GOE 29B AIRFOIL (goe29b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 29B AIRFOIL (goe29b-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.14 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe29b-il-1000000.txt Download as CSV file: xf-goe29b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 29B 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2373 0.10520 0.10322 -0.0178 0.8523 0.0223
-8.750 -0.2329 0.10187 0.09982 -0.0208 0.8350 0.0225
-8.500 -0.2281 0.09869 0.09657 -0.0234 0.8173 0.0226
-8.250 -0.2209 0.09515 0.09296 -0.0244 0.7983 0.0227
-8.000 -0.2102 0.09256 0.09030 -0.0246 0.7765 0.0228
-7.750 -0.1123 0.07938 0.07683 -0.0315 0.6752 0.0234
-7.250 -0.0963 0.07403 0.07139 -0.0334 0.6498 0.0243
-7.000 -0.0888 0.07117 0.06848 -0.0346 0.6403 0.0249
-6.500 -0.1364 0.07808 0.07531 -0.0357 0.6485 0.0250
-6.250 -0.1099 0.07307 0.07023 -0.0471 0.6399 0.0261
-6.000 -0.0855 0.06901 0.06611 -0.0540 0.6318 0.0262
-5.750 -0.0710 0.06561 0.06266 -0.0550 0.6235 0.0264
-5.500 -0.0518 0.06337 0.06040 -0.0565 0.6163 0.0266
-5.250 -0.0301 0.06113 0.05811 -0.0590 0.6090 0.0268
-5.000 -0.0061 0.05872 0.05566 -0.0621 0.6026 0.0272
-4.750 0.0197 0.05617 0.05306 -0.0656 0.5958 0.0277
-4.500 0.0475 0.05342 0.05024 -0.0696 0.5887 0.0286
-4.250 0.0985 0.04779 0.04443 -0.0812 0.5835 0.0300
-2.500 0.3089 0.02955 0.02543 -0.0987 0.5267 0.0348
-2.250 0.3363 0.02837 0.02416 -0.0995 0.5159 0.0351
-2.000 0.3867 0.01120 0.00518 -0.1068 0.5124 0.0350
-1.750 0.4154 0.01115 0.00508 -0.1068 0.5006 0.0356
-1.500 0.4440 0.01113 0.00500 -0.1068 0.4886 0.0362
-1.250 0.4728 0.01083 0.00457 -0.1068 0.4773 0.0370
-1.000 0.5014 0.01054 0.00414 -0.1067 0.4670 0.0380
-0.750 0.5301 0.01031 0.00381 -0.1067 0.4587 0.0388
-0.500 0.5587 0.00995 0.00335 -0.1067 0.4511 0.0400
-0.250 0.5874 0.00994 0.00333 -0.1067 0.4444 0.0410
0.000 0.6159 0.00996 0.00330 -0.1066 0.4367 0.0422
0.250 0.6446 0.00990 0.00319 -0.1065 0.4307 0.0436
0.500 0.6731 0.00976 0.00300 -0.1065 0.4243 0.0452
0.750 0.7015 0.00982 0.00305 -0.1064 0.4181 0.0465
1.000 0.7302 0.00981 0.00305 -0.1064 0.4133 0.0482
1.250 0.7587 0.00982 0.00302 -0.1063 0.4077 0.0498
1.500 0.7870 0.00974 0.00290 -0.1063 0.4013 0.0518
1.750 0.8156 0.00979 0.00297 -0.1063 0.3951 0.0536
2.000 0.8437 0.00988 0.00301 -0.1062 0.3869 0.0557
2.250 0.8721 0.00994 0.00305 -0.1061 0.3798 0.0571
2.500 0.9002 0.00984 0.00293 -0.1061 0.3699 0.0596
2.750 0.9283 0.00992 0.00299 -0.1061 0.3584 0.0618
3.000 0.9561 0.01003 0.00304 -0.1060 0.3422 0.0639
3.250 0.9830 0.01025 0.00312 -0.1058 0.3150 0.0654
3.500 1.0086 0.01057 0.00323 -0.1056 0.2747 0.0683
3.750 1.0351 0.01085 0.00341 -0.1053 0.2556 0.0704
4.000 1.0620 0.01105 0.00356 -0.1052 0.2460 0.0726
4.250 1.0892 0.01122 0.00371 -0.1050 0.2399 0.0742
4.500 1.1167 0.01128 0.00376 -0.1050 0.2357 0.0776
4.750 1.1437 0.01145 0.00391 -0.1048 0.2312 0.0805
