GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 8K AIRFOIL (goe08k-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.98 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe08k-il-1000000-n5.txt Download as CSV file: xf-goe08k-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 8K 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3485 0.02991 0.02679 -0.2352 0.9101 0.0062
-13.750 -0.3673 0.02711 0.02375 -0.2327 0.9033 0.0063
-13.500 -0.3709 0.02535 0.02181 -0.2304 0.8985 0.0064
-13.250 -0.3750 0.02346 0.01969 -0.2278 0.8942 0.0064
-13.000 -0.3867 0.02277 0.01893 -0.2213 0.8899 0.0064
-12.750 -0.4011 0.02172 0.01775 -0.2145 0.8853 0.0067
-12.500 -0.3981 0.02072 0.01660 -0.2110 0.8821 0.0068
-12.250 -0.3840 0.01976 0.01551 -0.2097 0.8796 0.0069
-12.000 -0.3891 0.01913 0.01480 -0.2038 0.8762 0.0070
-11.750 -0.3896 0.01849 0.01407 -0.1987 0.8726 0.0071
-11.500 -0.3792 0.01787 0.01335 -0.1960 0.8698 0.0074
-11.250 -0.3659 0.01718 0.01254 -0.1938 0.8674 0.0074
-11.000 -0.3476 0.01654 0.01177 -0.1927 0.8653 0.0077
-10.750 -0.3385 0.01603 0.01118 -0.1894 0.8629 0.0078
-10.500 -0.3324 0.01560 0.01068 -0.1853 0.8600 0.0081
-10.250 -0.3225 0.01514 0.01013 -0.1820 0.8570 0.0081
-10.000 -0.3074 0.01469 0.00959 -0.1798 0.8543 0.0085
-9.750 -0.2898 0.01417 0.00896 -0.1782 0.8520 0.0088
-9.500 -0.2677 0.01367 0.00837 -0.1776 0.8498 0.0091
-9.250 -0.2620 0.01340 0.00806 -0.1731 0.8470 0.0094
-9.000 -0.2507 0.01310 0.00770 -0.1699 0.8441 0.0097
-8.750 -0.2345 0.01282 0.00736 -0.1678 0.8414 0.0102
-8.500 -0.2162 0.01249 0.00695 -0.1661 0.8389 0.0105
-8.250 -0.1953 0.01215 0.00653 -0.1650 0.8367 0.0110
-8.000 -0.1759 0.01185 0.00617 -0.1635 0.8344 0.0115
-7.750 -0.1640 0.01163 0.00594 -0.1603 0.8315 0.0122
-7.500 -0.1501 0.01143 0.00569 -0.1576 0.8281 0.0129
-7.250 -0.1325 0.01123 0.00543 -0.1556 0.8251 0.0135
-7.000 -0.1129 0.01093 0.00509 -0.1541 0.8224 0.0151
-6.750 -0.0931 0.01073 0.00484 -0.1527 0.8198 0.0162
-6.500 -0.0789 0.01058 0.00466 -0.1499 0.8167 0.0172
-6.250 -0.0625 0.01038 0.00445 -0.1476 0.8135 0.0192
-6.000 -0.0436 0.01022 0.00426 -0.1459 0.8105 0.0212
-5.750 -0.0224 0.01006 0.00407 -0.1447 0.8078 0.0237
-5.500 -0.0017 0.00994 0.00394 -0.1434 0.8052 0.0275
-5.250 0.0150 0.00991 0.00394 -0.1412 0.8020 0.0303
-5.000 0.0335 0.00988 0.00391 -0.1393 0.7987 0.0332
-4.750 0.0537 0.00982 0.00381 -0.1379 0.7957 0.0345
-4.500 0.0765 0.00978 0.00375 -0.1370 0.7930 0.0366
-4.250 0.0984 0.00980 0.00378 -0.1359 0.7902 0.0388
