S8064 (s8064-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.27 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8064-il-1000000-n5.txt Download as CSV file: xf-s8064-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8481 0.06760 0.06522 -0.0539 0.9789 0.0029
-14.250 -0.8740 0.05092 0.04807 -0.0696 0.9450 0.0028
-13.750 -0.9036 0.04179 0.03852 -0.0728 0.9203 0.0029
-13.500 -0.9106 0.03887 0.03544 -0.0727 0.9133 0.0029
-13.250 -0.9140 0.03651 0.03295 -0.0722 0.9072 0.0029
-13.000 -0.9281 0.03343 0.02964 -0.0707 0.9016 0.0029
-12.750 -0.9323 0.03128 0.02734 -0.0692 0.8975 0.0029
-12.500 -0.9395 0.02906 0.02492 -0.0669 0.8932 0.0029
-12.250 -0.9349 0.02783 0.02358 -0.0651 0.8899 0.0029
-12.000 -0.9385 0.02604 0.02159 -0.0622 0.8867 0.0029
-11.750 -0.9377 0.02456 0.01997 -0.0594 0.8838 0.0030
-11.500 -0.9315 0.02349 0.01877 -0.0569 0.8810 0.0030
-11.250 -0.9265 0.02238 0.01752 -0.0540 0.8781 0.0030
-11.000 -0.9171 0.02150 0.01653 -0.0515 0.8760 0.0030
-10.750 -0.9045 0.02054 0.01543 -0.0497 0.8741 0.0031
-10.500 -0.8896 0.01965 0.01443 -0.0482 0.8725 0.0031
-10.250 -0.8728 0.01884 0.01354 -0.0469 0.8710 0.0032
-10.000 -0.8552 0.01804 0.01263 -0.0457 0.8692 0.0032
-9.750 -0.8357 0.01739 0.01190 -0.0447 0.8675 0.0033
-9.500 -0.8163 0.01668 0.01111 -0.0437 0.8660 0.0034
-9.250 -0.7957 0.01607 0.01042 -0.0428 0.8645 0.0035
-9.000 -0.7745 0.01550 0.00978 -0.0420 0.8629 0.0035
-8.750 -0.7530 0.01494 0.00914 -0.0412 0.8612 0.0037
-8.500 -0.7308 0.01444 0.00856 -0.0405 0.8595 0.0038
-8.250 -0.7082 0.01396 0.00801 -0.0399 0.8579 0.0040
-8.000 -0.6848 0.01350 0.00751 -0.0394 0.8566 0.0041
-7.750 -0.6611 0.01307 0.00702 -0.0389 0.8550 0.0042
-7.500 -0.6369 0.01268 0.00659 -0.0385 0.8534 0.0044
-7.250 -0.6124 0.01231 0.00617 -0.0381 0.8517 0.0045
-7.000 -0.5882 0.01192 0.00573 -0.0377 0.8500 0.0047
-6.750 -0.5638 0.01153 0.00528 -0.0373 0.8483 0.0050
-6.500 -0.5389 0.01120 0.00492 -0.0369 0.8467 0.0053
-6.250 -0.5136 0.01092 0.00459 -0.0366 0.8451 0.0057
-6.000 -0.4881 0.01066 0.00429 -0.0364 0.8434 0.0061
-5.750 -0.4619 0.01041 0.00403 -0.0362 0.8419 0.0067
-5.500 -0.4365 0.01008 0.00372 -0.0360 0.8400 0.0104
-5.250 -0.4112 0.00976 0.00345 -0.0357 0.8381 0.0193
-5.000 -0.3854 0.00949 0.00322 -0.0355 0.8361 0.0285
-4.750 -0.3593 0.00924 0.00301 -0.0354 0.8342 0.0386
-4.500 -0.3334 0.00898 0.00281 -0.0352 0.8322 0.0525
-4.250 -0.3074 0.00874 0.00262 -0.0350 0.8303 0.0686
