GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 500,000 Max Cl/Cd: 87.2 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe677-il-500000.txt Download as CSV file: xf-goe677-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5763 0.11463 0.11232 -0.0041 1.0000 0.0349
-11.250 -0.5666 0.11292 0.11061 -0.0036 1.0000 0.0353
-10.750 -0.8631 0.04482 0.04162 -0.0357 1.0000 0.0289
-10.500 -0.8729 0.04100 0.03759 -0.0331 1.0000 0.0293
-10.250 -0.8440 0.04229 0.03903 -0.0330 1.0000 0.0297
-10.000 -0.6385 0.07180 0.06954 -0.0320 1.0000 0.0336
-9.750 -0.6625 0.06552 0.06319 -0.0343 1.0000 0.0331
-9.500 -0.7058 0.05621 0.05365 -0.0339 1.0000 0.0322
-9.250 -0.7942 0.03669 0.03298 -0.0275 1.0000 0.0322
-9.000 -0.7991 0.03171 0.02741 -0.0238 1.0000 0.0334
-8.750 -0.7893 0.02927 0.02458 -0.0214 1.0000 0.0341
-8.500 -0.7816 0.02630 0.02119 -0.0187 1.0000 0.0348
-8.250 -0.7659 0.02470 0.01951 -0.0171 1.0000 0.0356
-8.000 -0.7466 0.02426 0.01907 -0.0158 1.0000 0.0363
-7.750 -0.7209 0.02364 0.01841 -0.0158 0.9975 0.0371
-7.500 -0.6869 0.02237 0.01698 -0.0177 0.9893 0.0381
-7.250 -0.6534 0.02105 0.01546 -0.0192 0.9763 0.0391
-7.000 -0.6196 0.02006 0.01426 -0.0206 0.9577 0.0402
-6.750 -0.5893 0.01925 0.01325 -0.0211 0.9314 0.0409
-6.500 -0.5661 0.01815 0.01189 -0.0200 0.9007 0.0415
-6.250 -0.5443 0.01678 0.01034 -0.0188 0.8702 0.0425
-6.000 -0.5208 0.01630 0.00973 -0.0179 0.8407 0.0435
-5.750 -0.4962 0.01595 0.00925 -0.0172 0.8148 0.0446
-5.500 -0.4708 0.01552 0.00868 -0.0166 0.7945 0.0456
-5.250 -0.4451 0.01504 0.00807 -0.0161 0.7780 0.0467
-4.750 -0.3924 0.01424 0.00703 -0.0153 0.7534 0.0487
-4.500 -0.3660 0.01385 0.00654 -0.0150 0.7441 0.0496
-4.250 -0.3413 0.01308 0.00572 -0.0145 0.7353 0.0519
-4.000 -0.3147 0.01280 0.00542 -0.0142 0.7279 0.0537
-3.750 -0.2881 0.01252 0.00510 -0.0139 0.7204 0.0556
-3.500 -0.2613 0.01230 0.00480 -0.0136 0.7140 0.0577
-3.250 -0.2342 0.01205 0.00450 -0.0134 0.7080 0.0595
-3.000 -0.2090 0.01157 0.00402 -0.0129 0.7027 0.0635
-2.750 -0.1819 0.01140 0.00382 -0.0127 0.6976 0.0674
-2.500 -0.1541 0.01127 0.00367 -0.0127 0.6922 0.0707
-2.250 -0.1284 0.01088 0.00329 -0.0123 0.6874 0.0775
-2.000 -0.1011 0.01076 0.00312 -0.0121 0.6830 0.0830
-1.750 -0.0741 0.01049 0.00291 -0.0119 0.6784 0.0922
-1.500 -0.0470 0.01029 0.00277 -0.0117 0.6735 0.1061
-1.250 -0.0204 0.01008 0.00266 -0.0115 0.6688 0.1397
-1.000 0.0047 0.00963 0.00252 -0.0111 0.6640 0.2173
-0.750 0.0251 0.00870 0.00238 -0.0101 0.6591 0.4335
-0.500 0.0327 0.00717 0.00233 -0.0057 0.6549 0.8164
-0.250 0.0583 0.00729 0.00259 -0.0044 0.6504 0.8971
0.000 0.0836 0.00742 0.00274 -0.0033 0.6451 0.9242
0.250 0.1115 0.00763 0.00291 -0.0027 0.6395 0.9407
0.500 0.1454 0.00792 0.00313 -0.0034 0.6341 0.9523
0.750 0.1858 0.00812 0.00332 -0.0058 0.6278 0.9590
1.000 0.2351 0.00840 0.00352 -0.0100 0.6211 0.9654
1.250 0.2809 0.00859 0.00368 -0.0136 0.6126 0.9718
1.500 0.3284 0.00875 0.00375 -0.0177 0.6031 0.9762
1.750 0.3652 0.00885 0.00385 -0.0195 0.5934 0.9828
2.000 0.4130 0.00887 0.00382 -0.0238 0.5825 0.9860
2.250 0.4551 0.00889 0.00378 -0.0269 0.5702 0.9900
2.500 0.4904 0.00890 0.00377 -0.0286 0.5558 0.9936
2.750 0.5295 0.00884 0.00366 -0.0311 0.5358 0.9955
3.000 0.5663 0.00884 0.00359 -0.0332 0.5126 0.9976
3.250 0.5990 0.00890 0.00355 -0.0344 0.4917 0.9990
3.500 0.6301 0.00898 0.00355 -0.0353 0.4731 1.0000
