S8064 (s8064-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 200,000 Max Cl/Cd: 55.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8064-il-200000-n5.txt Download as CSV file: xf-s8064-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5976 0.08891 0.08531 -0.0460 1.0000 0.0094
-12.500 -0.6262 0.07646 0.07277 -0.0543 1.0000 0.0092
-12.250 -0.6423 0.06874 0.06496 -0.0601 1.0000 0.0091
-12.000 -0.6674 0.06081 0.05685 -0.0659 1.0000 0.0090
-11.750 -0.6898 0.05491 0.05075 -0.0692 1.0000 0.0090
-11.500 -0.7064 0.05075 0.04641 -0.0703 1.0000 0.0090
-11.250 -0.7254 0.04721 0.04268 -0.0697 1.0000 0.0090
-11.000 -0.7396 0.04458 0.03987 -0.0682 0.9957 0.0089
-10.750 -0.7444 0.04065 0.03554 -0.0691 0.9848 0.0090
-10.500 -0.7428 0.03746 0.03196 -0.0690 0.9771 0.0090
-10.250 -0.7349 0.03470 0.02881 -0.0688 0.9721 0.0091
-10.000 -0.7270 0.03228 0.02601 -0.0675 0.9666 0.0093
-9.750 -0.7125 0.03037 0.02378 -0.0669 0.9626 0.0094
-9.500 -0.6955 0.02834 0.02150 -0.0665 0.9594 0.0096
-9.250 -0.6791 0.02689 0.01990 -0.0658 0.9557 0.0100
-9.000 -0.6618 0.02573 0.01859 -0.0649 0.9521 0.0102
-8.750 -0.6424 0.02482 0.01756 -0.0643 0.9488 0.0111
-8.500 -0.6212 0.02385 0.01642 -0.0639 0.9461 0.0119
-8.250 -0.6011 0.02283 0.01521 -0.0631 0.9434 0.0126
-8.000 -0.5855 0.02183 0.01411 -0.0615 0.9394 0.0130
-7.750 -0.5683 0.02091 0.01312 -0.0602 0.9358 0.0136
-7.500 -0.5487 0.02014 0.01224 -0.0592 0.9329 0.0144
-7.250 -0.5283 0.01940 0.01138 -0.0582 0.9304 0.0158
-7.000 -0.5109 0.01880 0.01067 -0.0567 0.9267 0.0172
-6.750 -0.4928 0.01813 0.00996 -0.0553 0.9231 0.0204
-6.500 -0.4730 0.01752 0.00932 -0.0541 0.9201 0.0264
-6.250 -0.4516 0.01698 0.00877 -0.0533 0.9176 0.0379
-6.000 -0.4307 0.01653 0.00834 -0.0523 0.9148 0.0511
-5.750 -0.4121 0.01610 0.00801 -0.0510 0.9109 0.0711
-5.500 -0.3918 0.01564 0.00766 -0.0500 0.9075 0.0953
-5.250 -0.3701 0.01521 0.00728 -0.0491 0.9047 0.1208
-5.000 -0.3480 0.01476 0.00692 -0.0483 0.9024 0.1554
-4.750 -0.3298 0.01433 0.00667 -0.0469 0.8984 0.1992
-4.500 -0.3119 0.01383 0.00640 -0.0455 0.8943 0.2591
-4.250 -0.2934 0.01327 0.00614 -0.0440 0.8910 0.3345
-4.000 -0.2742 0.01273 0.00590 -0.0426 0.8884 0.4176
-3.750 -0.2561 0.01239 0.00581 -0.0409 0.8844 0.4867
-3.500 -0.2364 0.01215 0.00575 -0.0393 0.8801 0.5432
-3.250 -0.2139 0.01193 0.00570 -0.0382 0.8769 0.5938
-3.000 -0.1892 0.01180 0.00568 -0.0373 0.8745 0.6378
-2.750 -0.1647 0.01178 0.00572 -0.0364 0.8715 0.6747
-2.500 -0.1427 0.01184 0.00580 -0.0351 0.8666 0.7026
-2.250 -0.1175 0.01185 0.00579 -0.0344 0.8631 0.7249
-2.000 -0.0910 0.01185 0.00576 -0.0339 0.8604 0.7444
-1.750 -0.0639 0.01184 0.00572 -0.0335 0.8582 0.7620
-1.500 -0.0425 0.01194 0.00582 -0.0322 0.8521 0.7762
-1.250 -0.0164 0.01194 0.00582 -0.0316 0.8484 0.7877
-1.000 0.0112 0.01190 0.00574 -0.0314 0.8455 0.7976
-0.750 0.0373 0.01188 0.00570 -0.0309 0.8420 0.8071
-0.500 0.0611 0.01192 0.00575 -0.0301 0.8362 0.8146
-0.250 0.0877 0.01186 0.00566 -0.0298 0.8324 0.8232
0.000 0.1168 0.01178 0.00559 -0.0298 0.8297 0.8293
0.250 0.1395 0.01182 0.00563 -0.0289 0.8232 0.8374
0.500 0.1665 0.01177 0.00560 -0.0286 0.8186 0.8432
0.750 0.1950 0.01166 0.00549 -0.0285 0.8153 0.8499