5.000 1.1704 0.01165 0.00409 -0.1046 0.2263 0.0836
5.250 1.1979 0.01174 0.00420 -0.1045 0.2245 0.0870
5.500 1.2252 0.01185 0.00435 -0.1044 0.2226 0.0926
5.750 1.2522 0.01199 0.00451 -0.1043 0.2205 0.1016
6.000 1.2758 0.01087 0.00493 -0.1039 0.2185 1.0000
6.250 1.3023 0.01111 0.00513 -0.1037 0.2160 1.0000
6.500 1.3283 0.01138 0.00537 -0.1034 0.2128 1.0000
6.750 1.3543 0.01165 0.00562 -0.1031 0.2103 1.0000
7.000 1.3812 0.01178 0.00577 -0.1030 0.2089 1.0000
7.250 1.4079 0.01194 0.00594 -0.1028 0.2067 1.0000
7.500 1.4342 0.01214 0.00614 -0.1026 0.2045 1.0000
7.750 1.4599 0.01238 0.00637 -0.1024 0.2014 1.0000
8.000 1.4849 0.01268 0.00665 -0.1020 0.1977 1.0000
8.250 1.5099 0.01298 0.00695 -0.1017 0.1946 1.0000
8.500 1.5362 0.01312 0.00712 -0.1015 0.1931 1.0000
8.750 1.5622 0.01329 0.00732 -0.1013 0.1905 1.0000
9.000 1.5874 0.01352 0.00754 -0.1010 0.1866 1.0000
9.250 1.6113 0.01386 0.00784 -0.1005 0.1812 1.0000
9.500 1.6365 0.01406 0.00808 -0.1002 0.1775 1.0000
9.750 1.6609 0.01432 0.00832 -0.0999 0.1709 1.0000
10.000 1.6840 0.01469 0.00864 -0.0993 0.1621 1.0000
10.250 1.7042 0.01528 0.00910 -0.0984 0.1435 1.0000
10.500 1.7206 0.01613 0.00981 -0.0970 0.1255 1.0000
11.000 1.7543 0.01759 0.01117 -0.0943 0.1076 1.0000
11.250 1.7705 0.01828 0.01185 -0.0929 0.1002 1.0000
11.500 1.7821 0.01916 0.01267 -0.0907 0.0903 1.0000
11.750 1.7792 0.02071 0.01404 -0.0867 0.0672 1.0000
12.000 1.7523 0.02414 0.01726 -0.0810 0.0294 1.0000
12.250 1.7467 0.02652 0.01964 -0.0783 0.0187 1.0000
12.500 1.7524 0.02817 0.02135 -0.0769 0.0171 1.0000
12.750 1.7565 0.03005 0.02330 -0.0756 0.0160 1.0000
13.000 1.7607 0.03204 0.02536 -0.0745 0.0152 1.0000
13.250 1.7657 0.03402 0.02742 -0.0737 0.0148 1.0000
13.500 1.7692 0.03625 0.02973 -0.0730 0.0144 1.0000
13.750 1.7707 0.03878 0.03235 -0.0724 0.0140 1.0000
14.000 1.7701 0.04164 0.03529 -0.0720 0.0136 1.0000
14.250 1.7673 0.04486 0.03861 -0.0718 0.0133 1.0000
14.500 1.7614 0.04850 0.04236 -0.0717 0.0129 1.0000
14.750 1.7522 0.05258 0.04656 -0.0717 0.0127 1.0000
15.000 1.7466 0.05626 0.05034 -0.0717 0.0125 1.0000
15.250 1.7409 0.06003 0.05421 -0.0719 0.0124 1.0000
15.500 1.7338 0.06408 0.05836 -0.0722 0.0122 1.0000
15.750 1.7256 0.06836 0.06274 -0.0727 0.0121 1.0000
16.000 1.7159 0.07291 0.06740 -0.0733 0.0119 1.0000
16.250 1.7051 0.07775 0.07235 -0.0741 0.0118 1.0000
16.500 1.6933 0.08282 0.07753 -0.0750 0.0116 1.0000
16.750 1.6806 0.08808 0.08289 -0.0761 0.0115 1.0000
17.000 1.6670 0.09356 0.08848 -0.0773 0.0114 1.0000
17.250 1.6529 0.09920 0.09424 -0.0787 0.0113 1.0000
17.500 1.6375 0.10507 0.10022 -0.0803 0.0112 1.0000
17.750 1.6218 0.11110 0.10636 -0.0820 0.0111 1.0000
18.000 1.6056 0.11733 0.11271 -0.0840 0.0110 1.0000
18.250 1.5891 0.12368 0.11917 -0.0861 0.0109 1.0000
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Polar data table (+)
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