S2027 (s2027-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2027 (s2027-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.89 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2027-il-1000000.txt Download as CSV file: xf-s2027-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S2027
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4258 0.12232 0.12067 -0.0262 1.0000 0.0140
-12.750 -0.5672 0.07794 0.07614 -0.0473 1.0000 0.0123
-12.500 -0.6204 0.06307 0.06109 -0.0584 1.0000 0.0119
-12.250 -0.6486 0.05490 0.05276 -0.0648 1.0000 0.0117
-12.000 -0.6731 0.04852 0.04622 -0.0693 1.0000 0.0117
-11.750 -0.6979 0.04307 0.04059 -0.0722 1.0000 0.0114
-11.500 -0.7084 0.04004 0.03742 -0.0731 1.0000 0.0117
-11.250 -0.7277 0.03661 0.03382 -0.0727 1.0000 0.0116
-11.000 -0.7235 0.03270 0.02956 -0.0758 0.9533 0.0115
-10.750 -0.7285 0.03070 0.02728 -0.0729 0.9262 0.0115
-10.500 -0.7286 0.02854 0.02485 -0.0703 0.9088 0.0115
-10.250 -0.7209 0.02688 0.02295 -0.0684 0.8957 0.0116
-10.000 -0.7098 0.02525 0.02110 -0.0668 0.8841 0.0117
-9.750 -0.6958 0.02370 0.01935 -0.0655 0.8737 0.0117
-9.500 -0.6792 0.02236 0.01781 -0.0643 0.8645 0.0118
-9.250 -0.6608 0.02113 0.01639 -0.0633 0.8551 0.0119
-9.000 -0.6408 0.02001 0.01511 -0.0625 0.8465 0.0120
-8.750 -0.6185 0.01941 0.01438 -0.0618 0.8380 0.0123
-8.500 -0.5948 0.01895 0.01381 -0.0614 0.8296 0.0125
-8.250 -0.5731 0.01791 0.01260 -0.0607 0.8217 0.0127
-8.000 -0.5543 0.01601 0.01058 -0.0597 0.8133 0.0131
-7.750 -0.5323 0.01508 0.00956 -0.0590 0.8053 0.0134
-7.500 -0.5089 0.01436 0.00878 -0.0585 0.7968 0.0137
-7.250 -0.4847 0.01378 0.00814 -0.0581 0.7891 0.0139
-7.000 -0.4599 0.01327 0.00756 -0.0577 0.7807 0.0142
-6.750 -0.4349 0.01276 0.00698 -0.0573 0.7728 0.0145
-6.500 -0.4095 0.01230 0.00644 -0.0570 0.7645 0.0148
-6.250 -0.3838 0.01186 0.00594 -0.0567 0.7567 0.0151
-6.000 -0.3579 0.01146 0.00546 -0.0564 0.7484 0.0154
-5.750 -0.3314 0.01109 0.00503 -0.0563 0.7403 0.0158
-5.500 -0.3048 0.01077 0.00464 -0.0561 0.7322 0.0162
-5.250 -0.2775 0.01052 0.00434 -0.0560 0.7240 0.0165
-5.000 -0.2514 0.01007 0.00378 -0.0557 0.7160 0.0176
-4.750 -0.2240 0.00977 0.00344 -0.0557 0.7076 0.0185
-4.500 -0.1965 0.00955 0.00316 -0.0556 0.6996 0.0196
-4.250 -0.1686 0.00936 0.00292 -0.0556 0.6910 0.0206
-4.000 -0.1407 0.00919 0.00270 -0.0556 0.6830 0.0222
-3.750 -0.1134 0.00890 0.00245 -0.0556 0.6745 0.0369
-3.500 -0.0875 0.00831 0.00216 -0.0555 0.6666 0.1092
-3.250 -0.0614 0.00782 0.00194 -0.0555 0.6582 0.1860
-3.000 -0.0348 0.00738 0.00177 -0.0555 0.6502 0.2635
-2.750 -0.0077 0.00710 0.00164 -0.0556 0.6420 0.3221
-2.500 0.0200 0.00685 0.00155 -0.0557 0.6339 0.3778
-2.250 0.0475 0.00666 0.00148 -0.0557 0.6258 0.4288
-2.000 0.0758 0.00653 0.00144 -0.0558 0.6176 0.4662
-1.750 0.1039 0.00644 0.00141 -0.0559 0.6097 0.5029
-1.500 0.1322 0.00636 0.00140 -0.0560 0.6015 0.5404
-1.250 0.1605 0.00633 0.00140 -0.0561 0.5937 0.5659
-1.000 0.1892 0.00632 0.00139 -0.0562 0.5855 0.5824
-0.750 0.2179 0.00633 0.00139 -0.0563 0.5779 0.5965
-0.500 0.2466 0.00635 0.00140 -0.0565 0.5697 0.6093
-0.250 0.2753 0.00638 0.00140 -0.0566 0.5622 0.6211
0.000 0.3039 0.00640 0.00142 -0.0568 0.5542 0.6323
0.250 0.3326 0.00642 0.00143 -0.0569 0.5469 0.6428
0.500 0.3611 0.00647 0.00145 -0.0570 0.5391 0.6532
0.750 0.3898 0.00650 0.00148 -0.0572 0.5316 0.6637
1.000 0.4181 0.00654 0.00152 -0.0573 0.5238 0.6737
1.250 0.4468 0.00658 0.00155 -0.0574 0.5164 0.6836
1.500 0.4750 0.00663 0.00159 -0.0575 0.5085 0.6939
1.750 0.5035 0.00666 0.00164 -0.0577 0.5013 0.7041
