GOE 775 AIRFOIL (goe775-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 775 AIRFOIL (goe775-il) Reynolds number: 50,000 Max Cl/Cd: 25.14 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe775-il-50000-n5.txt Download as CSV file: xf-goe775-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 775 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6653 0.09971 0.08982 -0.0394 1.0000 0.1813
-13.250 -0.6352 0.10156 0.09169 -0.0376 1.0000 0.1833
-13.000 -0.7842 0.07535 0.06518 -0.0483 1.0000 0.1963
-12.750 -0.7253 0.08051 0.07048 -0.0452 1.0000 0.1989
-12.500 -0.7792 0.07049 0.06030 -0.0481 1.0000 0.2059
-12.250 -0.8670 0.05873 0.04813 -0.0495 1.0000 0.2114
-12.000 -0.8297 0.05996 0.04954 -0.0485 1.0000 0.2164
-11.750 -0.8470 0.05624 0.04570 -0.0476 1.0000 0.2218
-11.500 -0.8882 0.05123 0.04039 -0.0452 1.0000 0.2268
-11.250 -0.8599 0.05140 0.04075 -0.0445 1.0000 0.2324
-11.000 -0.8651 0.04942 0.03872 -0.0424 1.0000 0.2382
-10.750 -0.8918 0.04645 0.03552 -0.0385 1.0000 0.2437
-10.500 -0.8700 0.04622 0.03546 -0.0374 1.0000 0.2497
-10.250 -0.8746 0.04485 0.03405 -0.0342 1.0000 0.2558
-10.000 -0.8984 0.04292 0.03194 -0.0287 1.0000 0.2615
-9.750 -0.8798 0.04266 0.03187 -0.0272 1.0000 0.2677
-9.500 -0.8869 0.04168 0.03087 -0.0227 1.0000 0.2738
-9.250 -0.9080 0.04041 0.02946 -0.0163 1.0000 0.2797
-9.000 -0.8937 0.04013 0.02935 -0.0141 1.0000 0.2862
-8.750 -0.8980 0.03930 0.02847 -0.0096 1.0000 0.2931
-8.500 -0.9011 0.03846 0.02759 -0.0053 1.0000 0.3000
-8.250 -0.8934 0.03804 0.02726 -0.0023 1.0000 0.3071
-8.000 -0.8988 0.03717 0.02627 0.0024 1.0000 0.3150
-7.750 -0.8896 0.03679 0.02600 0.0052 1.0000 0.3222
-7.500 -0.8869 0.03621 0.02540 0.0088 1.0000 0.3304
-7.250 -0.8832 0.03564 0.02481 0.0123 1.0000 0.3385
-7.000 -0.8752 0.03528 0.02451 0.0152 1.0000 0.3469
-6.750 -0.8733 0.03467 0.02382 0.0188 1.0000 0.3561
-6.500 -0.8622 0.03446 0.02371 0.0213 1.0000 0.3646
-6.250 -0.8473 0.03392 0.02310 0.0225 0.9967 0.3761
-6.000 -0.8096 0.03372 0.02296 0.0201 0.9883 0.3892
-5.750 -0.7726 0.03347 0.02274 0.0177 0.9794 0.4025
-5.500 -0.7410 0.03302 0.02223 0.0161 0.9689 0.4169
-5.250 -0.7024 0.03288 0.02215 0.0138 0.9601 0.4300
-5.000 -0.6676 0.03263 0.02193 0.0121 0.9498 0.4430
-4.750 -0.6382 0.03220 0.02142 0.0111 0.9385 0.4573
-4.500 -0.5955 0.03214 0.02147 0.0084 0.9300 0.4698
-4.250 -0.5665 0.03185 0.02118 0.0078 0.9178 0.4826
-4.000 -0.5257 0.03156 0.02086 0.0052 0.9096 0.4975
-3.750 -0.4961 0.03148 0.02086 0.0050 0.8967 0.5089
-3.500 -0.4534 0.03115 0.02050 0.0022 0.8891 0.5238
-3.250 -0.4280 0.03103 0.02043 0.0027 0.8751 0.5361
-3.000 -0.3845 0.03080 0.02022 0.0002 0.8676 0.5500
-2.750 -0.3661 0.03051 0.01990 0.0017 0.8527 0.5641
-2.500 -0.3284 0.03047 0.01994 0.0005 0.8426 0.5763
-2.250 -0.2993 0.03024 0.01972 0.0005 0.8306 0.5901
-2.000 -0.2729 0.03007 0.01956 0.0010 0.8181 0.6041
-1.750 -0.2345 0.02992 0.01946 -0.0001 0.8082 0.6172
-1.500 -0.2131 0.02972 0.01925 0.0011 0.7946 0.6317
-1.250 -0.1710 0.02954 0.01911 -0.0005 0.7858 0.6451
-1.000 -0.1469 0.02949 0.01909 0.0006 0.7717 0.6582
-0.750 -0.1138 0.02920 0.01877 0.0002 0.7618 0.6734
