S6061 9% (s6061-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 500,000 Max Cl/Cd: 77.29 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6061-il-500000-n5.txt Download as CSV file: xf-s6061-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6061 9%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5251 0.08293 0.08075 -0.0181 1.0000 0.0054
-9.000 -0.5302 0.07725 0.07510 -0.0214 1.0000 0.0057
-8.750 -0.5405 0.07130 0.06920 -0.0257 1.0000 0.0052
-8.500 -0.5539 0.06426 0.06220 -0.0326 1.0000 0.0056
-8.250 -0.5696 0.05605 0.05389 -0.0386 1.0000 0.0050
-8.000 -0.5774 0.04830 0.04594 -0.0415 1.0000 0.0050
-7.750 -0.5838 0.04033 0.03765 -0.0423 1.0000 0.0050
-7.500 -0.5810 0.03418 0.03111 -0.0420 0.9976 0.0053
-7.250 -0.5613 0.02828 0.02463 -0.0440 0.9827 0.0054
-7.000 -0.5379 0.02427 0.02009 -0.0451 0.9715 0.0054
-6.750 -0.5141 0.02122 0.01656 -0.0454 0.9605 0.0054
-6.500 -0.4899 0.01905 0.01402 -0.0453 0.9499 0.0054
-6.250 -0.4660 0.01738 0.01202 -0.0447 0.9398 0.0055
-6.000 -0.4425 0.01606 0.01045 -0.0440 0.9297 0.0056
-5.750 -0.4188 0.01497 0.00916 -0.0432 0.9194 0.0057
-5.500 -0.3948 0.01404 0.00806 -0.0424 0.9099 0.0058
-5.250 -0.3705 0.01329 0.00716 -0.0417 0.9007 0.0060
-5.000 -0.3459 0.01254 0.00629 -0.0410 0.8911 0.0062
-4.750 -0.3220 0.01158 0.00516 -0.0403 0.8819 0.0068
-4.250 -0.2706 0.01066 0.00406 -0.0394 0.8634 0.0081
-4.000 -0.2442 0.01036 0.00369 -0.0391 0.8544 0.0093
-3.750 -0.2177 0.01007 0.00329 -0.0387 0.8453 0.0102
-3.500 -0.1909 0.00973 0.00285 -0.0384 0.8357 0.0122
-3.250 -0.1643 0.00941 0.00253 -0.0381 0.8266 0.0218
-3.000 -0.1379 0.00908 0.00227 -0.0379 0.8171 0.0492
-2.750 -0.1115 0.00868 0.00205 -0.0378 0.8071 0.0989
-2.500 -0.0850 0.00835 0.00187 -0.0376 0.7974 0.1509
-2.250 -0.0590 0.00792 0.00169 -0.0375 0.7874 0.2336
-2.000 -0.0325 0.00761 0.00156 -0.0374 0.7766 0.2990
-1.750 -0.0062 0.00726 0.00144 -0.0373 0.7656 0.3802
-1.500 0.0201 0.00695 0.00134 -0.0371 0.7540 0.4597
-1.250 0.0462 0.00666 0.00125 -0.0368 0.7420 0.5412
-1.000 0.0722 0.00643 0.00121 -0.0364 0.7298 0.6169
-0.750 0.0982 0.00626 0.00119 -0.0359 0.7173 0.6793
-0.500 0.1245 0.00617 0.00118 -0.0355 0.7045 0.7261
-0.250 0.1510 0.00611 0.00117 -0.0351 0.6915 0.7627
0.000 0.1774 0.00608 0.00118 -0.0346 0.6781 0.7941
0.250 0.2037 0.00608 0.00119 -0.0341 0.6641 0.8213
0.500 0.2299 0.00609 0.00120 -0.0336 0.6496 0.8451
0.750 0.2559 0.00612 0.00122 -0.0330 0.6350 0.8671
1.000 0.2817 0.00615 0.00125 -0.0324 0.6206 0.8888
1.500 0.3344 0.00624 0.00132 -0.0314 0.5906 0.9312
1.750 0.3641 0.00631 0.00136 -0.0317 0.5740 0.9498
2.000 0.3967 0.00641 0.00140 -0.0327 0.5547 0.9656
2.250 0.4311 0.00653 0.00146 -0.0341 0.5339 0.9786
2.500 0.4659 0.00666 0.00151 -0.0357 0.5115 0.9892
2.750 0.5001 0.00682 0.00159 -0.0373 0.4876 0.9989
