GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 770 AIRFOIL (goe770-il) Reynolds number: 200,000 Max Cl/Cd: 53.65 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe770-il-200000.txt Download as CSV file: xf-goe770-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 770 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5730 0.10181 0.09788 -0.0462 1.0000 0.0637
-14.750 -0.6263 0.08782 0.08375 -0.0548 1.0000 0.0625
-14.500 -0.7351 0.06930 0.06475 -0.0674 1.0000 0.0606
-14.250 -0.7946 0.06022 0.05526 -0.0720 1.0000 0.0600
-14.000 -0.8234 0.05520 0.04998 -0.0732 1.0000 0.0599
-13.750 -0.8394 0.05172 0.04631 -0.0732 1.0000 0.0602
-13.500 -0.8505 0.04892 0.04335 -0.0724 1.0000 0.0606
-13.250 -0.8603 0.04647 0.04072 -0.0709 1.0000 0.0611
-13.000 -0.8698 0.04433 0.03842 -0.0685 1.0000 0.0617
-12.750 -0.8801 0.04253 0.03646 -0.0652 1.0000 0.0622
-12.500 -0.8642 0.03961 0.03310 -0.0671 0.9407 0.0633
-12.250 -0.8543 0.03755 0.03055 -0.0660 0.8814 0.0640
-12.000 -0.8340 0.03608 0.02897 -0.0650 0.8418 0.0649
-11.750 -0.8167 0.03515 0.02787 -0.0636 0.8136 0.0658
-11.500 -0.7989 0.03427 0.02684 -0.0624 0.7922 0.0670
-11.250 -0.7827 0.03324 0.02558 -0.0611 0.7750 0.0684
-11.000 -0.7676 0.03215 0.02417 -0.0596 0.7613 0.0697
-10.750 -0.7497 0.03096 0.02271 -0.0584 0.7491 0.0710
-10.500 -0.7241 0.02991 0.02167 -0.0583 0.7386 0.0723
-10.250 -0.7016 0.02912 0.02080 -0.0577 0.7289 0.0738
-10.000 -0.6796 0.02838 0.01991 -0.0570 0.7209 0.0757
-9.750 -0.6588 0.02765 0.01896 -0.0561 0.7124 0.0777
-9.500 -0.6331 0.02665 0.01797 -0.0559 0.7050 0.0797
-9.250 -0.6091 0.02601 0.01731 -0.0555 0.6981 0.0818
-9.000 -0.5855 0.02535 0.01656 -0.0549 0.6911 0.0843
-8.750 -0.5616 0.02462 0.01571 -0.0543 0.6852 0.0869
-8.500 -0.5373 0.02399 0.01510 -0.0539 0.6800 0.0898
-8.250 -0.5135 0.02346 0.01454 -0.0534 0.6742 0.0933
-8.000 -0.4896 0.02273 0.01380 -0.0529 0.6684 0.0968
-7.750 -0.4664 0.02215 0.01324 -0.0522 0.6632 0.1007
-7.500 -0.4429 0.02179 0.01273 -0.0515 0.6587 0.1053
-7.250 -0.4210 0.02103 0.01213 -0.0508 0.6541 0.1103
-7.000 -0.3976 0.02061 0.01165 -0.0501 0.6490 0.1161
-6.750 -0.3773 0.01990 0.01104 -0.0491 0.6443 0.1226
-6.500 -0.3559 0.01939 0.01050 -0.0481 0.6401 0.1303
-6.250 -0.3341 0.01898 0.01009 -0.0472 0.6362 0.1399
-6.000 -0.3136 0.01837 0.00962 -0.0462 0.6318 0.1528
-5.750 -0.2938 0.01771 0.00917 -0.0451 0.6272 0.1764
-5.500 -0.2755 0.01697 0.00884 -0.0438 0.6229 0.2521
-5.250 -0.2541 0.01652 0.00856 -0.0428 0.6191 0.3119
-5.000 -0.2327 0.01619 0.00840 -0.0418 0.6152 0.3543
