S2027 (s2027-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2027 (s2027-il) Reynolds number: 200,000 Max Cl/Cd: 69.34 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2027-il-200000.txt Download as CSV file: xf-s2027-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3748 0.11079 0.10732 -0.0344 1.0000 0.0644
-11.000 -0.4079 0.10261 0.09925 -0.0451 1.0000 0.0678
-10.750 -0.4148 0.09589 0.09259 -0.0477 1.0000 0.0687
-10.500 -0.3959 0.09451 0.09121 -0.0447 1.0000 0.0698
-10.250 -0.3855 0.09218 0.08890 -0.0443 1.0000 0.0711
-10.000 -0.3809 0.08906 0.08580 -0.0451 1.0000 0.0727
-9.750 -0.3820 0.08510 0.08188 -0.0470 1.0000 0.0748
-8.750 -0.5148 0.05832 0.05487 -0.0712 0.9797 0.0825
-8.500 -0.5260 0.04032 0.03555 -0.0759 0.9689 0.0426
-8.250 -0.5159 0.03313 0.02721 -0.0765 0.9584 0.0362
-8.000 -0.4885 0.03126 0.02498 -0.0772 0.9499 0.0356
-7.750 -0.4587 0.02927 0.02269 -0.0782 0.9431 0.0354
-7.500 -0.4367 0.02680 0.01994 -0.0777 0.9330 0.0356
-7.250 -0.4122 0.02436 0.01734 -0.0776 0.9253 0.0367
-7.000 -0.3896 0.02305 0.01593 -0.0768 0.9154 0.0377
-6.750 -0.3670 0.02184 0.01462 -0.0757 0.9058 0.0383
-6.500 -0.3441 0.02075 0.01343 -0.0745 0.8978 0.0390
-6.250 -0.3228 0.01983 0.01245 -0.0731 0.8873 0.0398
-6.000 -0.3012 0.01899 0.01155 -0.0718 0.8784 0.0412
-5.750 -0.2798 0.01823 0.01069 -0.0704 0.8695 0.0428
-5.500 -0.2579 0.01761 0.00998 -0.0692 0.8598 0.0446
-5.250 -0.2384 0.01666 0.00901 -0.0677 0.8523 0.0482
-5.000 -0.2158 0.01613 0.00843 -0.0668 0.8421 0.0549
-4.750 -0.1946 0.01525 0.00758 -0.0656 0.8338 0.0712
-4.500 -0.1787 0.01355 0.00672 -0.0642 0.8249 0.2267
-4.250 -0.1571 0.01288 0.00642 -0.0634 0.8159 0.3245
-4.000 -0.1338 0.01244 0.00620 -0.0625 0.8083 0.4014
-3.750 -0.1102 0.01218 0.00618 -0.0616 0.7989 0.4738
-3.500 -0.0850 0.01206 0.00609 -0.0607 0.7920 0.5231
-3.250 -0.0599 0.01206 0.00614 -0.0599 0.7822 0.5637
-3.000 -0.0341 0.01208 0.00615 -0.0590 0.7747 0.5969
-2.750 -0.0080 0.01210 0.00612 -0.0584 0.7657 0.6219
-2.500 0.0184 0.01210 0.00607 -0.0577 0.7575 0.6408
-2.250 0.0450 0.01209 0.00601 -0.0571 0.7493 0.6591
-2.000 0.0714 0.01210 0.00598 -0.0565 0.7406 0.6766
-1.750 0.0983 0.01208 0.00588 -0.0559 0.7329 0.6929
-1.500 0.1247 0.01208 0.00586 -0.0554 0.7239 0.7079
-1.250 0.1517 0.01206 0.00575 -0.0548 0.7168 0.7223
-1.000 0.1779 0.01205 0.00575 -0.0544 0.7072 0.7361
-0.750 0.2047 0.01204 0.00567 -0.0538 0.6998 0.7497
-0.500 0.2311 0.01203 0.00564 -0.0534 0.6908 0.7631
-0.250 0.2577 0.01203 0.00559 -0.0529 0.6828 0.7765
0.000 0.2842 0.01201 0.00554 -0.0524 0.6744 0.7899
0.250 0.3103 0.01202 0.00554 -0.0519 0.6661 0.8032
0.500 0.3364 0.01201 0.00548 -0.0512 0.6582 0.8162
0.750 0.3618 0.01202 0.00551 -0.0506 0.6495 0.8297
1.000 0.3877 0.01201 0.00545 -0.0499 0.6421 0.8437
1.250 0.4122 0.01202 0.00550 -0.0490 0.6329 0.8586
1.500 0.4376 0.01203 0.00546 -0.0482 0.6258 0.8741
1.750 0.4616 0.01204 0.00551 -0.0472 0.6166 0.8911
2.000 0.4871 0.01206 0.00550 -0.0465 0.6091 0.9095
2.250 0.5153 0.01207 0.00552 -0.0463 0.6002 0.9278
