NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 500,000 Max Cl/Cd: 50.28 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20406-il-500000-n5.txt Download as CSV file: xf-sc20406-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5737 0.10795 0.10575 0.0091 1.0000 0.0074
-10.750 -0.5785 0.10245 0.10026 0.0076 1.0000 0.0072
-9.750 -0.7048 0.09535 0.09311 0.0140 1.0000 0.0069
-9.500 -0.7100 0.08944 0.08723 0.0105 1.0000 0.0068
-9.250 -0.7155 0.08313 0.08095 0.0062 1.0000 0.0068
-9.000 -0.7232 0.07589 0.07375 -0.0002 1.0000 0.0067
-8.750 -0.7293 0.06549 0.06329 -0.0136 1.0000 0.0066
-8.500 -0.7319 0.05622 0.05382 -0.0206 1.0000 0.0066
-8.250 -0.7312 0.04623 0.04348 -0.0252 1.0000 0.0066
-8.000 -0.7281 0.03371 0.03026 -0.0282 1.0000 0.0068
-7.750 -0.7097 0.02860 0.02459 -0.0292 1.0000 0.0069
-7.500 -0.6899 0.02284 0.01807 -0.0303 1.0000 0.0072
-7.250 -0.6654 0.01990 0.01468 -0.0309 1.0000 0.0074
-7.000 -0.6395 0.01830 0.01286 -0.0312 1.0000 0.0079
-6.750 -0.6129 0.01720 0.01156 -0.0315 1.0000 0.0083
-6.500 -0.5860 0.01579 0.00994 -0.0317 1.0000 0.0084
-6.250 -0.5588 0.01452 0.00847 -0.0318 1.0000 0.0084
-6.000 -0.5313 0.01349 0.00729 -0.0320 1.0000 0.0085
-5.750 -0.5035 0.01262 0.00630 -0.0323 1.0000 0.0087
-5.500 -0.4755 0.01189 0.00547 -0.0325 1.0000 0.0090
-5.250 -0.4472 0.01127 0.00474 -0.0328 1.0000 0.0093
-5.000 -0.4189 0.01075 0.00415 -0.0331 1.0000 0.0099
-4.750 -0.3905 0.01031 0.00364 -0.0334 1.0000 0.0107
-4.500 -0.3620 0.00992 0.00319 -0.0336 1.0000 0.0119
-4.250 -0.3336 0.00955 0.00282 -0.0338 1.0000 0.0158
-4.000 -0.3054 0.00924 0.00252 -0.0341 1.0000 0.0247
-3.750 -0.2772 0.00897 0.00231 -0.0343 1.0000 0.0367
-3.500 -0.2492 0.00874 0.00211 -0.0345 1.0000 0.0466
-3.250 -0.2213 0.00853 0.00194 -0.0346 1.0000 0.0573
-3.000 -0.1934 0.00827 0.00178 -0.0348 1.0000 0.0820
-2.750 -0.1652 0.00785 0.00159 -0.0352 1.0000 0.1406
-2.500 -0.1369 0.00740 0.00144 -0.0357 1.0000 0.2225
-2.250 -0.1084 0.00689 0.00129 -0.0363 1.0000 0.3289
-2.000 -0.0794 0.00627 0.00120 -0.0371 1.0000 0.4765
-1.750 -0.0515 0.00595 0.00120 -0.0374 1.0000 0.5708
-1.500 -0.0243 0.00578 0.00124 -0.0373 1.0000 0.6285
-1.250 0.0026 0.00570 0.00129 -0.0371 1.0000 0.6675
-1.000 0.0368 0.00561 0.00130 -0.0386 0.9957 0.6941
-0.750 0.0781 0.00551 0.00128 -0.0415 0.9814 0.7175
-0.500 0.1158 0.00545 0.00129 -0.0435 0.9576 0.7416
-0.250 0.1464 0.00545 0.00133 -0.0437 0.9268 0.7605
0.000 0.1705 0.00556 0.00134 -0.0423 0.8718 0.7727
0.250 0.1947 0.00576 0.00135 -0.0411 0.8081 0.7832
0.500 0.2191 0.00616 0.00136 -0.0401 0.7036 0.7931
0.750 0.2434 0.00697 0.00145 -0.0395 0.5121 0.8013
1.000 0.2693 0.00778 0.00162 -0.0395 0.3317 0.8098
1.250 0.2958 0.00844 0.00181 -0.0396 0.1940 0.8187
1.500 0.3226 0.00897 0.00198 -0.0397 0.0990 0.8274
1.750 0.3502 0.00923 0.00214 -0.0397 0.0672 0.8364
2.000 0.3775 0.00941 0.00231 -0.0396 0.0537 0.8457
2.250 0.4046 0.00959 0.00252 -0.0394 0.0421 0.8559
2.500 0.4316 0.00981 0.00272 -0.0392 0.0304 0.8665
2.750 0.4585 0.01005 0.00296 -0.0389 0.0198 0.8768
3.000 0.4850 0.01034 0.00326 -0.0386 0.0137 0.8870
3.250 0.5110 0.01061 0.00360 -0.0381 0.0125 0.8981
3.500 0.5366 0.01091 0.00402 -0.0375 0.0117 0.9109
3.750 0.5612 0.01124 0.00443 -0.0367 0.0111 0.9261
4.000 0.5843 0.01162 0.00490 -0.0355 0.0101 0.9463
4.250 0.6093 0.01229 0.00570 -0.0349 0.0093 1.0000
4.500 0.6368 0.01295 0.00643 -0.0349 0.0091 1.0000
4.750 0.6641 0.01366 0.00727 -0.0349 0.0089 1.0000
5.000 0.6911 0.01449 0.00821 -0.0348 0.0086 1.0000
5.250 0.7177 0.01550 0.00938 -0.0346 0.0082 1.0000
5.500 0.7439 0.01674 0.01081 -0.0343 0.0079 1.0000
5.750 0.7696 0.01831 0.01263 -0.0339 0.0076 1.0000
6.000 0.7944 0.02035 0.01500 -0.0334 0.0075 1.0000
6.250 0.8174 0.02324 0.01835 -0.0327 0.0074 1.0000
6.500 0.8367 0.02772 0.02344 -0.0316 0.0074 1.0000
6.750 0.8539 0.03250 0.02877 -0.0306 0.0070 1.0000
7.000 0.8686 0.03779 0.03449 -0.0298 0.0066 1.0000
7.250 0.8723 0.04809 0.04536 -0.0290 0.0065 1.0000
7.500 0.8769 0.05612 0.05373 -0.0296 0.0064 1.0000
7.750 0.8790 0.06376 0.06160 -0.0313 0.0064 1.0000
8.000 0.8778 0.07137 0.06938 -0.0344 0.0063 1.0000
8.250 0.8711 0.07989 0.07799 -0.0397 0.0064 1.0000
8.500 0.8585 0.08817 0.08631 -0.0475 0.0064 1.0000
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Polar data table (+)
Polar graphs
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