-4.000 0.1164 0.00974 0.00370 -0.1339 0.7869 0.0397
-3.750 0.1377 0.00979 0.00375 -0.1327 0.7837 0.0420
-3.500 0.1587 0.00974 0.00365 -0.1314 0.7806 0.0428
-3.250 0.1820 0.00973 0.00360 -0.1307 0.7780 0.0438
-3.000 0.2040 0.00978 0.00365 -0.1296 0.7755 0.0445
-2.750 0.2217 0.00971 0.00355 -0.1276 0.7726 0.0447
-2.500 0.2393 0.00958 0.00339 -0.1256 0.7696 0.0464
-2.250 0.2593 0.00948 0.00328 -0.1241 0.7669 0.0478
-2.000 0.2811 0.00941 0.00318 -0.1230 0.7644 0.0486
-1.750 0.3038 0.00935 0.00309 -0.1221 0.7621 0.0492
-1.500 0.3239 0.00932 0.00306 -0.1207 0.7599 0.0499
-1.250 0.3446 0.00930 0.00303 -0.1194 0.7574 0.0507
-1.000 0.3655 0.00926 0.00298 -0.1181 0.7549 0.0512
-0.750 0.3871 0.00922 0.00292 -0.1170 0.7523 0.0514
-0.500 0.4101 0.00921 0.00289 -0.1162 0.7500 0.0521
-0.250 0.4344 0.00917 0.00283 -0.1157 0.7480 0.0527
0.000 0.4556 0.00918 0.00283 -0.1145 0.7461 0.0530
0.250 0.4757 0.00918 0.00285 -0.1131 0.7440 0.0535
0.500 0.4971 0.00919 0.00286 -0.1119 0.7418 0.0541
0.750 0.5186 0.00921 0.00288 -0.1109 0.7392 0.0546
1.000 0.5403 0.00924 0.00289 -0.1098 0.7356 0.0549
1.250 0.5651 0.00925 0.00288 -0.1095 0.7332 0.0559
1.500 0.5861 0.00929 0.00294 -0.1083 0.7307 0.0561
1.750 0.6052 0.00935 0.00301 -0.1067 0.7273 0.0564
2.000 0.6265 0.00939 0.00306 -0.1056 0.7243 0.0595
2.250 0.6490 0.00942 0.00312 -0.1048 0.7218 0.0659
2.500 0.6728 0.00946 0.00317 -0.1042 0.7194 0.0678
2.750 0.6997 0.00929 0.00330 -0.1047 0.7166 0.2070
3.250 1.0466 0.00858 0.00474 -0.1750 0.7186 1.0000
3.500 1.0620 0.00872 0.00489 -0.1726 0.7136 1.0000
3.750 1.0771 0.00888 0.00505 -0.1702 0.7078 1.0000
4.000 1.0866 0.00914 0.00529 -0.1665 0.6987 1.0000
4.250 1.0964 0.00942 0.00553 -0.1629 0.6885 1.0000
4.500 1.1164 0.00955 0.00568 -0.1616 0.6859 1.0000
4.750 1.1302 0.00978 0.00593 -0.1590 0.6775 1.0000
5.000 1.1414 0.01009 0.00623 -0.1558 0.6682 1.0000
5.250 1.1513 0.01045 0.00656 -0.1524 0.6562 1.0000
5.500 1.1650 0.01076 0.00688 -0.1498 0.6454 1.0000
5.750 1.1525 0.01177 0.00772 -0.1418 0.6054 1.0000
6.000 1.1227 0.01350 0.00915 -0.1306 0.5466 1.0000
6.250 1.1188 0.01457 0.01007 -0.1249 0.5152 1.0000
6.500 1.1141 0.01575 0.01109 -0.1192 0.4816 1.0000
6.750 1.0970 0.01752 0.01256 -0.1114 0.4231 1.0000
7.000 1.1080 0.01819 0.01317 -0.1088 0.4059 1.0000
7.250 1.1072 0.01941 0.01422 -0.1043 0.3673 1.0000
7.500 1.1025 0.02085 0.01542 -0.0992 0.3171 1.0000
7.750 1.0978 0.02237 0.01668 -0.0942 0.2649 1.0000