3.750 0.6557 0.00909 0.00360 -0.0351 0.4587 1.0000
4.000 0.6812 0.00922 0.00366 -0.0348 0.4460 1.0000
4.250 0.7066 0.00934 0.00373 -0.0345 0.4339 1.0000
4.500 0.7320 0.00944 0.00382 -0.0342 0.4230 1.0000
4.750 0.7572 0.00957 0.00392 -0.0338 0.4137 1.0000
5.000 0.7823 0.00969 0.00403 -0.0335 0.4040 1.0000
5.250 0.8074 0.00979 0.00414 -0.0331 0.3937 1.0000
5.500 0.8321 0.00994 0.00427 -0.0326 0.3826 1.0000
5.750 0.8567 0.01007 0.00439 -0.0322 0.3698 1.0000
6.000 0.8811 0.01021 0.00452 -0.0317 0.3546 1.0000
6.250 0.9051 0.01038 0.00466 -0.0311 0.3334 1.0000
6.500 0.9280 0.01066 0.00483 -0.0304 0.3009 1.0000
6.750 0.9485 0.01121 0.00513 -0.0295 0.2507 1.0000
7.000 0.9662 0.01199 0.00562 -0.0281 0.1952 1.0000
7.250 0.9835 0.01272 0.00612 -0.0267 0.1538 1.0000
7.500 1.0010 0.01335 0.00658 -0.0252 0.1243 1.0000
7.750 1.0190 0.01385 0.00700 -0.0236 0.1094 1.0000
8.000 1.0372 0.01427 0.00740 -0.0221 0.1016 1.0000
8.250 1.0547 0.01471 0.00782 -0.0205 0.0961 1.0000
8.500 1.0716 0.01513 0.00826 -0.0187 0.0912 1.0000
8.750 1.0891 0.01547 0.00864 -0.0170 0.0872 1.0000
9.000 1.1043 0.01594 0.00910 -0.0149 0.0828 1.0000
9.250 1.1191 0.01638 0.00958 -0.0128 0.0786 1.0000
9.500 1.1370 0.01662 0.00988 -0.0112 0.0741 1.0000
9.750 1.1507 0.01711 0.01034 -0.0089 0.0671 1.0000
10.000 1.1677 0.01742 0.01061 -0.0072 0.0526 1.0000
10.250 1.1726 0.01840 0.01137 -0.0038 0.0312 1.0000
10.500 1.1803 0.01924 0.01220 -0.0007 0.0263 1.0000
10.750 1.1888 0.02005 0.01304 0.0021 0.0241 1.0000
11.000 1.1928 0.02096 0.01399 0.0055 0.0225 1.0000
11.250 1.2009 0.02180 0.01490 0.0080 0.0215 1.0000
11.500 1.2084 0.02283 0.01601 0.0102 0.0205 1.0000
11.750 1.2145 0.02411 0.01736 0.0121 0.0197 1.0000
12.000 1.2165 0.02586 0.01917 0.0139 0.0189 1.0000
12.250 1.2199 0.02767 0.02108 0.0151 0.0184 1.0000
12.500 1.2270 0.02933 0.02283 0.0159 0.0180 1.0000
12.750 1.2326 0.03120 0.02480 0.0166 0.0175 1.0000
13.000 1.2371 0.03327 0.02695 0.0170 0.0171 1.0000
13.250 1.2406 0.03550 0.02926 0.0174 0.0167 1.0000
13.500 1.2429 0.03789 0.03175 0.0176 0.0164 1.0000
13.750 1.2438 0.04045 0.03438 0.0178 0.0161 1.0000
14.000 1.2430 0.04320 0.03720 0.0180 0.0158 1.0000
14.250 1.2400 0.04621 0.04028 0.0181 0.0155 1.0000
14.500 1.2343 0.04947 0.04361 0.0183 0.0152 1.0000
14.750 1.2307 0.05255 0.04677 0.0185 0.0150 1.0000
15.000 1.2327 0.05520 0.04953 0.0183 0.0148 1.0000
15.250 1.2337 0.05805 0.05249 0.0179 0.0145 1.0000
15.500 1.2339 0.06106 0.05560 0.0175 0.0143 1.0000
15.750 1.2336 0.06418 0.05882 0.0169 0.0141 1.0000
16.000 1.2327 0.06743 0.06217 0.0163 0.0139 1.0000
16.250 1.2318 0.07076 0.06560 0.0156 0.0137 1.0000
16.500 1.2303 0.07426 0.06919 0.0147 0.0135 1.0000
16.750 1.2283 0.07784 0.07287 0.0138 0.0133 1.0000
17.000 1.2260 0.08155 0.07667 0.0127 0.0131 1.0000
17.250 1.2234 0.08536 0.08057 0.0116 0.0130 1.0000
17.500 1.2204 0.08926 0.08456 0.0103 0.0129 1.0000
17.750 1.2171 0.09321 0.08859 0.0090 0.0127 1.0000
18.000 1.2136 0.09720 0.09267 0.0077 0.0126 1.0000
18.250 1.2098 0.10129 0.09683 0.0063 0.0125 1.0000
18.500 1.2057 0.10540 0.10103 0.0049 0.0124 1.0000
18.750 1.2003 0.10970 0.10543 0.0034 0.0122 1.0000
19.000 1.1931 0.11440 0.11024 0.0016 0.0121 1.0000
19.250 1.1840 0.11962 0.11559 -0.0006 0.0121 1.0000
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Polar data table (+)
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