S2027 (s2027-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2027 (s2027-il) Reynolds number: 100,000 Max Cl/Cd: 50.82 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2027-il-100000-n5.txt Download as CSV file: xf-s2027-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4427 0.09270 0.08772 -0.0443 1.0000 0.0273
-11.250 -0.4578 0.08429 0.07933 -0.0493 1.0000 0.0270
-11.000 -0.4791 0.07539 0.07041 -0.0555 1.0000 0.0266
-10.750 -0.5026 0.06761 0.06256 -0.0616 1.0000 0.0262
-10.500 -0.5277 0.06123 0.05607 -0.0664 1.0000 0.0260
-10.250 -0.5499 0.05659 0.05130 -0.0689 1.0000 0.0258
-10.000 -0.5715 0.05328 0.04788 -0.0689 1.0000 0.0257
-9.750 -0.5955 0.05134 0.04588 -0.0656 1.0000 0.0256
-9.500 -0.6198 0.04985 0.04431 -0.0610 1.0000 0.0256
-9.250 -0.6107 0.04543 0.03936 -0.0644 0.9844 0.0263
-9.000 -0.5948 0.04169 0.03506 -0.0669 0.9730 0.0270
-8.750 -0.5753 0.03866 0.03148 -0.0686 0.9624 0.0276
-8.500 -0.5508 0.03572 0.02825 -0.0702 0.9544 0.0281
-8.250 -0.5260 0.03345 0.02572 -0.0712 0.9451 0.0285
-8.000 -0.5005 0.03153 0.02359 -0.0718 0.9360 0.0291
-7.750 -0.4726 0.02981 0.02168 -0.0726 0.9281 0.0297
-7.500 -0.4489 0.02839 0.02009 -0.0724 0.9178 0.0305
-7.250 -0.4234 0.02707 0.01862 -0.0724 0.9090 0.0314
-7.000 -0.3992 0.02590 0.01731 -0.0720 0.8998 0.0324
-6.750 -0.3767 0.02497 0.01620 -0.0712 0.8897 0.0343
-6.500 -0.3541 0.02396 0.01511 -0.0706 0.8812 0.0364
-6.250 -0.3333 0.02313 0.01425 -0.0697 0.8711 0.0386
-6.000 -0.3118 0.02234 0.01336 -0.0688 0.8616 0.0412
-5.750 -0.2892 0.02158 0.01242 -0.0678 0.8533 0.0441
-5.500 -0.2688 0.02078 0.01159 -0.0668 0.8432 0.0485
-5.250 -0.2463 0.02004 0.01077 -0.0659 0.8351 0.0571
-5.000 -0.2255 0.01915 0.01004 -0.0649 0.8257 0.0838
-4.750 -0.2049 0.01823 0.00943 -0.0641 0.8169 0.1440
-4.500 -0.1834 0.01743 0.00892 -0.0634 0.8087 0.2200
-4.250 -0.1641 0.01661 0.00866 -0.0624 0.7994 0.3332
-4.000 -0.1421 0.01613 0.00852 -0.0612 0.7922 0.4239
-3.750 -0.1190 0.01597 0.00848 -0.0602 0.7825 0.4795
-3.500 -0.0938 0.01586 0.00834 -0.0592 0.7752 0.5184
-3.250 -0.0688 0.01582 0.00825 -0.0584 0.7661 0.5493
-3.000 -0.0431 0.01578 0.00813 -0.0576 0.7581 0.5765
-2.750 -0.0175 0.01575 0.00803 -0.0568 0.7497 0.6006
-2.500 0.0082 0.01573 0.00793 -0.0561 0.7414 0.6222
-2.250 0.0342 0.01570 0.00781 -0.0553 0.7335 0.6412
-2.000 0.0598 0.01569 0.00774 -0.0547 0.7248 0.6588
-1.750 0.0863 0.01564 0.00759 -0.0540 0.7174 0.6755
-1.500 0.1118 0.01565 0.00754 -0.0534 0.7083 0.6911
-1.250 0.1385 0.01559 0.00739 -0.0527 0.7014 0.7060
-1.000 0.1639 0.01561 0.00736 -0.0521 0.6920 0.7202
-0.750 0.1904 0.01558 0.00725 -0.0515 0.6846 0.7341
-0.500 0.2162 0.01558 0.00722 -0.0510 0.6757 0.7480
-0.250 0.2425 0.01557 0.00715 -0.0505 0.6679 0.7618
0.000 0.2684 0.01557 0.00710 -0.0499 0.6596 0.7757
0.250 0.2942 0.01559 0.00708 -0.0493 0.6514 0.7898
0.500 0.3202 0.01559 0.00702 -0.0487 0.6435 0.8041
0.750 0.3456 0.01562 0.00705 -0.0480 0.6350 0.8185
1.000 0.3718 0.01561 0.00699 -0.0474 0.6275 0.8334
1.250 0.3971 0.01566 0.00705 -0.0468 0.6186 0.8492
