GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 200,000 Max Cl/Cd: 61.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417a-il-200000-n5.txt Download as CSV file: xf-goe417a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417A (GEW. PLATTE) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3606 0.10840 0.10480 -0.0148 1.0000 0.0207
-8.000 -0.3661 0.10721 0.10365 -0.0132 1.0000 0.0208
-7.750 -0.3732 0.10623 0.10272 -0.0115 1.0000 0.0208
-7.250 -0.3537 0.09907 0.09557 -0.0139 0.9972 0.0210
-7.000 -0.3354 0.09529 0.09178 -0.0172 0.9945 0.0213
-6.750 -0.3167 0.09188 0.08836 -0.0210 0.9910 0.0216
-6.500 -0.2975 0.08866 0.08512 -0.0248 0.9878 0.0219
-6.250 -0.2751 0.08538 0.08182 -0.0293 0.9852 0.0223
-6.000 -0.2553 0.08233 0.07876 -0.0329 0.9811 0.0228
-5.750 -0.2299 0.07908 0.07546 -0.0378 0.9773 0.0233
-5.500 -0.1976 0.07604 0.07237 -0.0442 0.9741 0.0241
-5.250 -0.1687 0.07354 0.06981 -0.0496 0.9687 0.0243
-5.000 -0.1316 0.07069 0.06688 -0.0567 0.9654 0.0244
-4.750 -0.0991 0.06813 0.06424 -0.0623 0.9608 0.0245
-4.500 -0.0643 0.06553 0.06153 -0.0678 0.9564 0.0245
-4.250 -0.0434 0.06125 0.05727 -0.0695 0.9537 0.0247
-4.000 -0.0283 0.05787 0.05391 -0.0697 0.9486 0.0250
-3.750 -0.0039 0.05501 0.05103 -0.0720 0.9440 0.0255
-3.500 0.0296 0.05225 0.04819 -0.0761 0.9412 0.0260
-3.250 0.0555 0.04996 0.04586 -0.0781 0.9359 0.0265
-3.000 0.0849 0.04764 0.04348 -0.0807 0.9312 0.0271
-2.750 0.1201 0.04526 0.04101 -0.0844 0.9284 0.0277
-2.500 0.1613 0.04311 0.03875 -0.0887 0.9264 0.0287
-2.250 0.1911 0.04217 0.03766 -0.0896 0.9180 0.0292
-2.000 0.2351 0.04100 0.03626 -0.0930 0.9147 0.0294
-1.750 0.2640 0.03768 0.03293 -0.0951 0.9124 0.0297
-1.500 0.2767 0.03546 0.03073 -0.0934 0.9030 0.0300
-1.250 0.3063 0.03323 0.02846 -0.0950 0.8990 0.0305
-1.000 0.3295 0.03159 0.02676 -0.0947 0.8903 0.0311
-0.750 0.3616 0.02985 0.02494 -0.0960 0.8833 0.0318
-0.500 0.3855 0.02847 0.02348 -0.0953 0.8715 0.0326
-0.250 0.4172 0.02700 0.02190 -0.0960 0.8613 0.0338
0.250 0.4863 0.02581 0.02027 -0.0964 0.8350 0.0364
0.500 0.5129 0.02326 0.01767 -0.0969 0.8187 0.0373
0.750 0.5456 0.02158 0.01592 -0.0985 0.7961 0.0391
1.000 0.5862 0.02033 0.01446 -0.1009 0.7708 0.0415
1.250 0.6259 0.02017 0.01391 -0.1020 0.7427 0.0453
1.500 0.6568 0.01975 0.01315 -0.1018 0.7181 0.0461
1.750 0.6796 0.01815 0.01145 -0.1013 0.6942 0.0475
2.000 0.7031 0.01750 0.01067 -0.1004 0.6709 0.0496
2.250 0.7271 0.01716 0.01015 -0.0992 0.6470 0.0533
2.500 0.7510 0.01686 0.00962 -0.0978 0.6224 0.0578
2.750 0.7727 0.01636 0.00899 -0.0966 0.5968 0.0606
3.000 0.7951 0.01638 0.00875 -0.0949 0.5711 0.0690
3.250 0.8158 0.01594 0.00821 -0.0935 0.5461 0.0755
3.500 0.8376 0.01576 0.00790 -0.0922 0.5243 0.0892