-0.500 -0.0806 0.02928 0.01892 0.0001 0.7485 0.6847
-0.250 -0.0532 0.02909 0.01870 0.0006 0.7367 0.6996
0.000 -0.0141 0.02914 0.01878 -0.0004 0.7246 0.7108
0.250 0.0130 0.02913 0.01877 0.0002 0.7114 0.7242
0.500 0.0522 0.02910 0.01872 -0.0008 0.7000 0.7362
0.750 0.0795 0.02928 0.01892 -0.0003 0.6854 0.7482
1.000 0.1148 0.02918 0.01875 -0.0007 0.6743 0.7612
1.250 0.1458 0.02950 0.01910 -0.0007 0.6589 0.7715
1.500 0.1705 0.02953 0.01909 0.0002 0.6460 0.7857
1.750 0.2117 0.02973 0.01927 -0.0013 0.6324 0.7944
2.000 0.2338 0.02992 0.01946 -0.0001 0.6181 0.8081
2.250 0.2732 0.03004 0.01952 -0.0014 0.6053 0.8179
2.500 0.2983 0.03025 0.01973 -0.0007 0.5910 0.8305
2.750 0.3280 0.03045 0.01993 -0.0008 0.5774 0.8425
3.000 0.3649 0.03052 0.01993 -0.0019 0.5649 0.8528
3.250 0.3831 0.03079 0.02022 -0.0003 0.5511 0.8679
3.500 0.4281 0.03101 0.02040 -0.0031 0.5374 0.8751
3.750 0.4527 0.03116 0.02053 -0.0025 0.5248 0.8892
4.000 0.4958 0.03147 0.02085 -0.0053 0.5101 0.8968
4.250 0.5266 0.03151 0.02078 -0.0057 0.4990 0.9096
4.500 0.5659 0.03186 0.02119 -0.0081 0.4837 0.9181
4.750 0.5958 0.03212 0.02144 -0.0088 0.4712 0.9301
5.000 0.6373 0.03221 0.02145 -0.0114 0.4583 0.9389
5.250 0.6676 0.03262 0.02192 -0.0125 0.4443 0.9500
5.500 0.7028 0.03283 0.02209 -0.0142 0.4315 0.9604
5.750 0.7407 0.03302 0.02225 -0.0165 0.4179 0.9693
6.000 0.7729 0.03344 0.02272 -0.0182 0.4038 0.9796
6.250 0.8104 0.03366 0.02288 -0.0206 0.3907 0.9885
6.500 0.8473 0.03391 0.02311 -0.0230 0.3772 0.9971
6.750 0.8618 0.03441 0.02366 -0.0217 0.3661 1.0000
7.000 0.8716 0.03467 0.02385 -0.0190 0.3573 1.0000
7.250 0.8752 0.03522 0.02444 -0.0156 0.3483 1.0000
7.500 0.8817 0.03563 0.02482 -0.0125 0.3397 1.0000
7.750 0.8876 0.03612 0.02528 -0.0093 0.3318 1.0000
8.000 0.8886 0.03676 0.02598 -0.0055 0.3234 1.0000
8.250 0.9007 0.03704 0.02610 -0.0030 0.3163 1.0000
8.500 0.8935 0.03798 0.02719 0.0018 0.3083 1.0000
8.750 0.8989 0.03846 0.02762 0.0052 0.3011 1.0000
9.000 0.8995 0.03918 0.02833 0.0090 0.2943 1.0000
9.250 0.8932 0.04009 0.02931 0.0137 0.2873 1.0000
9.500 0.9038 0.04045 0.02954 0.0164 0.2808 1.0000
9.750 0.8891 0.04156 0.03072 0.0220 0.2749 1.0000
10.000 0.8794 0.04262 0.03183 0.0268 0.2688 1.0000
10.250 0.8948 0.04296 0.03203 0.0287 0.2625 1.0000
10.500 0.8773 0.04468 0.03387 0.0335 0.2568 1.0000
10.750 0.8698 0.04620 0.03544 0.0370 0.2507 1.0000
11.000 0.8923 0.04637 0.03545 0.0380 0.2446 1.0000
11.250 0.8686 0.04918 0.03845 0.0417 0.2391 1.0000
11.500 0.8600 0.05139 0.04075 0.0440 0.2333 1.0000
11.750 0.8879 0.05122 0.04040 0.0447 0.2277 1.0000
12.000 0.8529 0.05577 0.04521 0.0470 0.2226 1.0000
12.250 0.8303 0.05996 0.04953 0.0480 0.2172 1.0000
12.500 0.8596 0.05943 0.04888 0.0489 0.2122 1.0000
12.750 0.8010 0.06798 0.05771 0.0483 0.2071 1.0000
13.000 0.7223 0.08110 0.07108 0.0444 0.1994 1.0000
13.250 0.7756 0.07662 0.06648 0.0472 0.1968 1.0000
13.500 0.6348 0.10191 0.09204 0.0369 0.1838 1.0000
13.750 0.6634 0.10031 0.09042 0.0385 0.1816 1.0000
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Polar data table (+)
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