3.000 0.5259 0.00700 0.00168 -0.0370 0.4638 1.0000
3.250 0.5508 0.00721 0.00181 -0.0365 0.4370 1.0000
3.500 0.5758 0.00745 0.00195 -0.0361 0.4076 1.0000
3.750 0.6004 0.00779 0.00211 -0.0356 0.3677 1.0000
4.000 0.6238 0.00830 0.00234 -0.0351 0.3055 1.0000
4.250 0.6476 0.00880 0.00261 -0.0346 0.2521 1.0000
4.500 0.6715 0.00932 0.00289 -0.0342 0.2024 1.0000
4.750 0.6961 0.00975 0.00316 -0.0339 0.1654 1.0000
5.250 0.7452 0.01063 0.00380 -0.0332 0.1050 1.0000
5.500 0.7691 0.01118 0.00418 -0.0327 0.0718 1.0000
5.750 0.7921 0.01184 0.00466 -0.0322 0.0373 1.0000
6.000 0.8156 0.01244 0.00515 -0.0317 0.0186 1.0000
6.250 0.8405 0.01284 0.00557 -0.0313 0.0156 1.0000
6.500 0.8652 0.01324 0.00602 -0.0309 0.0144 1.0000
6.750 0.8896 0.01370 0.00655 -0.0304 0.0134 1.0000
7.000 0.9136 0.01419 0.00712 -0.0299 0.0126 1.0000
7.250 0.9366 0.01481 0.00782 -0.0293 0.0119 1.0000
7.500 0.9586 0.01555 0.00866 -0.0285 0.0114 1.0000
7.750 0.9810 0.01617 0.00937 -0.0278 0.0112 1.0000
8.000 1.0031 0.01682 0.01010 -0.0271 0.0109 1.0000
8.250 1.0249 0.01747 0.01084 -0.0264 0.0104 1.0000
8.500 1.0458 0.01821 0.01169 -0.0256 0.0099 1.0000
8.750 1.0655 0.01905 0.01263 -0.0246 0.0096 1.0000
9.000 1.0844 0.01996 0.01364 -0.0235 0.0093 1.0000
9.250 1.1029 0.02087 0.01465 -0.0224 0.0089 1.0000
9.500 1.1207 0.02180 0.01567 -0.0213 0.0085 1.0000
9.750 1.1381 0.02271 0.01666 -0.0201 0.0081 1.0000
10.000 1.1530 0.02384 0.01787 -0.0188 0.0077 1.0000
10.250 1.1592 0.02602 0.02024 -0.0165 0.0071 1.0000
10.500 1.1727 0.02713 0.02149 -0.0149 0.0069 1.0000
10.750 1.1834 0.02819 0.02269 -0.0129 0.0068 1.0000
11.000 1.1925 0.02928 0.02392 -0.0108 0.0066 1.0000
11.250 1.2002 0.03050 0.02529 -0.0088 0.0063 1.0000
11.500 1.2054 0.03204 0.02699 -0.0069 0.0060 1.0000
11.750 1.2112 0.03345 0.02854 -0.0053 0.0057 1.0000
12.000 1.2142 0.03525 0.03049 -0.0038 0.0055 1.0000
12.250 1.2181 0.03695 0.03231 -0.0027 0.0052 1.0000
12.500 1.2233 0.03854 0.03400 -0.0020 0.0050 1.0000
12.750 1.2299 0.04003 0.03555 -0.0016 0.0047 1.0000
13.000 1.2266 0.04293 0.03862 -0.0012 0.0047 1.0000
13.250 1.2275 0.04539 0.04120 -0.0014 0.0046 1.0000
13.500 1.2275 0.04811 0.04402 -0.0019 0.0044 1.0000
13.750 1.2179 0.05241 0.04851 -0.0029 0.0044 1.0000
14.000 1.2092 0.05680 0.05303 -0.0046 0.0042 1.0000
14.250 1.1960 0.06221 0.05861 -0.0069 0.0042 1.0000
14.500 1.1816 0.06824 0.06481 -0.0099 0.0042 1.0000
14.750 1.1659 0.07491 0.07165 -0.0135 0.0042 1.0000
15.000 1.1507 0.08200 0.07891 -0.0176 0.0042 1.0000
15.250 1.1307 0.09047 0.08754 -0.0225 0.0042 1.0000
15.500 1.1148 0.09867 0.09591 -0.0275 0.0042 1.0000
15.750 1.0958 0.10777 0.10514 -0.0329 0.0042 1.0000
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Polar data table (+)
Polar graphs
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