1.500 0.4242 0.01566 0.00699 -0.0463 0.6116 0.8656
1.750 0.4509 0.01572 0.00709 -0.0461 0.6022 0.8827
2.000 0.4810 0.01575 0.00708 -0.0463 0.5946 0.9006
2.250 0.5131 0.01581 0.00715 -0.0472 0.5854 0.9197
2.500 0.5483 0.01589 0.00721 -0.0487 0.5769 0.9394
2.750 0.5870 0.01595 0.00723 -0.0510 0.5682 0.9584
3.000 0.6265 0.01607 0.00736 -0.0537 0.5586 0.9793
3.250 0.6645 0.01617 0.00739 -0.0561 0.5503 1.0000
3.500 0.6843 0.01637 0.00756 -0.0550 0.5414 1.0000
3.750 0.7071 0.01655 0.00769 -0.0544 0.5336 1.0000
4.000 0.7304 0.01676 0.00788 -0.0538 0.5249 1.0000
4.250 0.7543 0.01699 0.00809 -0.0533 0.5166 1.0000
4.500 0.7789 0.01720 0.00826 -0.0529 0.5084 1.0000
5.000 0.8281 0.01768 0.00872 -0.0521 0.4918 1.0000
5.250 0.8515 0.01798 0.00908 -0.0516 0.4822 1.0000
5.500 0.8761 0.01825 0.00933 -0.0512 0.4741 1.0000
5.750 0.9001 0.01854 0.00967 -0.0507 0.4652 1.0000
6.000 0.9239 0.01885 0.01002 -0.0502 0.4563 1.0000
6.250 0.9484 0.01914 0.01030 -0.0498 0.4482 1.0000
6.500 0.9711 0.01950 0.01074 -0.0492 0.4387 1.0000
6.750 0.9951 0.01982 0.01108 -0.0487 0.4305 1.0000
7.000 1.0176 0.02019 0.01152 -0.0481 0.4211 1.0000
7.250 1.0401 0.02057 0.01196 -0.0474 0.4122 1.0000
7.500 1.0631 0.02092 0.01233 -0.0468 0.4037 1.0000
7.750 1.0840 0.02137 0.01290 -0.0460 0.3939 1.0000
8.000 1.1059 0.02177 0.01335 -0.0453 0.3852 1.0000
8.250 1.1265 0.02222 0.01387 -0.0444 0.3758 1.0000
8.500 1.1462 0.02271 0.01445 -0.0434 0.3662 1.0000
8.750 1.1666 0.02316 0.01493 -0.0425 0.3574 1.0000
9.000 1.1842 0.02370 0.01561 -0.0413 0.3473 1.0000
9.250 1.2015 0.02425 0.01625 -0.0400 0.3374 1.0000
9.500 1.2178 0.02479 0.01683 -0.0386 0.3272 1.0000
9.750 1.2313 0.02539 0.01751 -0.0368 0.3160 1.0000
10.000 1.2417 0.02606 0.01828 -0.0347 0.3045 1.0000
10.250 1.2502 0.02678 0.01909 -0.0324 0.2933 1.0000
10.500 1.2577 0.02759 0.01995 -0.0301 0.2822 1.0000
10.750 1.2640 0.02852 0.02090 -0.0279 0.2708 1.0000
11.000 1.2686 0.02963 0.02211 -0.0259 0.2586 1.0000
11.250 1.2724 0.03089 0.02345 -0.0240 0.2463 1.0000
11.500 1.2754 0.03230 0.02493 -0.0222 0.2342 1.0000
11.750 1.2773 0.03388 0.02658 -0.0207 0.2222 1.0000
12.000 1.2779 0.03569 0.02844 -0.0193 0.2100 1.0000
12.250 1.2769 0.03773 0.03053 -0.0181 0.1977 1.0000
12.500 1.2744 0.04004 0.03291 -0.0171 0.1851 1.0000
12.750 1.2703 0.04266 0.03556 -0.0164 0.1724 1.0000
13.000 1.2645 0.04559 0.03853 -0.0159 0.1591 1.0000
13.250 1.2569 0.04888 0.04184 -0.0157 0.1460 1.0000
13.500 1.2479 0.05250 0.04547 -0.0158 0.1332 1.0000
13.750 1.2380 0.05643 0.04942 -0.0162 0.1211 1.0000
14.000 1.2279 0.06060 0.05361 -0.0168 0.1100 1.0000
14.250 1.2165 0.06514 0.05817 -0.0178 0.0996 1.0000
14.500 1.2049 0.06988 0.06293 -0.0190 0.0915 1.0000
14.750 1.1933 0.07488 0.06795 -0.0204 0.0829 1.0000
15.000 1.1833 0.07978 0.07291 -0.0219 0.0759 1.0000
15.250 1.1718 0.08504 0.07820 -0.0237 0.0703 1.0000
15.500 1.1634 0.08999 0.08324 -0.0255 0.0644 1.0000
15.750 1.1531 0.09535 0.08864 -0.0275 0.0597 1.0000
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