-4.000 -0.2814 0.00849 0.00244 -0.0349 0.8284 0.0906
-3.750 -0.2557 0.00817 0.00227 -0.0347 0.8262 0.1227
-3.500 -0.2303 0.00784 0.00210 -0.0345 0.8237 0.1640
-3.250 -0.2047 0.00752 0.00194 -0.0343 0.8211 0.2066
-3.000 -0.1796 0.00717 0.00177 -0.0340 0.8185 0.2611
-2.750 -0.1541 0.00686 0.00163 -0.0338 0.8160 0.3114
-2.500 -0.1288 0.00654 0.00150 -0.0335 0.8135 0.3685
-2.250 -0.1030 0.00625 0.00140 -0.0334 0.8104 0.4227
-2.000 -0.0768 0.00601 0.00131 -0.0332 0.8071 0.4693
-1.750 -0.0504 0.00580 0.00123 -0.0331 0.8037 0.5127
-1.500 -0.0238 0.00561 0.00115 -0.0330 0.8006 0.5502
-1.250 0.0031 0.00545 0.00110 -0.0329 0.7969 0.5858
-1.000 0.0300 0.00529 0.00106 -0.0328 0.7923 0.6199
-0.750 0.0567 0.00515 0.00103 -0.0327 0.7876 0.6567
-0.500 0.0839 0.00506 0.00103 -0.0326 0.7824 0.6887
-0.250 0.1117 0.00502 0.00103 -0.0326 0.7756 0.7087
0.000 0.1397 0.00499 0.00102 -0.0327 0.7679 0.7226
0.250 0.1677 0.00499 0.00100 -0.0327 0.7576 0.7333
0.500 0.1953 0.00499 0.00099 -0.0327 0.7446 0.7412
0.750 0.2230 0.00504 0.00098 -0.0327 0.7292 0.7479
1.000 0.2502 0.00509 0.00099 -0.0326 0.7121 0.7536
1.250 0.2772 0.00517 0.00102 -0.0325 0.6930 0.7594
1.500 0.3039 0.00529 0.00106 -0.0324 0.6719 0.7644
1.750 0.3302 0.00541 0.00112 -0.0321 0.6477 0.7691
2.000 0.3562 0.00556 0.00118 -0.0319 0.6214 0.7740
2.250 0.3817 0.00575 0.00126 -0.0315 0.5905 0.7784
2.500 0.4058 0.00599 0.00138 -0.0310 0.5504 0.7825
2.750 0.4291 0.00630 0.00151 -0.0302 0.5021 0.7869
3.000 0.4519 0.00665 0.00166 -0.0295 0.4517 0.7914
3.250 0.4744 0.00702 0.00183 -0.0287 0.3980 0.7954
3.500 0.4971 0.00736 0.00202 -0.0279 0.3524 0.7998
3.750 0.5189 0.00776 0.00222 -0.0270 0.3008 0.8044
4.250 0.5616 0.00861 0.00267 -0.0251 0.2007 0.8135
4.500 0.5836 0.00899 0.00291 -0.0243 0.1626 0.8187
5.000 0.6295 0.00957 0.00333 -0.0228 0.1148 0.8300
5.250 0.6524 0.00985 0.00356 -0.0221 0.0960 0.8371
5.750 0.6970 0.01042 0.00405 -0.0204 0.0644 0.8515
6.000 0.7191 0.01070 0.00430 -0.0196 0.0521 0.8578
6.250 0.7418 0.01094 0.00454 -0.0188 0.0456 0.8651
6.500 0.7640 0.01118 0.00479 -0.0179 0.0395 0.8730
6.750 0.7855 0.01144 0.00506 -0.0170 0.0341 0.8821
7.000 0.8070 0.01167 0.00533 -0.0159 0.0302 0.8927
7.250 0.8274 0.01193 0.00562 -0.0147 0.0262 0.9063
7.500 0.8485 0.01215 0.00592 -0.0136 0.0241 0.9254
7.750 0.8755 0.01248 0.00630 -0.0139 0.0201 0.9507
8.250 0.9459 0.01346 0.00725 -0.0185 0.0110 0.9937
