S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.81 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8065-il-1000000.txt Download as CSV file: xf-s8065-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S8065 (11% version of S8064)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7451 0.03602 0.03335 -0.0640 0.9568 0.0072
-10.000 -0.7683 0.03174 0.02861 -0.0589 0.9431 0.0070
-9.750 -0.7650 0.02960 0.02624 -0.0565 0.9368 0.0071
-9.500 -0.7712 0.02545 0.02157 -0.0525 0.9303 0.0068
-9.250 -0.7664 0.02198 0.01762 -0.0496 0.9257 0.0064
-9.000 -0.7502 0.02049 0.01593 -0.0482 0.9221 0.0064
-8.750 -0.7322 0.01923 0.01449 -0.0470 0.9189 0.0065
-8.500 -0.7144 0.01784 0.01290 -0.0456 0.9158 0.0065
-8.250 -0.6930 0.01698 0.01193 -0.0448 0.9133 0.0066
-8.000 -0.6706 0.01628 0.01115 -0.0442 0.9107 0.0069
-7.750 -0.6492 0.01537 0.01013 -0.0433 0.9079 0.0070
-7.500 -0.6284 0.01443 0.00905 -0.0422 0.9052 0.0070
-7.250 -0.6069 0.01365 0.00817 -0.0412 0.9027 0.0070
-7.000 -0.5844 0.01297 0.00740 -0.0404 0.9002 0.0072
-6.750 -0.5611 0.01235 0.00669 -0.0398 0.8978 0.0074
-6.500 -0.5372 0.01182 0.00609 -0.0392 0.8952 0.0077
-6.250 -0.5127 0.01137 0.00557 -0.0387 0.8928 0.0082
-6.000 -0.4887 0.01087 0.00499 -0.0380 0.8904 0.0087
-5.750 -0.4645 0.01041 0.00446 -0.0374 0.8880 0.0098
-5.500 -0.4387 0.01012 0.00414 -0.0372 0.8857 0.0112
-5.250 -0.4132 0.00973 0.00374 -0.0368 0.8832 0.0154
-5.000 -0.3884 0.00930 0.00341 -0.0364 0.8806 0.0334
-4.750 -0.3628 0.00899 0.00317 -0.0361 0.8780 0.0496
-4.500 -0.3369 0.00873 0.00297 -0.0359 0.8756 0.0664
-4.250 -0.3112 0.00847 0.00278 -0.0356 0.8730 0.0899
-4.000 -0.2852 0.00817 0.00259 -0.0354 0.8705 0.1204
-3.750 -0.2599 0.00779 0.00241 -0.0352 0.8675 0.1656
-3.500 -0.2354 0.00734 0.00221 -0.0348 0.8645 0.2341
-3.250 -0.2116 0.00684 0.00200 -0.0343 0.8617 0.3194
-3.000 -0.1873 0.00642 0.00186 -0.0338 0.8588 0.4008
-2.750 -0.1622 0.00606 0.00175 -0.0335 0.8558 0.4730
-2.500 -0.1364 0.00579 0.00165 -0.0332 0.8524 0.5309
-2.250 -0.1100 0.00559 0.00156 -0.0330 0.8492 0.5723
-2.000 -0.0836 0.00540 0.00148 -0.0327 0.8461 0.6138
-1.750 -0.0571 0.00526 0.00145 -0.0325 0.8429 0.6532
-1.500 -0.0302 0.00514 0.00142 -0.0323 0.8391 0.6869
-1.250 -0.0028 0.00506 0.00140 -0.0321 0.8352 0.7132
-1.000 0.0248 0.00501 0.00137 -0.0320 0.8316 0.7325
-0.750 0.0526 0.00498 0.00136 -0.0320 0.8274 0.7484
-0.500 0.0805 0.00493 0.00133 -0.0320 0.8224 0.7618
-0.250 0.1082 0.00489 0.00130 -0.0319 0.8176 0.7745
0.000 0.1361 0.00486 0.00129 -0.0318 0.8120 0.7861
0.250 0.1640 0.00482 0.00126 -0.0318 0.8053 0.7968
0.500 0.1916 0.00478 0.00124 -0.0317 0.7984 0.8058
0.750 0.2195 0.00475 0.00122 -0.0317 0.7899 0.8140
1.000 0.2473 0.00473 0.00121 -0.0316 0.7801 0.8215
1.250 0.2750 0.00471 0.00119 -0.0316 0.7686 0.8285
1.500 0.3024 0.00471 0.00118 -0.0314 0.7543 0.8354
1.750 0.3297 0.00474 0.00118 -0.0313 0.7375 0.8423
2.000 0.3562 0.00480 0.00120 -0.0310 0.7176 0.8491
2.250 0.3828 0.00489 0.00123 -0.0307 0.6937 0.8560