1.000 0.2186 0.01167 0.00555 -0.0277 0.8083 0.8562
1.250 0.2458 0.01159 0.00549 -0.0275 0.8032 0.8623
1.500 0.2729 0.01148 0.00540 -0.0272 0.7981 0.8688
1.750 0.2979 0.01144 0.00542 -0.0266 0.7900 0.8745
2.000 0.3251 0.01131 0.00533 -0.0263 0.7837 0.8812
2.250 0.3511 0.01123 0.00530 -0.0258 0.7744 0.8869
2.500 0.3768 0.01113 0.00526 -0.0253 0.7642 0.8936
2.750 0.4046 0.01099 0.00517 -0.0250 0.7536 0.8998
3.000 0.4337 0.01084 0.00506 -0.0250 0.7409 0.9056
3.250 0.4614 0.01070 0.00494 -0.0247 0.7251 0.9128
3.500 0.4928 0.01058 0.00483 -0.0251 0.7051 0.9178
3.750 0.5220 0.01052 0.00473 -0.0251 0.6794 0.9244
4.000 0.5519 0.01056 0.00467 -0.0253 0.6456 0.9301
4.250 0.5807 0.01072 0.00473 -0.0254 0.6055 0.9362
4.500 0.6067 0.01100 0.00484 -0.0251 0.5570 0.9434
4.750 0.6330 0.01146 0.00505 -0.0251 0.4956 0.9499
5.000 0.6551 0.01209 0.00537 -0.0245 0.4215 0.9585
5.250 0.6769 0.01295 0.00585 -0.0242 0.3370 0.9675
5.500 0.7000 0.01387 0.00640 -0.0243 0.2578 0.9769
5.750 0.7251 0.01474 0.00696 -0.0249 0.1935 0.9865
6.000 0.7520 0.01556 0.00754 -0.0258 0.1456 0.9957
6.250 0.7684 0.01615 0.00800 -0.0244 0.1174 1.0000
6.500 0.7771 0.01659 0.00838 -0.0213 0.1006 1.0000
6.750 0.7880 0.01707 0.00881 -0.0185 0.0876 1.0000
7.000 0.8000 0.01760 0.00930 -0.0159 0.0773 1.0000
7.250 0.8128 0.01810 0.00981 -0.0135 0.0686 1.0000
7.500 0.8251 0.01865 0.01038 -0.0111 0.0618 1.0000
7.750 0.8381 0.01924 0.01096 -0.0088 0.0549 1.0000
8.000 0.8529 0.01979 0.01154 -0.0070 0.0482 1.0000
8.250 0.8663 0.02048 0.01219 -0.0050 0.0421 1.0000
8.500 0.8824 0.02105 0.01285 -0.0034 0.0376 1.0000
8.750 0.8963 0.02180 0.01361 -0.0016 0.0335 1.0000
9.000 0.9113 0.02252 0.01442 0.0000 0.0295 1.0000
9.250 0.9257 0.02331 0.01522 0.0015 0.0255 1.0000
9.500 0.9382 0.02427 0.01627 0.0034 0.0231 1.0000
9.750 0.9514 0.02521 0.01730 0.0051 0.0209 1.0000
10.000 0.9632 0.02625 0.01839 0.0068 0.0192 1.0000
10.250 0.9731 0.02753 0.01975 0.0087 0.0181 1.0000
10.500 0.9849 0.02874 0.02110 0.0104 0.0171 1.0000
10.750 0.9963 0.02999 0.02249 0.0120 0.0162 1.0000
11.000 1.0078 0.03114 0.02374 0.0134 0.0152 1.0000
11.250 1.0177 0.03243 0.02512 0.0149 0.0145 1.0000
11.500 1.0249 0.03398 0.02671 0.0164 0.0138 1.0000
11.750 1.0343 0.03555 0.02848 0.0179 0.0133 1.0000
12.000 1.0418 0.03734 0.03047 0.0194 0.0129 1.0000
12.250 1.0481 0.03924 0.03256 0.0209 0.0125 1.0000
12.500 1.0524 0.04133 0.03485 0.0223 0.0122 1.0000
12.750 1.0550 0.04354 0.03725 0.0236 0.0118 1.0000
13.000 1.0555 0.04600 0.03991 0.0249 0.0116 1.0000
13.250 1.0542 0.04861 0.04275 0.0258 0.0114 1.0000
13.500 1.0504 0.05162 0.04597 0.0266 0.0113 1.0000
13.750 1.0448 0.05481 0.04934 0.0270 0.0111 1.0000
14.000 1.0371 0.05842 0.05317 0.0271 0.0110 1.0000
14.250 1.0272 0.06248 0.05742 0.0266 0.0109 1.0000
14.500 1.0143 0.06725 0.06241 0.0254 0.0109 1.0000
14.750 1.0004 0.07250 0.06786 0.0235 0.0108 1.0000
15.000 0.9816 0.07906 0.07466 0.0206 0.0108 1.0000
15.250 0.9586 0.08709 0.08292 0.0162 0.0109 1.0000
15.500 0.9283 0.09761 0.09371 0.0099 0.0110 1.0000
15.750 0.8734 0.11612 0.11251 -0.0016 0.0115 1.0000
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