GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 511 AIRFOIL (goe511-il) Reynolds number: 100,000 Max Cl/Cd: 41.65 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe511-il-100000-n5.txt Download as CSV file: xf-goe511-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 511 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 0.0248 0.10905 0.10409 -0.0882 0.9161 0.0747
-9.500 0.0222 0.10601 0.10106 -0.0934 0.9103 0.0777
-9.250 0.0065 0.10371 0.09883 -0.0954 0.8988 0.0781
-9.000 0.0457 0.09966 0.09475 -0.0940 0.8957 0.0800
-8.750 0.0655 0.09631 0.09140 -0.0967 0.8917 0.0828
-8.500 0.0594 0.09429 0.08942 -0.0958 0.8787 0.0851
-8.250 0.0338 0.09230 0.08748 -0.0979 0.8640 0.0872
-7.750 -0.0036 0.08764 0.08284 -0.0966 0.8338 0.0876
-7.250 -0.0083 0.07638 0.07148 -0.0949 0.8098 0.0617
-7.000 -0.0005 0.07431 0.06942 -0.0929 0.7963 0.0609
-6.750 0.0048 0.07114 0.06619 -0.0926 0.7841 0.0601
-6.500 0.0112 0.06720 0.06214 -0.0936 0.7736 0.0600
-6.000 0.0033 0.05484 0.04923 -0.0945 0.7500 0.0548
-5.750 0.0212 0.05130 0.04549 -0.0949 0.7393 0.0544
-5.500 0.0341 0.04732 0.04124 -0.0946 0.7273 0.0540
-5.250 0.0482 0.04176 0.03518 -0.0948 0.7178 0.0538
-5.000 0.0506 0.03730 0.03008 -0.0920 0.7050 0.0543
-4.750 0.0659 0.03373 0.02575 -0.0905 0.6937 0.0548
-4.250 0.1055 0.03021 0.02144 -0.0877 0.6669 0.0553
-4.000 0.1325 0.02884 0.01973 -0.0875 0.6548 0.0557
-3.750 0.1542 0.02782 0.01847 -0.0862 0.6416 0.0563
-3.500 0.1771 0.02693 0.01734 -0.0851 0.6292 0.0569
-3.250 0.2058 0.02611 0.01624 -0.0851 0.6180 0.0584
-3.000 0.2268 0.02548 0.01538 -0.0836 0.6063 0.0598
-2.750 0.2543 0.02478 0.01436 -0.0833 0.5963 0.0612
-2.500 0.2794 0.02423 0.01357 -0.0825 0.5862 0.0620
-2.250 0.3064 0.02371 0.01296 -0.0822 0.5773 0.0630
-2.000 0.3303 0.02333 0.01251 -0.0813 0.5680 0.0643
-1.750 0.3579 0.02299 0.01201 -0.0811 0.5599 0.0659
-1.500 0.3796 0.02277 0.01170 -0.0798 0.5511 0.0680
-1.250 0.4077 0.02253 0.01133 -0.0797 0.5436 0.0709
-1.000 0.4290 0.02239 0.01118 -0.0784 0.5358 0.0739
-0.750 0.4534 0.02227 0.01095 -0.0776 0.5286 0.0771
-0.500 0.4833 0.02213 0.01071 -0.0779 0.5223 0.0812
-0.250 0.5035 0.02210 0.01069 -0.0764 0.5150 0.0877
0.000 0.5302 0.02201 0.01061 -0.0761 0.5080 0.0998
0.250 0.5659 0.02182 0.01065 -0.0778 0.5015 0.1432
0.500 0.5837 0.02204 0.01100 -0.0758 0.4945 0.2089
0.750 0.6052 0.02229 0.01115 -0.0746 0.4882 0.2398
1.250 0.6489 0.02276 0.01155 -0.0724 0.4767 0.2870
