GOE 29B AIRFOIL (goe29b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 29B AIRFOIL (goe29b-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.46 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe29b-il-1000000-n5.txt Download as CSV file: xf-goe29b-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2182 0.09091 0.08786 -0.0242 0.6069 0.0175
-7.750 -0.2084 0.08824 0.08518 -0.0259 0.6018 0.0178
-7.500 -0.1989 0.08547 0.08240 -0.0278 0.5965 0.0180
-7.000 -0.1755 0.07943 0.07632 -0.0338 0.5872 0.0185
-6.750 -0.1622 0.07235 0.06921 -0.0428 0.5836 0.0197
-6.500 -0.1431 0.06955 0.06637 -0.0465 0.5768 0.0198
-6.250 -0.1223 0.06702 0.06382 -0.0499 0.5697 0.0200
-6.000 -0.1003 0.06454 0.06129 -0.0533 0.5610 0.0201
-5.500 -0.0525 0.05912 0.05577 -0.0610 0.5459 0.0204
-5.000 0.0417 0.01384 0.00827 -0.1070 0.5444 0.0263
-4.750 0.0700 0.01280 0.00699 -0.1072 0.5353 0.0265
-4.500 0.0986 0.01213 0.00614 -0.1074 0.5248 0.0267
-4.250 0.1272 0.01167 0.00556 -0.1074 0.5147 0.0271
-4.000 0.1559 0.01137 0.00516 -0.1074 0.5035 0.0275
-3.750 0.1846 0.01112 0.00481 -0.1074 0.4912 0.0278
-3.500 0.2133 0.01091 0.00451 -0.1074 0.4797 0.0282
-3.250 0.2420 0.01073 0.00424 -0.1074 0.4691 0.0286
-3.000 0.2706 0.01058 0.00399 -0.1073 0.4574 0.0291
-2.750 0.2993 0.01042 0.00374 -0.1073 0.4474 0.0296
-2.250 0.3568 0.01011 0.00327 -0.1072 0.4334 0.0303
-2.000 0.3856 0.00995 0.00306 -0.1072 0.4268 0.0308
-1.750 0.4143 0.00985 0.00291 -0.1071 0.4202 0.0315
-1.500 0.4431 0.00977 0.00281 -0.1071 0.4140 0.0322
-1.250 0.4717 0.00972 0.00271 -0.1070 0.4071 0.0329
-1.000 0.5005 0.00967 0.00262 -0.1070 0.4013 0.0336
-0.750 0.5292 0.00960 0.00252 -0.1069 0.3961 0.0345
-0.500 0.5579 0.00955 0.00244 -0.1069 0.3910 0.0354
-0.250 0.5866 0.00954 0.00242 -0.1068 0.3861 0.0366
0.000 0.6153 0.00952 0.00239 -0.1068 0.3811 0.0380
0.250 0.6438 0.00953 0.00236 -0.1068 0.3734 0.0393
0.500 0.6724 0.00953 0.00234 -0.1067 0.3664 0.0407
0.750 0.7009 0.00958 0.00236 -0.1067 0.3572 0.0422
1.000 0.7293 0.00963 0.00237 -0.1066 0.3480 0.0438
1.250 0.7574 0.00972 0.00239 -0.1065 0.3331 0.0451
1.500 0.7846 0.00996 0.00249 -0.1064 0.3012 0.0469
1.750 0.8107 0.01039 0.00271 -0.1061 0.2585 0.0487
2.000 0.8379 0.01061 0.00284 -0.1060 0.2418 0.0503
2.250 0.8657 0.01073 0.00292 -0.1059 0.2334 0.0516
2.500 0.8933 0.01088 0.00304 -0.1058 0.2259 0.0533
2.750 0.9213 0.01097 0.00313 -0.1057 0.2229 0.0551
3.000 0.9492 0.01107 0.00322 -0.1056 0.2201 0.0568
3.250 0.9770 0.01116 0.00330 -0.1055 0.2174 0.0583
3.500 1.0047 0.01126 0.00341 -0.1054 0.2147 0.0599
3.750 1.0323 0.01138 0.00353 -0.1053 0.2120 0.0617
4.000 1.0598 0.01150 0.00365 -0.1052 0.2093 0.0635
4.250 1.0875 0.01159 0.00376 -0.1051 0.2080 0.0648
4.500 1.1152 0.01167 0.00385 -0.1050 0.2065 0.0665
4.750 1.1426 0.01177 0.00398 -0.1049 0.2045 0.0688
5.000 1.1700 0.01189 0.00411 -0.1048 0.2029 0.0711
5.250 1.1972 0.01202 0.00425 -0.1047 0.2014 0.0730
