S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 100,000 Max Cl/Cd: 49.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8065-il-100000.txt Download as CSV file: xf-s8065-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3874 0.09738 0.09282 -0.0345 1.0000 0.1271
-10.000 -0.4031 0.09317 0.08867 -0.0374 1.0000 0.1331
-9.750 -0.4288 0.08782 0.08343 -0.0414 1.0000 0.1355
-9.500 -0.4054 0.08437 0.07995 -0.0385 1.0000 0.1385
-9.250 -0.4065 0.08040 0.07601 -0.0387 1.0000 0.1420
-9.000 -0.5096 0.08361 0.07903 -0.0403 1.0000 0.1392
-8.750 -0.5173 0.07977 0.07525 -0.0416 1.0000 0.1430
-7.250 -0.7077 0.04740 0.04095 -0.0252 1.0000 0.0547
-7.000 -0.6997 0.04511 0.03833 -0.0224 1.0000 0.0537
-6.750 -0.6934 0.04132 0.03427 -0.0200 1.0000 0.0530
-6.500 -0.6846 0.03789 0.03048 -0.0176 1.0000 0.0522
-6.250 -0.6728 0.03475 0.02692 -0.0152 1.0000 0.0515
-6.000 -0.6578 0.03205 0.02379 -0.0131 1.0000 0.0514
-5.750 -0.6400 0.02973 0.02103 -0.0111 1.0000 0.0522
-5.500 -0.6201 0.02797 0.01882 -0.0092 1.0000 0.0539
-5.250 -0.6006 0.02581 0.01672 -0.0082 1.0000 0.0600
-5.000 -0.5796 0.02432 0.01499 -0.0066 1.0000 0.0677
-4.750 -0.5598 0.02300 0.01363 -0.0051 1.0000 0.0797
-4.500 -0.5422 0.02156 0.01239 -0.0036 1.0000 0.0998
-4.250 -0.5247 0.02038 0.01136 -0.0020 1.0000 0.1305
-4.000 -0.5080 0.01915 0.01040 -0.0003 1.0000 0.1724
-3.750 -0.4938 0.01753 0.00952 0.0016 1.0000 0.2685
-3.500 -0.4864 0.01582 0.00934 0.0051 1.0000 0.5295
-3.250 -0.4756 0.01560 0.00971 0.0096 1.0000 0.6752
-3.000 -0.4629 0.01579 0.00994 0.0135 1.0000 0.7517
-2.750 -0.4497 0.01600 0.01016 0.0173 1.0000 0.8029
-2.500 -0.4357 0.01623 0.01035 0.0210 1.0000 0.8474
-2.250 -0.4156 0.01654 0.01059 0.0235 1.0000 0.8893
-2.000 -0.3740 0.01718 0.01104 0.0218 1.0000 0.9295
-1.750 -0.2958 0.01830 0.01186 0.0127 1.0000 0.9589
-1.500 -0.1996 0.01933 0.01255 -0.0004 1.0000 0.9816
-1.250 -0.1134 0.01985 0.01282 -0.0127 1.0000 0.9998
-1.000 -0.1177 0.01952 0.01243 -0.0091 1.0000 1.0000
-0.750 -0.0925 0.01955 0.01236 -0.0106 0.9951 1.0000
-0.500 -0.0555 0.01974 0.01244 -0.0141 0.9870 1.0000
-0.250 -0.0208 0.01997 0.01259 -0.0170 0.9788 1.0000
0.000 0.0179 0.02031 0.01285 -0.0205 0.9711 1.0000
0.250 0.0448 0.02046 0.01295 -0.0217 0.9613 1.0000
0.500 0.0752 0.02073 0.01318 -0.0234 0.9521 1.0000
0.750 0.1139 0.02109 0.01352 -0.0265 0.9441 1.0000
1.000 0.1376 0.02129 0.01369 -0.0268 0.9331 1.0000
1.250 0.1660 0.02157 0.01396 -0.0277 0.9229 1.0000
1.500 0.2113 0.02195 0.01437 -0.0316 0.9156 1.0000
1.750 0.2350 0.02215 0.01458 -0.0315 0.9037 1.0000
2.000 0.2621 0.02239 0.01484 -0.0319 0.8922 1.0000
2.250 0.2959 0.02262 0.01511 -0.0334 0.8816 1.0000
2.500 0.3476 0.02271 0.01533 -0.0378 0.8735 1.0000
2.750 0.3774 0.02278 0.01546 -0.0382 0.8608 1.0000
3.000 0.4123 0.02275 0.01552 -0.0394 0.8482 1.0000
3.250 0.4555 0.02251 0.01544 -0.0417 0.8357 1.0000
3.500 0.5049 0.02189 0.01500 -0.0445 0.8229 1.0000
3.750 0.5509 0.02094 0.01423 -0.0461 0.8084 1.0000
4.000 0.5934 0.01970 0.01320 -0.0465 0.7922 1.0000
4.250 0.6332 0.01828 0.01195 -0.0461 0.7748 1.0000
4.500 0.6562 0.01740 0.01120 -0.0435 0.7525 1.0000
4.750 0.6837 0.01638 0.01033 -0.0413 0.7269 1.0000
5.000 0.7087 0.01559 0.00961 -0.0389 0.6916 1.0000
5.250 0.7303 0.01514 0.00913 -0.0361 0.6395 1.0000
5.500 0.7471 0.01511 0.00881 -0.0326 0.5526 1.0000
5.750 0.7510 0.01601 0.00890 -0.0274 0.4039 1.0000
6.000 0.7453 0.01790 0.00969 -0.0218 0.2577 1.0000
6.250 0.7489 0.01965 0.01076 -0.0180 0.1890 1.0000
6.500 0.7610 0.02107 0.01191 -0.0154 0.1552 1.0000
6.750 0.7768 0.02248 0.01306 -0.0136 0.1333 1.0000
7.000 0.7985 0.02395 0.01445 -0.0125 0.1174 1.0000
7.250 0.8217 0.02550 0.01596 -0.0118 0.1033 1.0000
7.500 0.8470 0.02734 0.01777 -0.0115 0.0913 1.0000
7.750 0.8694 0.02900 0.01946 -0.0107 0.0798 1.0000
8.000 0.8897 0.03057 0.02133 -0.0093 0.0708 1.0000
8.250 0.9150 0.03365 0.02452 -0.0090 0.0649 1.0000
8.500 0.9323 0.03574 0.02705 -0.0071 0.0600 1.0000
8.750 0.9506 0.03788 0.02924 -0.0062 0.0554 1.0000
9.000 0.9648 0.04241 0.03412 -0.0048 0.0537 1.0000
9.250 0.9721 0.04552 0.03775 -0.0019 0.0532 1.0000
9.500 0.9765 0.04923 0.04189 0.0008 0.0531 1.0000
9.750 0.9785 0.05353 0.04656 0.0033 0.0535 1.0000
10.000 0.9810 0.05811 0.05143 0.0054 0.0541 1.0000
10.250 0.9765 0.06055 0.05426 0.0088 0.0547 1.0000
10.500 0.9671 0.06508 0.05902 0.0112 0.0543 1.0000
10.750 0.8972 0.06928 0.06397 0.0187 0.0618 1.0000
11.000 0.8757 0.07369 0.06852 0.0198 0.0630 1.0000
11.250 0.8612 0.07860 0.07351 0.0199 0.0644 1.0000
11.500 0.7345 0.07721 0.07255 0.0210 0.0630 1.0000
11.750 0.7098 0.08429 0.07969 0.0182 0.0642 1.0000
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Polar data table (+)
Polar graphs
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