1.500 0.6690 0.02296 0.01175 -0.0711 0.4708 0.3089
1.750 0.6939 0.02311 0.01184 -0.0707 0.4658 0.3301
2.000 0.7177 0.02327 0.01194 -0.0701 0.4607 0.3445
2.250 0.7353 0.02348 0.01214 -0.0683 0.4550 0.3529
2.500 0.7561 0.02363 0.01225 -0.0671 0.4497 0.3610
2.750 0.7798 0.02377 0.01228 -0.0664 0.4452 0.3714
3.000 0.7978 0.02397 0.01250 -0.0648 0.4404 0.3839
3.250 0.8147 0.02418 0.01276 -0.0631 0.4355 0.4022
3.500 0.8355 0.02421 0.01292 -0.0621 0.4312 0.4522
3.750 1.0337 0.02495 0.01448 -0.0977 0.4224 1.0000
4.000 1.0456 0.02532 0.01483 -0.0949 0.4183 1.0000
4.250 1.0599 0.02567 0.01512 -0.0926 0.4147 1.0000
4.500 1.0763 0.02600 0.01536 -0.0907 0.4114 1.0000
4.750 1.0963 0.02632 0.01555 -0.0895 0.4084 1.0000
5.000 1.1088 0.02674 0.01596 -0.0870 0.4049 1.0000
5.250 1.1189 0.02722 0.01646 -0.0841 0.4013 1.0000
5.500 1.1319 0.02767 0.01690 -0.0818 0.3979 1.0000
5.750 1.1474 0.02810 0.01728 -0.0799 0.3950 1.0000
6.000 1.1658 0.02849 0.01761 -0.0785 0.3925 1.0000
6.250 1.1876 0.02887 0.01790 -0.0778 0.3902 1.0000
6.500 1.1992 0.02946 0.01852 -0.0754 0.3876 1.0000
6.750 1.2071 0.03015 0.01927 -0.0725 0.3848 1.0000
7.000 1.2169 0.03080 0.01997 -0.0699 0.3820 1.0000
7.250 1.2289 0.03140 0.02058 -0.0677 0.3792 1.0000
7.500 1.2443 0.03192 0.02109 -0.0661 0.3766 1.0000
7.750 1.2632 0.03236 0.02148 -0.0650 0.3743 1.0000
8.000 1.2862 0.03278 0.02184 -0.0646 0.3724 1.0000
8.250 1.2912 0.03370 0.02285 -0.0616 0.3700 1.0000
8.500 1.2908 0.03482 0.02411 -0.0580 0.3675 1.0000
8.750 1.2937 0.03591 0.02530 -0.0550 0.3650 1.0000
9.000 1.2990 0.03694 0.02639 -0.0523 0.3625 1.0000
9.250 1.3092 0.03774 0.02722 -0.0504 0.3598 1.0000
9.500 1.3274 0.03819 0.02765 -0.0494 0.3572 1.0000
9.750 1.3572 0.03820 0.02755 -0.0499 0.3545 1.0000
10.000 1.3375 0.04027 0.02982 -0.0446 0.3512 1.0000
10.250 1.3168 0.04260 0.03234 -0.0397 0.3472 1.0000
10.500 1.3143 0.04414 0.03395 -0.0370 0.3434 1.0000
10.750 1.3303 0.04463 0.03444 -0.0360 0.3403 1.0000
11.000 1.3576 0.04458 0.03431 -0.0361 0.3378 1.0000
11.250 1.3548 0.04638 0.03620 -0.0336 0.3351 1.0000
11.500 1.2680 0.05455 0.04481 -0.0262 0.3295 1.0000
11.750 1.2257 0.06058 0.05102 -0.0234 0.3243 1.0000
12.000 1.2485 0.06059 0.05101 -0.0230 0.3222 1.0000
12.250 1.2839 0.05941 0.04979 -0.0230 0.3207 1.0000
12.500 1.3285 0.05752 0.04782 -0.0235 0.3192 1.0000
12.750 1.1124 0.08434 0.07520 -0.0203 0.3013 1.0000
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