GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe92-il-1000000-n5.txt Download as CSV file: xf-goe92-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3118 0.12676 0.12495 -0.0142 0.8985 0.0042
-10.500 -0.3052 0.12359 0.12175 -0.0154 0.8894 0.0042
-10.250 -0.2986 0.12045 0.11857 -0.0165 0.8812 0.0042
-10.000 -0.2919 0.11727 0.11536 -0.0178 0.8737 0.0042
-9.750 -0.2852 0.11408 0.11214 -0.0191 0.8674 0.0042
-9.500 -0.2783 0.11089 0.10894 -0.0204 0.8608 0.0042
-9.250 -0.2714 0.10774 0.10575 -0.0217 0.8532 0.0042
-9.000 -0.2645 0.10456 0.10256 -0.0231 0.8454 0.0042
-8.750 -0.2575 0.10139 0.09937 -0.0245 0.8381 0.0042
-8.500 -0.2505 0.09821 0.09617 -0.0259 0.8295 0.0042
-8.250 -0.2435 0.09502 0.09296 -0.0274 0.8207 0.0042
-8.000 -0.2367 0.09201 0.08992 -0.0287 0.8102 0.0041
-7.750 -0.2293 0.08912 0.08701 -0.0303 0.7983 0.0040
-7.500 -0.2216 0.08594 0.08379 -0.0323 0.7858 0.0040
-7.250 -0.2137 0.08269 0.08051 -0.0347 0.7718 0.0040
-7.000 -0.2023 0.07917 0.07694 -0.0383 0.7550 0.0040
-6.750 -0.1877 0.07545 0.07313 -0.0426 0.7304 0.0040
-6.500 -0.1698 0.07082 0.06835 -0.0485 0.6927 0.0043
-6.250 -0.1532 0.06838 0.06571 -0.0516 0.6459 0.0046
-6.000 -0.1337 0.06589 0.06308 -0.0551 0.6160 0.0050
-5.500 -0.0832 0.05566 0.05263 -0.0675 0.5850 0.0042
-5.250 -0.0568 0.05153 0.04839 -0.0723 0.5722 0.0041
-5.000 -0.0285 0.04715 0.04387 -0.0769 0.5606 0.0041
-4.750 0.0019 0.04221 0.03876 -0.0814 0.5497 0.0041
-4.500 0.0334 0.03682 0.03316 -0.0853 0.5401 0.0044
-4.250 0.0615 0.03408 0.03025 -0.0871 0.5291 0.0046
-4.000 0.0903 0.03106 0.02702 -0.0886 0.5182 0.0049
-3.750 0.1203 0.02698 0.02266 -0.0899 0.5083 0.0053
-3.500 0.1521 0.01767 0.01245 -0.0905 0.5026 0.0069
-3.250 0.1795 0.01632 0.01086 -0.0904 0.4897 0.0075
-3.000 0.2069 0.01418 0.00835 -0.0902 0.4763 0.0086
-2.750 0.2338 0.01161 0.00530 -0.0898 0.4622 0.0107
-2.500 0.2613 0.01177 0.00539 -0.0898 0.4448 0.0119
-2.250 0.2884 0.01096 0.00437 -0.0896 0.4280 0.0140
-2.000 0.3160 0.01128 0.00462 -0.0896 0.4085 0.0146
-1.750 0.3435 0.01150 0.00473 -0.0896 0.3895 0.0157
-1.500 0.3708 0.01136 0.00444 -0.0895 0.3741 0.0180
-1.250 0.3983 0.01125 0.00419 -0.0894 0.3616 0.0195
-1.000 0.4260 0.01146 0.00430 -0.0893 0.3491 0.0201
-0.750 0.4528 0.01087 0.00362 -0.0893 0.3390 0.0214
-0.500 0.4802 0.01081 0.00350 -0.0892 0.3302 0.0223
-0.250 0.5078 0.01073 0.00339 -0.0892 0.3251 0.0235
0.000 0.5354 0.01056 0.00317 -0.0892 0.3202 0.0241
0.250 0.5628 0.01042 0.00297 -0.0892 0.3151 0.0246
0.500 0.5903 0.01027 0.00278 -0.0891 0.3108 0.0248
0.750 0.6179 0.01017 0.00265 -0.0891 0.3069 0.0253
1.000 0.6454 0.01007 0.00251 -0.0891 0.3026 0.0255
1.250 0.6728 0.00999 0.00239 -0.0891 0.2988 0.0253
1.500 0.7006 0.00991 0.00229 -0.0891 0.2966 0.0253
1.750 0.7283 0.00986 0.00222 -0.0891 0.2943 0.0255