-4.750 -0.2110 0.01586 0.00839 -0.0408 0.6107 0.4028
-4.500 -0.1869 0.01579 0.00848 -0.0399 0.6059 0.4513
-4.250 -0.1609 0.01583 0.00851 -0.0394 0.6014 0.4853
-4.000 -0.1344 0.01591 0.00855 -0.0388 0.5975 0.5108
-3.750 -0.1079 0.01612 0.00872 -0.0383 0.5937 0.5337
-3.500 -0.0817 0.01619 0.00885 -0.0378 0.5891 0.5528
-3.250 -0.0551 0.01628 0.00892 -0.0373 0.5844 0.5698
-3.000 -0.0281 0.01638 0.00895 -0.0369 0.5802 0.5862
-2.750 -0.0002 0.01644 0.00900 -0.0365 0.5766 0.5989
-2.500 0.0272 0.01663 0.00910 -0.0363 0.5730 0.6121
-2.250 0.0539 0.01667 0.00923 -0.0359 0.5684 0.6235
-2.000 0.0809 0.01671 0.00925 -0.0356 0.5637 0.6346
-1.750 0.1086 0.01673 0.00926 -0.0353 0.5595 0.6459
-1.500 0.1367 0.01676 0.00921 -0.0351 0.5559 0.6568
-1.250 0.1646 0.01692 0.00934 -0.0349 0.5523 0.6670
-1.000 0.1910 0.01697 0.00941 -0.0347 0.5475 0.6763
-0.750 0.2186 0.01695 0.00944 -0.0345 0.5428 0.6833
-0.500 0.2470 0.01692 0.00936 -0.0345 0.5386 0.6913
-0.250 0.2759 0.01691 0.00924 -0.0346 0.5350 0.6996
0.000 0.3032 0.01699 0.00936 -0.0344 0.5307 0.7070
0.250 0.3296 0.01705 0.00946 -0.0342 0.5255 0.7165
0.500 0.3573 0.01702 0.00945 -0.0341 0.5210 0.7244
0.750 0.3861 0.01699 0.00937 -0.0342 0.5172 0.7321
1.000 0.4156 0.01707 0.00932 -0.0345 0.5138 0.7411
1.250 0.4405 0.01712 0.00954 -0.0340 0.5083 0.7499
1.500 0.4672 0.01713 0.00958 -0.0338 0.5032 0.7614
1.750 0.4953 0.01706 0.00951 -0.0336 0.4990 0.7721
2.000 0.5243 0.01708 0.00944 -0.0338 0.4954 0.7853
2.250 0.5489 0.01720 0.00971 -0.0332 0.4904 0.7981
2.500 0.5741 0.01726 0.00986 -0.0327 0.4852 0.8140
2.750 0.6008 0.01725 0.00988 -0.0323 0.4811 0.8327
3.000 0.6287 0.01725 0.00986 -0.0320 0.4776 0.8533
3.250 0.6539 0.01744 0.01014 -0.0314 0.4732 0.8756
3.500 0.6808 0.01760 0.01042 -0.0311 0.4678 0.8991
3.750 0.7154 0.01769 0.01051 -0.0323 0.4632 0.9208
4.000 0.7566 0.01779 0.01051 -0.0348 0.4593 0.9395
4.250 0.7974 0.01814 0.01089 -0.0376 0.4544 0.9562
4.500 0.8408 0.01844 0.01124 -0.0411 0.4491 0.9698
4.750 0.8878 0.01862 0.01136 -0.0452 0.4448 0.9804
5.000 0.9377 0.01877 0.01139 -0.0498 0.4412 0.9882
5.250 0.9840 0.01916 0.01184 -0.0542 0.4366 0.9966
5.500 1.0098 0.01945 0.01218 -0.0547 0.4323 1.0000
5.750 1.0244 0.01962 0.01233 -0.0528 0.4289 1.0000
6.000 1.0436 0.01976 0.01240 -0.0515 0.4258 1.0000
6.250 1.0666 0.01996 0.01249 -0.0509 0.4231 1.0000
6.500 1.0810 0.02042 0.01302 -0.0489 0.4198 1.0000
6.750 1.0954 0.02087 0.01355 -0.0470 0.4162 1.0000
7.000 1.1137 0.02124 0.01394 -0.0457 0.4130 1.0000
