S8064 (s8064-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 100,000 Max Cl/Cd: 46.43 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8064-il-100000-n5.txt Download as CSV file: xf-s8064-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8064
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5239 0.09509 0.09012 -0.0475 1.0000 0.0206
-11.500 -0.5413 0.08517 0.08023 -0.0530 1.0000 0.0200
-11.250 -0.5718 0.07388 0.06890 -0.0612 1.0000 0.0194
-11.000 -0.6011 0.06633 0.06121 -0.0662 1.0000 0.0189
-10.750 -0.6297 0.06097 0.05570 -0.0679 1.0000 0.0187
-10.500 -0.6605 0.05714 0.05173 -0.0664 1.0000 0.0183
-10.250 -0.6919 0.05501 0.04947 -0.0617 1.0000 0.0181
-10.000 -0.7215 0.05381 0.04819 -0.0555 1.0000 0.0181
-9.750 -0.7495 0.05245 0.04669 -0.0488 1.0000 0.0180
-9.500 -0.7699 0.05049 0.04454 -0.0434 1.0000 0.0180
-9.250 -0.7712 0.04753 0.04127 -0.0418 0.9962 0.0182
-9.000 -0.7664 0.04414 0.03743 -0.0409 0.9915 0.0183
-8.750 -0.7567 0.04116 0.03405 -0.0400 0.9873 0.0186
-8.500 -0.7414 0.03837 0.03086 -0.0397 0.9842 0.0189
-8.250 -0.7271 0.03597 0.02810 -0.0385 0.9805 0.0195
-8.000 -0.7088 0.03381 0.02559 -0.0377 0.9772 0.0200
-7.750 -0.6868 0.03176 0.02323 -0.0374 0.9745 0.0208
-7.500 -0.6618 0.02992 0.02110 -0.0375 0.9723 0.0219
-7.250 -0.6421 0.02837 0.01938 -0.0366 0.9692 0.0235
-7.000 -0.6229 0.02739 0.01833 -0.0359 0.9655 0.0260
-6.750 -0.5995 0.02632 0.01706 -0.0356 0.9625 0.0298
-6.500 -0.5765 0.02505 0.01576 -0.0355 0.9597 0.0338
-6.250 -0.5554 0.02403 0.01466 -0.0347 0.9565 0.0412
-6.000 -0.5379 0.02325 0.01389 -0.0334 0.9522 0.0533
-5.750 -0.5151 0.02249 0.01313 -0.0331 0.9488 0.0715
-5.500 -0.4898 0.02168 0.01238 -0.0332 0.9459 0.0948
-5.250 -0.4686 0.02099 0.01178 -0.0326 0.9423 0.1220
-5.000 -0.4515 0.02036 0.01128 -0.0310 0.9376 0.1583
-4.750 -0.4288 0.01960 0.01077 -0.0308 0.9340 0.2179
-4.500 -0.4051 0.01873 0.01036 -0.0308 0.9312 0.3139
-4.250 -0.3929 0.01809 0.01016 -0.0281 0.9259 0.4120
-4.000 -0.3742 0.01764 0.01009 -0.0264 0.9215 0.5087
-3.750 -0.3477 0.01744 0.01013 -0.0259 0.9185 0.5889
-3.500 -0.3166 0.01751 0.01034 -0.0259 0.9163 0.6507
-3.250 -0.3034 0.01764 0.01046 -0.0227 0.9098 0.6886
-3.000 -0.2769 0.01780 0.01056 -0.0221 0.9059 0.7228
-2.750 -0.2460 0.01797 0.01062 -0.0223 0.9032 0.7511
-2.500 -0.2259 0.01815 0.01074 -0.0204 0.8980 0.7732
-2.250 -0.2037 0.01830 0.01082 -0.0190 0.8929 0.7945
-2.000 -0.1718 0.01849 0.01092 -0.0192 0.8899 0.8125
-1.750 -0.1380 0.01863 0.01097 -0.0200 0.8876 0.8277
-1.500 -0.1231 0.01874 0.01104 -0.0174 0.8801 0.8414
-1.250 -0.0931 0.01880 0.01102 -0.0177 0.8763 0.8534
-1.000 -0.0554 0.01888 0.01102 -0.0195 0.8739 0.8618
-0.750 -0.0351 0.01897 0.01108 -0.0181 0.8672 0.8723
-0.500 -0.0062 0.01900 0.01105 -0.0183 0.8626 0.8823
-0.250 0.0338 0.01905 0.01105 -0.0206 0.8600 0.8885
0.000 0.0564 0.01912 0.01110 -0.0198 0.8534 0.8983
0.250 0.0922 0.01918 0.01115 -0.0215 0.8488 0.9044