2.000 0.7560 0.00983 0.00217 -0.0892 0.2917 0.0259
2.250 0.7835 0.00984 0.00216 -0.0892 0.2882 0.0266
2.500 0.8109 0.00990 0.00219 -0.0892 0.2844 0.0277
2.750 0.8385 0.00995 0.00225 -0.0892 0.2822 0.0285
3.000 0.8661 0.00996 0.00226 -0.0892 0.2800 0.0301
3.250 0.8935 0.01001 0.00231 -0.0893 0.2771 0.0315
3.500 0.9209 0.01008 0.00238 -0.0893 0.2740 0.0326
3.750 0.9481 0.01017 0.00246 -0.0893 0.2710 0.0337
4.000 0.9753 0.01026 0.00256 -0.0893 0.2685 0.0360
4.250 1.0026 0.01033 0.00266 -0.0893 0.2659 0.0375
4.750 1.0535 0.00903 0.00313 -0.0892 0.2529 1.0000
5.000 1.0797 0.00925 0.00328 -0.0891 0.2403 1.0000
5.250 1.1053 0.00953 0.00346 -0.0889 0.2216 1.0000
5.500 1.1218 0.01089 0.00426 -0.0876 0.1317 1.0000
5.750 1.1455 0.01140 0.00465 -0.0871 0.1115 1.0000
6.000 1.1698 0.01181 0.00500 -0.0868 0.0982 1.0000
6.250 1.1861 0.01320 0.00600 -0.0853 0.0193 1.0000
6.500 1.2111 0.01349 0.00632 -0.0851 0.0130 1.0000
6.750 1.2356 0.01384 0.00670 -0.0847 0.0105 1.0000
7.000 1.2597 0.01422 0.00712 -0.0843 0.0082 1.0000
7.250 1.2837 0.01457 0.00750 -0.0839 0.0070 1.0000
7.500 1.3069 0.01502 0.00798 -0.0834 0.0059 1.0000
7.750 1.3299 0.01545 0.00845 -0.0829 0.0053 1.0000
8.000 1.3529 0.01587 0.00891 -0.0824 0.0046 1.0000
8.250 1.3750 0.01635 0.00941 -0.0818 0.0041 1.0000
8.500 1.3956 0.01696 0.01009 -0.0809 0.0037 1.0000
8.750 1.4164 0.01750 0.01069 -0.0801 0.0034 1.0000
9.000 1.4363 0.01810 0.01135 -0.0792 0.0031 1.0000
9.250 1.4553 0.01874 0.01205 -0.0781 0.0029 1.0000
9.500 1.4735 0.01939 0.01278 -0.0770 0.0027 1.0000
9.750 1.4902 0.02011 0.01355 -0.0757 0.0025 1.0000
10.000 1.5023 0.02110 0.01463 -0.0737 0.0023 1.0000
10.250 1.5146 0.02185 0.01546 -0.0717 0.0022 1.0000
10.500 1.5235 0.02282 0.01652 -0.0693 0.0021 1.0000
10.750 1.5304 0.02396 0.01777 -0.0670 0.0020 1.0000
11.000 1.5359 0.02529 0.01921 -0.0647 0.0019 1.0000
11.250 1.5404 0.02680 0.02082 -0.0628 0.0018 1.0000
11.500 1.5436 0.02851 0.02264 -0.0609 0.0017 1.0000
11.750 1.5455 0.03045 0.02469 -0.0593 0.0017 1.0000
12.000 1.5468 0.03259 0.02693 -0.0580 0.0016 1.0000
12.250 1.5465 0.03501 0.02948 -0.0569 0.0016 1.0000
12.500 1.5460 0.03764 0.03221 -0.0562 0.0015 1.0000
12.750 1.5436 0.04067 0.03535 -0.0559 0.0015 1.0000
13.000 1.5381 0.04434 0.03914 -0.0560 0.0015 1.0000
13.250 1.5326 0.04829 0.04321 -0.0565 0.0014 1.0000
13.500 1.5221 0.05310 0.04815 -0.0574 0.0014 1.0000
13.750 1.5103 0.05821 0.05339 -0.0585 0.0014 1.0000
14.000 1.4967 0.06360 0.05891 -0.0597 0.0014 1.0000
14.250 1.4816 0.06930 0.06473 -0.0610 0.0013 1.0000
14.500 1.4656 0.07522 0.07077 -0.0624 0.0013 1.0000
14.750 1.4489 0.08122 0.07689 -0.0639 0.0013 1.0000
15.000 1.4330 0.08724 0.08302 -0.0654 0.0013 1.0000
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