5.500 1.2243 0.01215 0.00440 -0.1046 0.1998 0.0750
5.750 1.2513 0.01230 0.00456 -0.1044 0.1981 0.0786
6.000 1.2781 0.01246 0.00474 -0.1043 0.1962 0.0824
6.250 1.3046 0.01263 0.00493 -0.1041 0.1941 0.0883
6.500 1.3313 0.01277 0.00516 -0.1039 0.1920 0.1380
7.000 1.3818 0.01188 0.00569 -0.1034 0.1876 1.0000
7.250 1.4080 0.01209 0.00588 -0.1032 0.1838 1.0000
7.500 1.4337 0.01234 0.00610 -0.1029 0.1802 1.0000
7.750 1.4594 0.01259 0.00634 -0.1026 0.1765 1.0000
8.000 1.4854 0.01279 0.00654 -0.1024 0.1729 1.0000
8.250 1.5101 0.01310 0.00680 -0.1021 0.1649 1.0000
8.500 1.5343 0.01346 0.00709 -0.1016 0.1535 1.0000
8.750 1.5547 0.01416 0.00761 -0.1007 0.1310 1.0000
9.000 1.5760 0.01474 0.00811 -0.1000 0.1199 1.0000
9.250 1.5975 0.01527 0.00860 -0.0992 0.1123 1.0000
9.500 1.6196 0.01571 0.00903 -0.0985 0.1077 1.0000
9.750 1.6402 0.01625 0.00954 -0.0976 0.1022 1.0000
10.000 1.6619 0.01667 0.00997 -0.0968 0.0984 1.0000
10.250 1.6818 0.01720 0.01049 -0.0959 0.0927 1.0000
10.500 1.7000 0.01783 0.01108 -0.0947 0.0857 1.0000
10.750 1.6972 0.01980 0.01276 -0.0908 0.0484 1.0000
11.000 1.6842 0.02203 0.01488 -0.0855 0.0186 1.0000
11.250 1.6930 0.02310 0.01598 -0.0835 0.0155 1.0000
11.500 1.7027 0.02418 0.01710 -0.0817 0.0139 1.0000
11.750 1.7136 0.02525 0.01822 -0.0803 0.0132 1.0000
12.000 1.7233 0.02647 0.01950 -0.0790 0.0126 1.0000
12.250 1.7319 0.02787 0.02095 -0.0777 0.0120 1.0000
12.500 1.7391 0.02945 0.02259 -0.0766 0.0114 1.0000
12.750 1.7462 0.03113 0.02433 -0.0756 0.0111 1.0000
13.000 1.7533 0.03286 0.02613 -0.0747 0.0108 1.0000
13.250 1.7592 0.03479 0.02812 -0.0740 0.0105 1.0000
13.500 1.7639 0.03692 0.03033 -0.0734 0.0102 1.0000
13.750 1.7671 0.03928 0.03276 -0.0729 0.0099 1.0000
14.000 1.7689 0.04188 0.03544 -0.0726 0.0097 1.0000
14.250 1.7693 0.04472 0.03835 -0.0724 0.0094 1.0000
14.500 1.7674 0.04785 0.04157 -0.0722 0.0091 1.0000
14.750 1.7636 0.05125 0.04506 -0.0721 0.0089 1.0000
15.000 1.7584 0.05484 0.04873 -0.0722 0.0087 1.0000
15.250 1.7543 0.05835 0.05233 -0.0722 0.0086 1.0000
15.500 1.7490 0.06210 0.05618 -0.0725 0.0085 1.0000
15.750 1.7427 0.06607 0.06025 -0.0728 0.0084 1.0000
16.000 1.7351 0.07026 0.06453 -0.0733 0.0083 1.0000
16.250 1.7267 0.07465 0.06902 -0.0739 0.0082 1.0000
16.500 1.7176 0.07923 0.07371 -0.0746 0.0081 1.0000
16.750 1.7076 0.08400 0.07858 -0.0755 0.0080 1.0000
17.000 1.6968 0.08894 0.08363 -0.0765 0.0079 1.0000
17.250 1.6853 0.09407 0.08886 -0.0776 0.0078 1.0000
17.500 1.6729 0.09939 0.09428 -0.0789 0.0077 1.0000
17.750 1.6598 0.10484 0.09983 -0.0803 0.0076 1.0000
18.000 1.6462 0.11046 0.10556 -0.0818 0.0075 1.0000
18.250 1.6326 0.11617 0.11137 -0.0836 0.0075 1.0000
18.500 1.6188 0.12197 0.11728 -0.0855 0.0074 1.0000
18.750 1.6046 0.12793 0.12334 -0.0876 0.0073 1.0000
19.000 1.5905 0.13401 0.12953 -0.0899 0.0073 1.0000
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