2.500 0.4087 0.00500 0.00128 -0.0303 0.6684 0.8628
2.750 0.4346 0.00514 0.00135 -0.0299 0.6407 0.8702
3.000 0.4600 0.00527 0.00144 -0.0295 0.6130 0.8776
3.250 0.4849 0.00546 0.00154 -0.0290 0.5787 0.8857
3.500 0.5081 0.00573 0.00167 -0.0281 0.5310 0.8947
3.750 0.5303 0.00608 0.00184 -0.0271 0.4727 0.9047
4.000 0.5517 0.00648 0.00203 -0.0260 0.4089 0.9165
4.250 0.5714 0.00702 0.00229 -0.0247 0.3319 0.9308
4.500 0.5937 0.00752 0.00256 -0.0238 0.2655 0.9468
4.750 0.6210 0.00806 0.00287 -0.0242 0.2050 0.9611
5.000 0.6517 0.00859 0.00318 -0.0253 0.1544 0.9727
5.500 0.7168 0.00962 0.00384 -0.0284 0.0792 0.9885
6.000 0.7859 0.01037 0.00446 -0.0321 0.0502 0.9977
6.250 0.8173 0.01073 0.00478 -0.0333 0.0417 1.0000
6.500 0.8359 0.01097 0.00501 -0.0317 0.0380 1.0000
6.750 0.8541 0.01133 0.00535 -0.0300 0.0321 1.0000
7.000 0.8751 0.01153 0.00558 -0.0288 0.0297 1.0000
7.250 0.8941 0.01192 0.00592 -0.0273 0.0240 1.0000
7.500 0.9147 0.01220 0.00620 -0.0261 0.0205 1.0000
7.750 0.9335 0.01266 0.00664 -0.0246 0.0155 1.0000
8.000 0.9522 0.01315 0.00712 -0.0231 0.0127 1.0000
8.250 0.9710 0.01367 0.00770 -0.0215 0.0115 1.0000
8.500 0.9907 0.01411 0.00819 -0.0202 0.0108 1.0000
8.750 1.0102 0.01456 0.00868 -0.0190 0.0100 1.0000
9.000 1.0283 0.01513 0.00927 -0.0175 0.0092 1.0000
9.250 1.0414 0.01608 0.01032 -0.0152 0.0085 1.0000
9.500 1.0582 0.01671 0.01102 -0.0135 0.0082 1.0000
9.750 1.0746 0.01724 0.01161 -0.0117 0.0079 1.0000
10.000 1.0880 0.01790 0.01236 -0.0095 0.0077 1.0000
10.250 1.1016 0.01856 0.01310 -0.0073 0.0075 1.0000
10.500 1.1142 0.01933 0.01394 -0.0052 0.0071 1.0000
10.750 1.1258 0.02019 0.01490 -0.0029 0.0071 1.0000
11.000 1.1381 0.02103 0.01581 -0.0009 0.0068 1.0000
11.250 1.1491 0.02198 0.01684 0.0011 0.0067 1.0000
11.500 1.1595 0.02299 0.01795 0.0032 0.0066 1.0000
11.750 1.1696 0.02399 0.01902 0.0051 0.0063 1.0000
12.000 1.1766 0.02530 0.02044 0.0073 0.0062 1.0000
12.250 1.1777 0.02716 0.02245 0.0100 0.0059 1.0000
12.500 1.1760 0.02935 0.02483 0.0127 0.0058 1.0000
12.750 1.1652 0.03256 0.02831 0.0158 0.0056 1.0000
13.000 1.1654 0.03459 0.03049 0.0177 0.0056 1.0000
13.250 1.1740 0.03572 0.03171 0.0188 0.0055 1.0000
13.500 1.1814 0.03702 0.03311 0.0198 0.0054 1.0000
13.750 1.1798 0.03934 0.03558 0.0211 0.0053 1.0000
14.000 1.1814 0.04140 0.03775 0.0219 0.0052 1.0000
14.250 1.1742 0.04455 0.04106 0.0227 0.0051 1.0000
14.500 1.1642 0.04823 0.04492 0.0229 0.0051 1.0000
14.750 1.1562 0.05190 0.04873 0.0225 0.0050 1.0000
15.000 1.1480 0.05588 0.05285 0.0216 0.0050 1.0000
15.250 1.1319 0.06137 0.05852 0.0197 0.0050 1.0000
15.500 1.1253 0.06589 0.06316 0.0176 0.0049 1.0000
15.750 1.0943 0.07506 0.07255 0.0128 0.0050 1.0000
16.000 1.0680 0.08444 0.08211 0.0073 0.0050 1.0000
16.250 1.0450 0.09405 0.09189 0.0014 0.0049 1.0000
16.500 1.0185 0.10488 0.10286 -0.0051 0.0051 1.0000
16.750 0.9814 0.11903 0.11717 -0.0132 0.0052 1.0000
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Polar data table (+)
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