NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 1,000,000 Max Cl/Cd: 61.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20406-il-1000000-n5.txt Download as CSV file: xf-sc20406-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0406 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7385 0.09284 0.09128 0.0142 1.0000 0.0044
-9.750 -0.7468 0.08590 0.08437 0.0097 1.0000 0.0044
-9.250 -0.8595 0.02997 0.02722 -0.0282 1.0000 0.0044
-9.000 -0.8396 0.02728 0.02426 -0.0289 1.0000 0.0045
-8.750 -0.8180 0.02489 0.02161 -0.0294 1.0000 0.0047
-8.500 -0.7949 0.02288 0.01933 -0.0299 1.0000 0.0049
-8.250 -0.7707 0.02096 0.01715 -0.0303 1.0000 0.0051
-8.000 -0.7457 0.01930 0.01524 -0.0306 1.0000 0.0053
-7.750 -0.7199 0.01777 0.01349 -0.0310 1.0000 0.0054
-7.500 -0.6936 0.01644 0.01195 -0.0313 1.0000 0.0056
-7.250 -0.6668 0.01519 0.01051 -0.0315 1.0000 0.0057
-7.000 -0.6397 0.01411 0.00927 -0.0318 1.0000 0.0058
-6.750 -0.6123 0.01319 0.00820 -0.0321 1.0000 0.0060
-6.500 -0.5846 0.01248 0.00737 -0.0323 1.0000 0.0062
-6.250 -0.5567 0.01175 0.00654 -0.0326 1.0000 0.0063
-6.000 -0.5286 0.01099 0.00567 -0.0329 1.0000 0.0064
-5.750 -0.5002 0.01035 0.00494 -0.0332 1.0000 0.0064
-5.500 -0.4716 0.00981 0.00432 -0.0336 1.0000 0.0065
-5.250 -0.4430 0.00936 0.00378 -0.0339 1.0000 0.0066
-5.000 -0.4144 0.00898 0.00334 -0.0342 1.0000 0.0067
-4.750 -0.3859 0.00866 0.00298 -0.0345 1.0000 0.0069
-4.500 -0.3571 0.00830 0.00256 -0.0348 1.0000 0.0075
-4.250 -0.3284 0.00803 0.00226 -0.0350 1.0000 0.0089
-4.000 -0.2999 0.00780 0.00202 -0.0352 1.0000 0.0104
-3.750 -0.2715 0.00757 0.00183 -0.0355 1.0000 0.0166
-3.500 -0.2432 0.00736 0.00168 -0.0357 1.0000 0.0262
-3.250 -0.2150 0.00719 0.00155 -0.0358 1.0000 0.0335
-3.000 -0.1870 0.00701 0.00142 -0.0360 1.0000 0.0465
-2.750 -0.1592 0.00683 0.00133 -0.0361 1.0000 0.0625
-2.500 -0.1316 0.00663 0.00123 -0.0362 1.0000 0.0884
-2.250 -0.1018 0.00632 0.00113 -0.0368 0.9988 0.1429
-2.000 -0.0662 0.00593 0.00101 -0.0389 0.9935 0.2263
-1.750 -0.0291 0.00553 0.00090 -0.0413 0.9802 0.3156
-1.500 0.0050 0.00500 0.00083 -0.0430 0.9498 0.4654
-1.250 0.0317 0.00478 0.00083 -0.0427 0.9158 0.5545
-1.000 0.0580 0.00475 0.00082 -0.0422 0.8840 0.5997
-0.750 0.0849 0.00479 0.00082 -0.0419 0.8489 0.6225
-0.500 0.1112 0.00498 0.00082 -0.0414 0.7783 0.6490
-0.250 0.1385 0.00521 0.00084 -0.0413 0.7053 0.6682
0.000 0.1658 0.00562 0.00089 -0.0413 0.5872 0.6865
0.250 0.1927 0.00636 0.00101 -0.0415 0.3950 0.7087
0.500 0.2202 0.00694 0.00114 -0.0418 0.2450 0.7283
0.750 0.2478 0.00745 0.00127 -0.0420 0.1269 0.7422
1.000 0.2759 0.00768 0.00137 -0.0422 0.0838 0.7538
1.250 0.3041 0.00785 0.00149 -0.0423 0.0584 0.7642
1.500 0.3323 0.00799 0.00160 -0.0424 0.0448 0.7735
1.750 0.3605 0.00814 0.00172 -0.0424 0.0345 0.7818
2.000 0.3886 0.00831 0.00186 -0.0425 0.0239 0.7902
2.250 0.4165 0.00853 0.00205 -0.0425 0.0122 0.7975
2.500 0.4446 0.00870 0.00224 -0.0425 0.0093 0.8050
2.750 0.4726 0.00887 0.00246 -0.0425 0.0090 0.8127
3.250 0.5281 0.00928 0.00298 -0.0424 0.0082 0.8324
3.500 0.5557 0.00952 0.00330 -0.0423 0.0079 0.8418
3.750 0.5831 0.00980 0.00365 -0.0422 0.0077 0.8511
4.000 0.6103 0.01010 0.00403 -0.0421 0.0074 0.8604
4.250 0.6373 0.01044 0.00444 -0.0419 0.0072 0.8698
4.500 0.6640 0.01081 0.00489 -0.0416 0.0069 0.8806
4.750 0.6903 0.01122 0.00541 -0.0413 0.0066 0.8924
5.000 0.7159 0.01178 0.00608 -0.0408 0.0062 0.9045
5.250 0.7399 0.01302 0.00754 -0.0401 0.0056 0.9174
5.500 0.7636 0.01401 0.00872 -0.0392 0.0055 0.9313
5.750 0.7858 0.01470 0.00958 -0.0379 0.0054 0.9547
6.000 0.8103 0.01565 0.01071 -0.0373 0.0053 1.0000
6.250 0.8358 0.01693 0.01221 -0.0370 0.0053 1.0000
6.500 0.8614 0.01801 0.01346 -0.0367 0.0051 1.0000
6.750 0.8865 0.01916 0.01480 -0.0365 0.0050 1.0000
7.000 0.9102 0.02084 0.01672 -0.0360 0.0048 1.0000
7.250 0.9318 0.02325 0.01947 -0.0354 0.0047 1.0000
7.500 0.9502 0.02670 0.02336 -0.0344 0.0046 1.0000
7.750 0.9180 0.05185 0.04995 -0.0314 0.0043 1.0000
8.000 0.9121 0.06273 0.06114 -0.0332 0.0041 1.0000
8.250 0.9052 0.07216 0.07075 -0.0369 0.0040 1.0000
8.500 0.8963 0.08103 0.07973 -0.0428 0.0040 1.0000
8.750 0.8805 0.08946 0.08817 -0.0516 0.0040 1.0000
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Polar data table (+)
Polar graphs
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