S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 500,000 Max Cl/Cd: 80.53 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8065-il-500000.txt Download as CSV file: xf-s8065-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4224 0.13674 0.13464 -0.0161 1.0000 0.0178
-13.500 -0.4171 0.13417 0.13206 -0.0173 1.0000 0.0182
-13.250 -0.5331 0.13414 0.13179 -0.0179 1.0000 0.0172
-13.000 -0.5273 0.13123 0.12888 -0.0187 1.0000 0.0176
-12.750 -0.5217 0.12804 0.12570 -0.0199 1.0000 0.0180
-12.500 -0.5163 0.12486 0.12251 -0.0212 1.0000 0.0185
-12.250 -0.5140 0.12072 0.11839 -0.0230 1.0000 0.0188
-12.000 -0.5112 0.11684 0.11452 -0.0247 1.0000 0.0197
-8.500 -0.6464 0.02662 0.02169 -0.0601 0.9717 0.0121
-8.250 -0.6280 0.02408 0.01891 -0.0594 0.9675 0.0117
-8.000 -0.6102 0.02150 0.01604 -0.0583 0.9631 0.0115
-7.750 -0.5889 0.01964 0.01393 -0.0576 0.9597 0.0114
-7.500 -0.5673 0.01823 0.01233 -0.0567 0.9564 0.0115
-7.250 -0.5473 0.01713 0.01110 -0.0555 0.9523 0.0116
-7.000 -0.5261 0.01624 0.01008 -0.0545 0.9485 0.0118
-6.750 -0.5087 0.01494 0.00865 -0.0528 0.9448 0.0125
-6.500 -0.4893 0.01415 0.00779 -0.0514 0.9412 0.0133
-6.250 -0.4678 0.01363 0.00723 -0.0504 0.9373 0.0145
-6.000 -0.4457 0.01315 0.00667 -0.0494 0.9339 0.0159
-5.750 -0.4245 0.01256 0.00599 -0.0481 0.9308 0.0183
-5.500 -0.4024 0.01206 0.00550 -0.0472 0.9275 0.0267
-5.250 -0.3806 0.01151 0.00507 -0.0462 0.9237 0.0502
-5.000 -0.3570 0.01118 0.00478 -0.0455 0.9203 0.0684
-4.750 -0.3337 0.01085 0.00453 -0.0447 0.9173 0.0918
-4.500 -0.3110 0.01046 0.00429 -0.0440 0.9144 0.1313
-4.250 -0.2891 0.00993 0.00406 -0.0432 0.9103 0.1963
-4.000 -0.2677 0.00939 0.00382 -0.0423 0.9066 0.2765
-3.750 -0.2471 0.00881 0.00360 -0.0411 0.9033 0.3712
-3.500 -0.2256 0.00838 0.00346 -0.0401 0.9001 0.4586
-3.250 -0.2029 0.00805 0.00336 -0.0392 0.8958 0.5289
-3.000 -0.1795 0.00778 0.00326 -0.0383 0.8920 0.5855
-2.750 -0.1555 0.00757 0.00319 -0.0374 0.8890 0.6324
-2.500 -0.1308 0.00746 0.00317 -0.0366 0.8857 0.6733
-2.250 -0.1054 0.00739 0.00317 -0.0360 0.8812 0.7061
-2.000 -0.0794 0.00734 0.00314 -0.0355 0.8775 0.7302
-1.750 -0.0531 0.00731 0.00310 -0.0350 0.8743 0.7505
-1.500 -0.0267 0.00730 0.00309 -0.0345 0.8705 0.7682
-1.250 -0.0004 0.00728 0.00309 -0.0341 0.8658 0.7832
-1.000 0.0261 0.00724 0.00305 -0.0336 0.8619 0.7974
-0.750 0.0528 0.00721 0.00301 -0.0331 0.8588 0.8111
-0.500 0.0788 0.00719 0.00303 -0.0326 0.8533 0.8234
-0.250 0.1054 0.00713 0.00300 -0.0322 0.8487 0.8345
0.000 0.1325 0.00708 0.00293 -0.0318 0.8449 0.8444
0.250 0.1588 0.00704 0.00293 -0.0314 0.8387 0.8539
0.500 0.1857 0.00696 0.00286 -0.0310 0.8333 0.8617
0.750 0.2127 0.00690 0.00279 -0.0306 0.8278 0.8703
1.000 0.2392 0.00681 0.00275 -0.0301 0.8204 0.8779
1.250 0.2662 0.00672 0.00266 -0.0298 0.8139 0.8859