2.000 0.5316 0.00673 0.00169 -0.0578 0.4933 0.7148
2.250 0.5600 0.00677 0.00175 -0.0579 0.4859 0.7261
2.500 0.5879 0.00683 0.00182 -0.0579 0.4780 0.7378
2.750 0.6161 0.00687 0.00188 -0.0580 0.4703 0.7501
3.250 0.6716 0.00699 0.00204 -0.0581 0.4544 0.7778
3.500 0.6989 0.00707 0.00214 -0.0580 0.4464 0.7934
3.750 0.7264 0.00711 0.00223 -0.0580 0.4383 0.8105
4.000 0.7532 0.00718 0.00234 -0.0578 0.4303 0.8295
4.500 0.8057 0.00730 0.00256 -0.0572 0.4138 0.8745
4.750 0.8303 0.00737 0.00269 -0.0565 0.4051 0.9027
5.000 0.8543 0.00741 0.00280 -0.0556 0.3972 0.9383
5.250 0.8871 0.00754 0.00293 -0.0568 0.3876 0.9742
5.500 0.9242 0.00767 0.00306 -0.0590 0.3778 1.0000
5.750 0.9507 0.00784 0.00320 -0.0589 0.3693 1.0000
6.000 0.9769 0.00803 0.00335 -0.0588 0.3601 1.0000
6.250 1.0035 0.00819 0.00350 -0.0587 0.3517 1.0000
6.500 1.0294 0.00840 0.00369 -0.0585 0.3427 1.0000
6.750 1.0556 0.00859 0.00386 -0.0584 0.3336 1.0000
7.000 1.0813 0.00880 0.00405 -0.0582 0.3228 1.0000
7.250 1.1065 0.00905 0.00426 -0.0580 0.3117 1.0000
7.500 1.1311 0.00933 0.00449 -0.0576 0.2982 1.0000
7.750 1.1552 0.00963 0.00473 -0.0572 0.2833 1.0000
8.000 1.1792 0.00994 0.00499 -0.0568 0.2706 1.0000
8.250 1.2033 0.01022 0.00525 -0.0564 0.2591 1.0000
8.500 1.2260 0.01058 0.00556 -0.0558 0.2442 1.0000
8.750 1.2483 0.01096 0.00588 -0.0551 0.2297 1.0000
9.000 1.2698 0.01136 0.00622 -0.0543 0.2150 1.0000
9.250 1.2899 0.01182 0.00661 -0.0534 0.1982 1.0000
9.500 1.3087 0.01233 0.00704 -0.0522 0.1799 1.0000
9.750 1.3252 0.01293 0.00754 -0.0507 0.1611 1.0000
10.000 1.3398 0.01356 0.00808 -0.0489 0.1428 1.0000
10.250 1.3482 0.01429 0.00870 -0.0461 0.1224 1.0000
10.500 1.3554 0.01502 0.00935 -0.0431 0.1072 1.0000
10.750 1.3604 0.01592 0.01016 -0.0401 0.0895 1.0000
11.000 1.3654 0.01690 0.01106 -0.0373 0.0744 1.0000
11.250 1.3712 0.01792 0.01203 -0.0348 0.0627 1.0000
11.500 1.3778 0.01897 0.01304 -0.0327 0.0531 1.0000
11.750 1.3831 0.02016 0.01420 -0.0306 0.0440 1.0000
12.000 1.3882 0.02144 0.01546 -0.0286 0.0365 1.0000
12.250 1.3925 0.02286 0.01686 -0.0268 0.0299 1.0000
12.500 1.3978 0.02428 0.01829 -0.0253 0.0250 1.0000
12.750 1.3969 0.02625 0.02023 -0.0235 0.0175 1.0000
13.250 1.4038 0.02981 0.02384 -0.0212 0.0123 1.0000
13.500 1.4036 0.03203 0.02611 -0.0201 0.0105 1.0000
13.750 1.4072 0.03401 0.02816 -0.0194 0.0097 1.0000
14.000 1.4118 0.03595 0.03017 -0.0188 0.0093 1.0000
14.250 1.4127 0.03832 0.03260 -0.0183 0.0087 1.0000
14.500 1.4151 0.04063 0.03499 -0.0180 0.0085 1.0000
14.750 1.4127 0.04355 0.03798 -0.0178 0.0080 1.0000
15.000 1.4062 0.04704 0.04158 -0.0177 0.0075 1.0000
15.250 1.4074 0.04978 0.04439 -0.0179 0.0074 1.0000
15.500 1.4076 0.05273 0.04743 -0.0182 0.0073 1.0000
15.750 1.4062 0.05593 0.05072 -0.0186 0.0072 1.0000
16.000 1.4039 0.05935 0.05423 -0.0192 0.0071 1.0000
16.250 1.4032 0.06265 0.05761 -0.0199 0.0068 1.0000
16.500 1.3987 0.06655 0.06160 -0.0209 0.0066 1.0000
16.750 1.3953 0.07036 0.06551 -0.0219 0.0065 1.0000
17.000 1.3901 0.07454 0.06979 -0.0231 0.0064 1.0000
17.250 1.3837 0.07901 0.07435 -0.0246 0.0062 1.0000
17.500 1.3764 0.08369 0.07911 -0.0262 0.0060 1.0000
17.750 1.3690 0.08850 0.08402 -0.0279 0.0060 1.0000
18.000 1.3601 0.09366 0.08928 -0.0299 0.0059 1.0000
18.250 1.3492 0.09924 0.09497 -0.0322 0.0058 1.0000
18.500 1.3397 0.10468 0.10050 -0.0345 0.0056 1.0000
18.750 1.3243 0.11127 0.10721 -0.0374 0.0056 1.0000
19.000 1.3137 0.11710 0.11315 -0.0401 0.0055 1.0000
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Polar data table (+)
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