7.250 1.1353 0.02153 0.01421 -0.0449 0.4102 1.0000
7.500 1.1601 0.02179 0.01442 -0.0445 0.4078 1.0000
7.750 1.1878 0.02214 0.01469 -0.0448 0.4054 1.0000
8.000 1.1999 0.02279 0.01548 -0.0426 0.4022 1.0000
8.250 1.2143 0.02338 0.01617 -0.0409 0.3988 1.0000
8.500 1.2332 0.02388 0.01673 -0.0399 0.3959 1.0000
8.750 1.2566 0.02419 0.01704 -0.0395 0.3931 1.0000
9.000 1.2863 0.02429 0.01705 -0.0400 0.3901 1.0000
9.250 1.3086 0.02472 0.01748 -0.0395 0.3866 1.0000
9.500 1.3155 0.02541 0.01833 -0.0369 0.3824 1.0000
9.750 1.3321 0.02586 0.01885 -0.0356 0.3788 1.0000
10.000 1.3558 0.02615 0.01914 -0.0353 0.3759 1.0000
10.250 1.3859 0.02635 0.01927 -0.0360 0.3732 1.0000
10.500 1.4116 0.02688 0.01979 -0.0361 0.3705 1.0000
10.750 1.4102 0.02794 0.02107 -0.0327 0.3672 1.0000
11.000 1.4144 0.02883 0.02208 -0.0300 0.3639 1.0000
11.250 1.4279 0.02941 0.02271 -0.0285 0.3609 1.0000
11.500 1.4572 0.02950 0.02276 -0.0290 0.3578 1.0000
11.750 1.5013 0.02947 0.02261 -0.0316 0.3542 1.0000
12.000 1.4768 0.03108 0.02446 -0.0255 0.3510 1.0000
12.250 1.4652 0.03268 0.02623 -0.0220 0.3471 1.0000
12.500 1.4821 0.03306 0.02661 -0.0212 0.3431 1.0000
12.750 1.5350 0.03196 0.02534 -0.0236 0.3389 1.0000
13.000 1.5153 0.03415 0.02772 -0.0199 0.3352 1.0000
13.250 1.4890 0.03713 0.03091 -0.0168 0.3308 1.0000
13.500 1.5039 0.03773 0.03153 -0.0163 0.3266 1.0000
13.750 1.5581 0.03600 0.02963 -0.0178 0.3224 1.0000
14.000 1.5193 0.04019 0.03408 -0.0148 0.3181 1.0000
14.250 1.4877 0.04454 0.03861 -0.0133 0.3128 1.0000
14.500 1.5236 0.04347 0.03747 -0.0135 0.3086 1.0000
14.750 1.5467 0.04359 0.03756 -0.0133 0.3043 1.0000
15.000 1.4636 0.05309 0.04740 -0.0120 0.2974 1.0000
15.250 1.4994 0.05174 0.04599 -0.0119 0.2930 1.0000
15.500 1.5253 0.05142 0.04563 -0.0118 0.2884 1.0000
15.750 1.4365 0.06289 0.05741 -0.0120 0.2799 1.0000
16.000 1.4926 0.05912 0.05351 -0.0117 0.2759 1.0000
16.250 1.3927 0.07311 0.06780 -0.0131 0.2657 1.0000
16.500 1.4447 0.06949 0.06409 -0.0128 0.2618 1.0000
16.750 1.3708 0.08135 0.07615 -0.0146 0.2515 1.0000
17.000 1.4104 0.07914 0.07389 -0.0144 0.2473 1.0000
17.250 1.3597 0.08858 0.08346 -0.0161 0.2380 1.0000
17.500 1.3836 0.08837 0.08323 -0.0162 0.2332 1.0000
17.750 1.3887 0.09062 0.08550 -0.0167 0.2274 1.0000
18.000 1.3662 0.09667 0.09163 -0.0182 0.2197 1.0000
18.250 1.4005 0.09495 0.08983 -0.0178 0.2154 1.0000
18.500 1.3573 0.10397 0.09900 -0.0201 0.2068 1.0000
18.750 1.3979 0.10126 0.09617 -0.0195 0.2024 1.0000
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