1.500 0.2926 0.00663 0.00260 -0.0293 0.8050 0.8937
1.750 0.3192 0.00655 0.00254 -0.0289 0.7959 0.9014
2.000 0.3458 0.00646 0.00247 -0.0284 0.7857 0.9094
2.250 0.3726 0.00639 0.00241 -0.0280 0.7734 0.9171
2.500 0.3987 0.00634 0.00238 -0.0274 0.7580 0.9260
2.750 0.4263 0.00632 0.00236 -0.0272 0.7386 0.9334
3.000 0.4529 0.00636 0.00235 -0.0268 0.7169 0.9424
3.250 0.4832 0.00646 0.00241 -0.0272 0.6927 0.9490
3.500 0.5120 0.00660 0.00248 -0.0274 0.6648 0.9572
3.750 0.5443 0.00682 0.00261 -0.0284 0.6293 0.9628
4.000 0.5734 0.00712 0.00275 -0.0288 0.5815 0.9708
4.250 0.6064 0.00758 0.00296 -0.0302 0.5150 0.9754
4.500 0.6357 0.00822 0.00325 -0.0311 0.4315 0.9828
4.750 0.6670 0.00916 0.00367 -0.0328 0.3175 0.9879
5.000 0.6978 0.01004 0.00412 -0.0344 0.2232 0.9942
5.250 0.7319 0.01085 0.00456 -0.0366 0.1491 0.9986
5.500 0.7489 0.01138 0.00489 -0.0351 0.1106 1.0000
5.750 0.7607 0.01181 0.00522 -0.0324 0.0882 1.0000
6.000 0.7760 0.01224 0.00556 -0.0302 0.0719 1.0000
6.250 0.7933 0.01264 0.00592 -0.0284 0.0611 1.0000
6.500 0.8104 0.01310 0.00634 -0.0266 0.0528 1.0000
6.750 0.8298 0.01344 0.00669 -0.0251 0.0470 1.0000
7.000 0.8473 0.01396 0.00722 -0.0234 0.0414 1.0000
7.250 0.8677 0.01429 0.00758 -0.0222 0.0367 1.0000
7.500 0.8845 0.01493 0.00822 -0.0204 0.0313 1.0000
7.750 0.9042 0.01536 0.00865 -0.0191 0.0258 1.0000
8.000 0.9205 0.01608 0.00941 -0.0173 0.0216 1.0000
8.250 0.9387 0.01663 0.00998 -0.0158 0.0188 1.0000
8.500 0.9487 0.01788 0.01130 -0.0130 0.0168 1.0000
8.750 0.9664 0.01847 0.01198 -0.0114 0.0160 1.0000
9.000 0.9817 0.01917 0.01276 -0.0095 0.0150 1.0000
9.250 0.9955 0.01998 0.01364 -0.0073 0.0143 1.0000
9.500 1.0090 0.02082 0.01455 -0.0053 0.0136 1.0000
9.750 1.0218 0.02177 0.01556 -0.0032 0.0130 1.0000
10.000 1.0322 0.02329 0.01718 -0.0010 0.0124 1.0000
10.250 1.0436 0.02505 0.01911 0.0011 0.0118 1.0000
10.500 1.0572 0.02606 0.02028 0.0028 0.0114 1.0000
10.750 1.0691 0.02752 0.02190 0.0047 0.0112 1.0000
11.000 1.0793 0.02906 0.02362 0.0066 0.0109 1.0000
11.250 1.0873 0.03084 0.02559 0.0087 0.0107 1.0000
11.500 1.0929 0.03276 0.02772 0.0109 0.0105 1.0000
11.750 1.0968 0.03452 0.02965 0.0131 0.0102 1.0000
12.000 1.0964 0.03689 0.03225 0.0154 0.0101 1.0000
12.250 1.0951 0.03908 0.03463 0.0176 0.0099 1.0000
12.500 1.0847 0.04248 0.03831 0.0199 0.0100 1.0000
12.750 1.0818 0.04471 0.04068 0.0214 0.0097 1.0000
13.000 1.0655 0.04877 0.04501 0.0228 0.0098 1.0000
13.250 1.0474 0.05320 0.04968 0.0234 0.0098 1.0000
13.500 1.0326 0.05748 0.05415 0.0231 0.0097 1.0000
13.750 1.0154 0.06250 0.05936 0.0219 0.0096 1.0000
14.000 0.9664 0.07351 0.07075 0.0169 0.0101 1.0000
14.250 0.9424 0.08175 0.07916 0.0119 0.0101 1.0000
14.500 0.9062 0.09446 0.09207 0.0033 0.0104 1.0000
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