1.0000 0.0098
-3.250 -0.2117 0.00769 0.00236 -0.0385 1.0000 0.0103
-3.000 -0.1821 0.00713 0.00171 -0.0388 1.0000 0.0149
-2.750 -0.1542 0.00694 0.00147 -0.0389 1.0000 0.0180
-2.500 -0.1248 0.00638 0.00105 -0.0393 1.0000 0.0733
-2.250 -0.0958 0.00582 0.00089 -0.0401 1.0000 0.1948
-2.000 -0.0658 0.00492 0.00073 -0.0413 1.0000 0.4265
-1.750 -0.0373 0.00438 0.00069 -0.0419 1.0000 0.5833
-1.500 -0.0100 0.00416 0.00071 -0.0419 1.0000 0.6648
-1.250 0.0169 0.00402 0.00075 -0.0417 1.0000 0.7198
-1.000 0.0436 0.00398 0.00077 -0.0414 1.0000 0.7411
-0.750 0.0702 0.00393 0.00083 -0.0411 1.0000 0.7736
-0.500 0.0968 0.00390 0.00088 -0.0408 1.0000 0.7943
-0.250 0.1237 0.00389 0.00093 -0.0405 1.0000 0.8080
0.000 0.1576 0.00384 0.00095 -0.0419 0.9962 0.8206
0.250 0.1998 0.00402 0.00090 -0.0445 0.8633 0.8304
0.500 0.2207 0.00519 0.00099 -0.0430 0.5641 0.8414
0.750 0.2462 0.00616 0.00113 -0.0431 0.3116 0.8522
1.000 0.2725 0.00687 0.00129 -0.0432 0.1359 0.8631
1.250 0.2991 0.00734 0.00146 -0.0430 0.0395 0.8747
1.500 0.3261 0.00780 0.00198 -0.0426 0.0163 0.8869
1.750 0.3527 0.00794 0.00223 -0.0423 0.0145 0.9004
2.000 0.3787 0.00817 0.00254 -0.0418 0.0117 0.9156
2.250 0.4027 0.00880 0.00333 -0.0406 0.0093 0.9361
2.500 0.4253 0.00954 0.00426 -0.0391 0.0092 1.0000
2.750 0.4532 0.01086 0.00571 -0.0387 0.0100 1.0000
3.250 0.5077 0.01442 0.00967 -0.0382 0.0072 1.0000
3.500 0.5359 0.01483 0.01015 -0.0381 0.0059 1.0000
3.750 0.5637 0.01845 0.01427 -0.0369 0.0051 1.0000
4.250 0.6075 0.03279 0.02987 -0.0342 0.0075 1.0000
4.500 0.6305 0.03705 0.03439 -0.0337 0.0075 1.0000
4.750 0.6529 0.04143 0.03900 -0.0334 0.0075 1.0000
5.000 0.6747 0.04589 0.04366 -0.0334 0.0074 1.0000
5.250 0.6961 0.05029 0.04824 -0.0337 0.0073 1.0000
5.500 0.7200 0.05374 0.05182 -0.0342 0.0069 1.0000
5.750 0.7430 0.05794 0.05615 -0.0351 0.0062 1.0000
6.000 0.7614 0.06316 0.06150 -0.0371 0.0058 1.0000
6.250 0.7773 0.06860 0.06704 -0.0397 0.0055 1.0000
6.500 0.7909 0.07415 0.07269 -0.0431 0.0053 1.0000
6.750 0.8023 0.07978 0.07837 -0.0472 0.0051 1.0000
7.000 0.8114 0.08539 0.08403 -0.0518 0.0049 1.0000
7.250 0.8179 0.09097 0.08965 -0.0570 0.0049 1.0000
7.500 0.8204 0.09630 0.09497 -0.0624 0.0048 1.0000
7.750 0.8186 0.10099 0.09965 -0.0662 0.0048 1.0000
8.000 0.8181 0.10551 0.10416 -0.0690 0.0047 1.0000
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Polar data table (+)
Polar graphs
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