8.000 1.0971 0.02375 0.01782 -0.0901 0.2208 1.0000
8.250 1.1016 0.02491 0.01882 -0.0869 0.1867 1.0000
8.500 1.1052 0.02613 0.01985 -0.0836 0.1493 1.0000
8.750 1.1043 0.02765 0.02112 -0.0797 0.0991 1.0000
9.000 1.1133 0.02866 0.02203 -0.0774 0.0784 1.0000
9.250 1.1249 0.02953 0.02286 -0.0755 0.0673 1.0000
9.500 1.1368 0.03039 0.02370 -0.0737 0.0572 1.0000
9.750 1.1466 0.03140 0.02462 -0.0716 0.0400 1.0000
10.000 1.1570 0.03237 0.02554 -0.0696 0.0284 1.0000
10.250 1.1683 0.03332 0.02647 -0.0678 0.0220 1.0000
10.500 1.1808 0.03419 0.02735 -0.0663 0.0192 1.0000
10.750 1.1941 0.03503 0.02820 -0.0648 0.0169 1.0000
11.000 1.2055 0.03601 0.02919 -0.0632 0.0149 1.0000
11.250 1.2183 0.03690 0.03011 -0.0617 0.0131 1.0000
11.500 1.2311 0.03780 0.03102 -0.0603 0.0121 1.0000
11.750 1.2433 0.03874 0.03199 -0.0589 0.0114 1.0000
12.000 1.2550 0.03973 0.03301 -0.0574 0.0105 1.0000
12.250 1.2669 0.04071 0.03402 -0.0560 0.0098 1.0000
12.500 1.2774 0.04180 0.03515 -0.0545 0.0091 1.0000
12.750 1.2885 0.04289 0.03627 -0.0530 0.0089 1.0000
13.000 1.3002 0.04393 0.03736 -0.0517 0.0083 1.0000
13.250 1.3113 0.04501 0.03847 -0.0504 0.0078 1.0000
13.500 1.3207 0.04625 0.03976 -0.0489 0.0078 1.0000
13.750 1.3298 0.04750 0.04104 -0.0474 0.0071 1.0000
14.000 1.3397 0.04871 0.04230 -0.0461 0.0068 1.0000
14.250 1.3490 0.04999 0.04365 -0.0447 0.0064 1.0000
14.500 1.3578 0.05132 0.04502 -0.0434 0.0060 1.0000
14.750 1.3659 0.05272 0.04645 -0.0420 0.0055 1.0000
15.000 1.3730 0.05423 0.04802 -0.0406 0.0054 1.0000
15.250 1.3799 0.05577 0.04961 -0.0392 0.0053 1.0000
15.500 1.3867 0.05736 0.05126 -0.0379 0.0052 1.0000
15.750 1.3950 0.05879 0.05276 -0.0368 0.0050 1.0000
16.000 1.3999 0.06056 0.05459 -0.0354 0.0049 1.0000
16.250 1.4046 0.06238 0.05648 -0.0341 0.0045 1.0000
16.500 1.4122 0.06394 0.05811 -0.0331 0.0046 1.0000
16.750 1.4166 0.06584 0.06007 -0.0320 0.0044 1.0000
17.000 1.4193 0.06795 0.06226 -0.0307 0.0043 1.0000
17.250 1.4228 0.06998 0.06434 -0.0297 0.0041 1.0000
17.500 1.4239 0.07229 0.06672 -0.0285 0.0040 1.0000
17.750 1.4252 0.07462 0.06913 -0.0275 0.0040 1.0000
18.000 1.4257 0.07705 0.07164 -0.0265 0.0039 1.0000
18.250 1.4296 0.07916 0.07384 -0.0259 0.0038 1.0000
18.500 1.4283 0.08189 0.07666 -0.0251 0.0038 1.0000
18.750 1.4300 0.08431 0.07917 -0.0244 0.0036 1.0000
19.000 1.4290 0.08710 0.08205 -0.0239 0.0036 1.0000
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Polar data table (+)
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