3.750 0.8601 0.01550 0.00751 -0.0909 0.5025 0.0980
4.000 0.8879 0.01505 0.00670 -0.0893 0.4781 0.0389
4.250 0.9093 0.01502 0.00645 -0.0876 0.4388 0.0373
4.500 0.9267 0.01523 0.00636 -0.0854 0.3747 0.0370
4.750 0.9416 0.01567 0.00638 -0.0830 0.2938 0.0371
5.000 0.9592 0.01608 0.00653 -0.0812 0.2449 0.0381
5.250 0.9792 0.01640 0.00676 -0.0798 0.2207 0.0409
5.500 1.0007 0.01662 0.00693 -0.0786 0.2038 0.0422
5.750 1.0278 0.01691 0.00718 -0.0788 0.1865 0.0429
6.000 1.0526 0.01724 0.00742 -0.0784 0.1677 0.0439
6.250 1.0751 0.01762 0.00769 -0.0775 0.1440 0.0454
6.500 1.0879 0.01878 0.00827 -0.0751 0.0602 0.0486
6.750 1.1048 0.01954 0.00897 -0.0731 0.0472 0.0548
7.000 1.1226 0.02020 0.00964 -0.0712 0.0415 0.0624
7.250 1.1350 0.02011 0.01033 -0.0682 0.0387 0.6625
7.500 1.2505 0.02215 0.01293 -0.0890 0.0301 1.0000
7.750 1.2650 0.02292 0.01376 -0.0866 0.0284 1.0000
8.000 1.2782 0.02377 0.01465 -0.0840 0.0270 1.0000
8.250 1.2892 0.02477 0.01568 -0.0811 0.0256 1.0000
8.500 1.2980 0.02599 0.01692 -0.0778 0.0244 1.0000
8.750 1.3112 0.02674 0.01779 -0.0753 0.0232 1.0000
9.000 1.3216 0.02765 0.01878 -0.0722 0.0220 1.0000
9.250 1.3309 0.02866 0.01986 -0.0691 0.0212 1.0000
9.500 1.3400 0.02974 0.02101 -0.0660 0.0205 1.0000
9.750 1.3491 0.03084 0.02216 -0.0630 0.0198 1.0000
10.000 1.3580 0.03210 0.02348 -0.0602 0.0192 1.0000
10.250 1.3672 0.03393 0.02534 -0.0577 0.0185 1.0000
10.500 1.3778 0.03520 0.02678 -0.0551 0.0181 1.0000
10.750 1.3868 0.03639 0.02816 -0.0524 0.0172 1.0000
11.000 1.3953 0.03786 0.02979 -0.0498 0.0165 1.0000
11.250 1.4023 0.03943 0.03154 -0.0471 0.0160 1.0000
11.500 1.4083 0.04115 0.03344 -0.0444 0.0156 1.0000
11.750 1.4125 0.04291 0.03537 -0.0417 0.0152 1.0000
12.000 1.4153 0.04479 0.03741 -0.0390 0.0149 1.0000
12.250 1.4164 0.04677 0.03955 -0.0364 0.0147 1.0000
12.500 1.4158 0.04887 0.04180 -0.0339 0.0144 1.0000
12.750 1.4137 0.05130 0.04440 -0.0315 0.0142 1.0000
13.000 1.4095 0.05397 0.04724 -0.0292 0.0140 1.0000
13.250 1.4026 0.05712 0.05059 -0.0272 0.0139 1.0000
13.500 1.3931 0.06064 0.05435 -0.0255 0.0138 1.0000
13.750 1.3802 0.06458 0.05852 -0.0243 0.0137 1.0000
14.000 1.3665 0.06873 0.06292 -0.0237 0.0137 1.0000
14.250 1.3492 0.07368 0.06813 -0.0239 0.0136 1.0000
14.500 1.3313 0.07902 0.07372 -0.0249 0.0135 1.0000
14.750 1.3142 0.08465 0.07956 -0.0266 0.0135 1.0000
15.000 1.2939 0.09128 0.08643 -0.0294 0.0134 1.0000
15.250 1.2737 0.09846 0.09381 -0.0327 0.0134 1.0000
15.500 1.2538 0.10613 0.10166 -0.0368 0.0134 1.0000
15.750 1.2344 0.11414 0.10980 -0.0412 0.0136 1.0000
16.000 1.2143 0.12297 0.11878 -0.0464 0.0136 1.0000
16.250 1.1931 0.13298 0.12894 -0.0526 0.0137 1.0000
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