0.500 0.1262 0.01914 0.01109 -0.0227 0.8454 0.9123
0.750 0.1615 0.01923 0.01119 -0.0244 0.8401 0.9177
1.000 0.1910 0.01927 0.01124 -0.0250 0.8339 0.9255
1.250 0.2321 0.01920 0.01120 -0.0276 0.8306 0.9299
1.500 0.2635 0.01929 0.01133 -0.0287 0.8235 0.9364
1.750 0.2972 0.01922 0.01131 -0.0299 0.8179 0.9428
2.000 0.3416 0.01905 0.01121 -0.0330 0.8147 0.9458
2.250 0.3713 0.01911 0.01135 -0.0339 0.8048 0.9527
2.500 0.4109 0.01883 0.01116 -0.0359 0.8003 0.9572
2.750 0.4453 0.01877 0.01121 -0.0375 0.7897 0.9624
3.000 0.4789 0.01856 0.01110 -0.0386 0.7801 0.9686
3.250 0.5183 0.01808 0.01075 -0.0404 0.7718 0.9727
3.500 0.5533 0.01772 0.01051 -0.0416 0.7581 0.9781
3.750 0.5852 0.01736 0.01027 -0.0422 0.7410 0.9846
4.000 0.6209 0.01689 0.00993 -0.0433 0.7196 0.9898
4.250 0.6567 0.01638 0.00950 -0.0442 0.6929 0.9947
4.500 0.6938 0.01590 0.00900 -0.0452 0.6564 0.9987
5.000 0.7313 0.01575 0.00864 -0.0410 0.5609 1.0000
5.250 0.7420 0.01600 0.00864 -0.0376 0.4996 1.0000
5.500 0.7468 0.01649 0.00877 -0.0334 0.4299 1.0000
5.750 0.7482 0.01717 0.00906 -0.0288 0.3602 1.0000
6.000 0.7497 0.01797 0.00948 -0.0244 0.2945 1.0000
6.250 0.7530 0.01883 0.01001 -0.0205 0.2356 1.0000
6.500 0.7592 0.01970 0.01059 -0.0172 0.1877 1.0000
6.750 0.7681 0.02055 0.01123 -0.0143 0.1514 1.0000
7.000 0.7786 0.02138 0.01193 -0.0117 0.1262 1.0000
7.250 0.7896 0.02222 0.01269 -0.0092 0.1085 1.0000
7.500 0.8005 0.02304 0.01347 -0.0067 0.0950 1.0000
7.750 0.8118 0.02390 0.01436 -0.0043 0.0854 1.0000
8.000 0.8220 0.02490 0.01530 -0.0019 0.0777 1.0000
8.250 0.8359 0.02577 0.01627 0.0000 0.0696 1.0000
8.500 0.8479 0.02686 0.01737 0.0020 0.0634 1.0000
8.750 0.8623 0.02781 0.01841 0.0036 0.0565 1.0000
9.000 0.8756 0.02896 0.01959 0.0053 0.0506 1.0000
9.250 0.8894 0.02996 0.02070 0.0068 0.0446 1.0000
9.500 0.9027 0.03126 0.02207 0.0084 0.0400 1.0000
9.750 0.9175 0.03257 0.02352 0.0098 0.0361 1.0000
10.000 0.9298 0.03403 0.02500 0.0112 0.0334 1.0000
10.250 0.9461 0.03582 0.02699 0.0124 0.0308 1.0000
10.500 0.9595 0.03738 0.02877 0.0138 0.0282 1.0000
10.750 0.9696 0.03888 0.03037 0.0153 0.0264 1.0000
11.000 0.9794 0.04073 0.03229 0.0166 0.0252 1.0000
11.250 0.9896 0.04325 0.03510 0.0181 0.0242 1.0000
11.500 0.9958 0.04589 0.03810 0.0197 0.0235 1.0000
11.750 0.9966 0.04880 0.04135 0.0217 0.0229 1.0000
12.000 0.9926 0.05191 0.04480 0.0236 0.0224 1.0000
12.250 0.9850 0.05522 0.04841 0.0253 0.0221 1.0000
12.500 0.9735 0.05885 0.05234 0.0267 0.0219 1.0000
12.750 0.9594 0.06276 0.05651 0.0275 0.0216 1.0000
13.000 0.9420 0.06727 0.06128 0.0276 0.0215 1.0000
13.250 0.9226 0.07230 0.06656 0.0267 0.0215 1.0000
13.500 0.8991 0.07850 0.07300 0.0246 0.0218 1.0000
13.750 0.8719 0.08599 0.08069 0.0209 0.0218 1.0000
14.000 0.8424 0.09520 0.09009 0.0153 0.0223 1.0000
14.250 0.8096 0.10707 0.10209 0.0076 0.0229 1.0000
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