2.500 0.5496 0.01213 0.00556 -0.0475 0.5916 0.9453
2.750 0.5900 0.01218 0.00555 -0.0501 0.5829 0.9609
3.000 0.6333 0.01226 0.00564 -0.0534 0.5728 0.9753
3.250 0.6794 0.01235 0.00566 -0.0574 0.5637 0.9875
3.500 0.7254 0.01242 0.00569 -0.0615 0.5538 1.0000
3.750 0.7390 0.01255 0.00581 -0.0595 0.5456 1.0000
4.000 0.7597 0.01270 0.00587 -0.0585 0.5378 1.0000
4.250 0.7823 0.01288 0.00605 -0.0578 0.5286 1.0000
4.500 0.8076 0.01307 0.00615 -0.0575 0.5208 1.0000
4.750 0.8320 0.01326 0.00637 -0.0570 0.5113 1.0000
5.000 0.8574 0.01347 0.00656 -0.0567 0.5028 1.0000
5.250 0.8830 0.01367 0.00672 -0.0565 0.4939 1.0000
5.500 0.9079 0.01390 0.00697 -0.0561 0.4846 1.0000
5.750 0.9342 0.01413 0.00715 -0.0559 0.4765 1.0000
6.000 0.9585 0.01435 0.00743 -0.0555 0.4665 1.0000
6.250 0.9837 0.01461 0.00769 -0.0552 0.4576 1.0000
6.500 1.0090 0.01486 0.00792 -0.0549 0.4487 1.0000
6.750 1.0331 0.01513 0.00826 -0.0544 0.4389 1.0000
7.000 1.0580 0.01541 0.00852 -0.0541 0.4300 1.0000
7.250 1.0820 0.01568 0.00882 -0.0536 0.4203 1.0000
7.500 1.1055 0.01599 0.00920 -0.0530 0.4105 1.0000
7.750 1.1300 0.01632 0.00949 -0.0526 0.4017 1.0000
8.000 1.1524 0.01662 0.00988 -0.0519 0.3915 1.0000
8.250 1.1749 0.01697 0.01028 -0.0512 0.3815 1.0000
8.500 1.1972 0.01732 0.01062 -0.0505 0.3713 1.0000
8.750 1.2178 0.01764 0.01098 -0.0495 0.3600 1.0000
9.000 1.2371 0.01799 0.01142 -0.0484 0.3482 1.0000
9.250 1.2559 0.01838 0.01185 -0.0472 0.3365 1.0000
9.500 1.2735 0.01878 0.01228 -0.0458 0.3246 1.0000
9.750 1.2905 0.01924 0.01275 -0.0444 0.3133 1.0000
10.000 1.3057 0.01971 0.01329 -0.0427 0.3017 1.0000
10.250 1.3195 0.02022 0.01389 -0.0409 0.2902 1.0000
10.500 1.3294 0.02076 0.01448 -0.0384 0.2784 1.0000
10.750 1.3359 0.02140 0.01515 -0.0356 0.2654 1.0000
11.000 1.3410 0.02218 0.01595 -0.0330 0.2513 1.0000
11.250 1.3449 0.02312 0.01690 -0.0304 0.2360 1.0000
11.500 1.3478 0.02425 0.01804 -0.0281 0.2198 1.0000
11.750 1.3495 0.02560 0.01940 -0.0260 0.2034 1.0000
12.000 1.3506 0.02716 0.02094 -0.0241 0.1876 1.0000
12.250 1.3500 0.02896 0.02272 -0.0224 0.1717 1.0000
12.500 1.3491 0.03095 0.02471 -0.0209 0.1545 1.0000
12.750 1.3445 0.03338 0.02709 -0.0196 0.1365 1.0000
13.000 1.3375 0.03616 0.02982 -0.0184 0.1205 1.0000
13.250 1.3289 0.03928 0.03289 -0.0176 0.1059 1.0000
13.500 1.3198 0.04263 0.03621 -0.0170 0.0919 1.0000
13.750 1.3094 0.04629 0.03984 -0.0168 0.0802 1.0000
14.000 1.2991 0.05014 0.04369 -0.0168 0.0709 1.0000
14.250 1.2885 0.05425 0.04782 -0.0171 0.0617 1.0000
14.500 1.2770 0.05863 0.05223 -0.0176 0.0556 1.0000
14.750 1.2637 0.06347 0.05708 -0.0185 0.0493 1.0000
15.000 1.2532 0.06809 0.06179 -0.0194 0.0441 1.0000
15.250 1.2427 0.07287 0.06661 -0.0206 0.0405 1.0000
15.500 1.2308 0.07789 0.07166 -0.0219 0.0376 1.0000
15.750 1.2262 0.08206 0.07596 -0.0230 0.0347 1.0000
16.000 1.2206 0.08645 0.08041 -0.0243 0.0325 1.0000
16.250 1.2138 0.09076 0.08469 -0.0253 0.0305 1.0000
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Polar data table (+)
Polar graphs
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