8.500 0.9657 0.01388 0.00768 -0.0174 0.0091 1.0000
8.750 0.9806 0.01425 0.00806 -0.0152 0.0082 1.0000
9.000 0.9959 0.01467 0.00851 -0.0132 0.0075 1.0000
9.250 1.0121 0.01510 0.00897 -0.0114 0.0070 1.0000
9.500 1.0288 0.01553 0.00943 -0.0098 0.0069 1.0000
9.750 1.0455 0.01599 0.00993 -0.0082 0.0065 1.0000
10.000 1.0617 0.01650 0.01050 -0.0066 0.0063 1.0000
10.250 1.0780 0.01701 0.01106 -0.0051 0.0061 1.0000
10.500 1.0938 0.01758 0.01167 -0.0036 0.0058 1.0000
10.750 1.1091 0.01820 0.01233 -0.0020 0.0057 1.0000
11.000 1.1231 0.01892 0.01310 -0.0003 0.0053 1.0000
11.250 1.1358 0.01973 0.01398 0.0015 0.0052 1.0000
11.500 1.1484 0.02055 0.01487 0.0032 0.0050 1.0000
11.750 1.1643 0.02113 0.01550 0.0045 0.0049 1.0000
12.000 1.1770 0.02196 0.01641 0.0061 0.0049 1.0000
12.250 1.1902 0.02275 0.01728 0.0076 0.0048 1.0000
12.500 1.2021 0.02364 0.01824 0.0092 0.0047 1.0000
12.750 1.2135 0.02458 0.01925 0.0107 0.0045 1.0000
13.000 1.2240 0.02559 0.02035 0.0123 0.0044 1.0000
13.250 1.2334 0.02669 0.02153 0.0139 0.0044 1.0000
13.500 1.2426 0.02784 0.02277 0.0154 0.0044 1.0000
13.750 1.2508 0.02907 0.02408 0.0169 0.0042 1.0000
14.000 1.2579 0.03041 0.02552 0.0183 0.0041 1.0000
14.250 1.2649 0.03180 0.02700 0.0197 0.0040 1.0000
14.500 1.2692 0.03343 0.02873 0.0211 0.0040 1.0000
14.750 1.2752 0.03498 0.03036 0.0222 0.0039 1.0000
15.000 1.2777 0.03689 0.03238 0.0233 0.0038 1.0000
15.250 1.2801 0.03887 0.03446 0.0242 0.0038 1.0000
15.500 1.2820 0.04100 0.03668 0.0249 0.0037 1.0000
15.750 1.2819 0.04343 0.03922 0.0255 0.0037 1.0000
16.000 1.2787 0.04633 0.04223 0.0258 0.0036 1.0000
16.250 1.2747 0.04949 0.04551 0.0258 0.0036 1.0000
16.500 1.2673 0.05325 0.04941 0.0253 0.0036 1.0000
16.750 1.2604 0.05717 0.05344 0.0244 0.0035 1.0000
17.000 1.2491 0.06195 0.05837 0.0230 0.0035 1.0000
17.250 1.2330 0.06777 0.06432 0.0208 0.0033 1.0000
17.500 1.2199 0.07350 0.07021 0.0183 0.0034 1.0000
17.750 1.1999 0.08075 0.07761 0.0147 0.0034 1.0000
18.000 1.1774 0.08894 0.08596 0.0103 0.0033 1.0000
18.250 1.1600 0.09657 0.09373 0.0061 0.0034 1.0000
18.500 1.1353 0.10597 0.10329 0.0009 0.0034 1.0000
18.750 1.1126 0.11527 0.11272 -0.0043 0.0034 1.0000
19.000 1.0845 0.12588 0.12349 -0.0101 0.0035 1.0000
19.250 1.0516 0.13786 0.13561 -0.0168 0.0035 1.0000
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Polar data table (+)
Polar graphs
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