GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.84 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe182-il-1000000-n5.txt Download as CSV file: xf-goe182-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 182 (MVA H.27) 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7290 0.02448 0.02195 -0.0957 0.9979 0.0149
-11.000 -0.6982 0.02216 0.01941 -0.0987 0.9954 0.0156
-10.750 -0.6679 0.02038 0.01743 -0.1009 0.9926 0.0162
-10.500 -0.6384 0.01891 0.01575 -0.1024 0.9885 0.0167
-10.250 -0.6064 0.01790 0.01462 -0.1040 0.9846 0.0172
-10.000 -0.5765 0.01760 0.01431 -0.1044 0.9785 0.0177
-9.750 -0.5457 0.01739 0.01410 -0.1050 0.9737 0.0182
-9.500 -0.5178 0.01708 0.01374 -0.1050 0.9678 0.0187
-9.250 -0.4897 0.01657 0.01314 -0.1052 0.9618 0.0191
-9.000 -0.4630 0.01598 0.01244 -0.1051 0.9543 0.0196
-8.750 -0.4364 0.01540 0.01174 -0.1050 0.9460 0.0201
-8.500 -0.4100 0.01491 0.01114 -0.1047 0.9360 0.0205
-8.250 -0.3837 0.01449 0.01060 -0.1043 0.9230 0.0208
-8.000 -0.3583 0.01380 0.00974 -0.1039 0.9029 0.0212
-7.750 -0.3334 0.01338 0.00914 -0.1032 0.8672 0.0216
-7.250 -0.2827 0.01329 0.00856 -0.1018 0.7604 0.0224
-6.750 -0.2286 0.01297 0.00789 -0.1012 0.7035 0.0232
-6.500 -0.2012 0.01265 0.00741 -0.1011 0.6809 0.0237
-6.250 -0.1736 0.01235 0.00695 -0.1009 0.6608 0.0241
-6.000 -0.1459 0.01206 0.00651 -0.1008 0.6401 0.0246
-5.750 -0.1180 0.01173 0.00604 -0.1007 0.6220 0.0249
-5.500 -0.0902 0.01145 0.00561 -0.1005 0.6026 0.0252
-5.250 -0.0623 0.01122 0.00523 -0.1004 0.5814 0.0254
-5.000 -0.0344 0.01103 0.00489 -0.1003 0.5606 0.0256
-4.750 -0.0067 0.01068 0.00440 -0.1001 0.5421 0.0260
-4.500 0.0212 0.01035 0.00394 -0.1000 0.5262 0.0266
-4.250 0.0493 0.01013 0.00363 -0.0999 0.5114 0.0270
-4.000 0.0774 0.00997 0.00337 -0.0998 0.4969 0.0274
-3.750 0.1055 0.00984 0.00315 -0.0997 0.4817 0.0278
-3.500 0.1337 0.00972 0.00294 -0.0996 0.4662 0.0282
-3.250 0.1619 0.00962 0.00275 -0.0994 0.4508 0.0286
-3.000 0.1901 0.00954 0.00258 -0.0993 0.4351 0.0291
-2.750 0.2182 0.00947 0.00242 -0.0992 0.4175 0.0296
-2.500 0.2463 0.00944 0.00228 -0.0991 0.3982 0.0301
-2.250 0.2743 0.00944 0.00217 -0.0989 0.3788 0.0307
-2.000 0.3023 0.00945 0.00208 -0.0988 0.3609 0.0312
-1.750 0.3303 0.00945 0.00200 -0.0987 0.3451 0.0316
-1.500 0.3584 0.00941 0.00188 -0.0985 0.3315 0.0328
-1.250 0.3865 0.00940 0.00181 -0.0984 0.3195 0.0340
-1.000 0.4147 0.00940 0.00177 -0.0983 0.3100 0.0353
-0.750 0.4428 0.00942 0.00174 -0.0982 0.3009 0.0369
-0.500 0.4710 0.00943 0.00171 -0.0981 0.2931 0.0385
-0.250 0.4991 0.00945 0.00170 -0.0980 0.2855 0.0429
0.000 0.5273 0.00946 0.00171 -0.0979 0.2793 0.0483
0.250 0.5553 0.00949 0.00173 -0.0977 0.2725 0.0561
0.500 0.5834 0.00951 0.00175 -0.0976 0.2674 0.0635
0.750 0.6115 0.00956 0.00178 -0.0975 0.2624 0.0680
1.000 0.6395 0.00960 0.00180 -0.0974 0.2571 0.0742
1.250 0.6675 0.00965 0.00184 -0.0973 0.2529 0.0799
1.500 0.6955 0.00966 0.00188 -0.0972 0.2492 0.0925
1.750 0.7233 0.00965 0.00197 -0.0972 0.2444 0.1446
2.000 0.7510 0.00973 0.00205 -0.0971 0.2389 0.1611
2.500 0.8067 0.00979 0.00222 -0.0969 0.2319 0.2129
2.750 0.8345 0.00980 0.00232 -0.0968 0.2295 0.2609
3.000 0.8621 0.00982 0.00243 -0.0967 0.2273 0.3076
3.250 0.8896 0.00977 0.00258 -0.0967 0.2251 0.4041
3.500 0.9170 0.00973 0.00274 -0.0966 0.2229 0.5028
4.000 0.9706 0.00900 0.00302 -0.0962 0.2204 1.0000
4.250 0.9982 0.00912 0.00314 -0.0960 0.2195 1.0000
4.500 1.0257 0.00924 0.00326 -0.0959 0.2185 1.0000
4.750 1.0531 0.00937 0.00338 -0.0957 0.2175 1.0000
5.000 1.0804 0.00951 0.00352 -0.0956 0.2160 1.0000
5.250 1.1075 0.00967 0.00366 -0.0954 0.2127 1.0000
5.500 1.1344 0.00985 0.00381 -0.0952 0.2097 1.0000
5.750 1.1613 0.01002 0.00398 -0.0950 0.2076 1.0000
6.000 1.1882 0.01018 0.00415 -0.0949 0.2055 1.0000
6.250 1.2153 0.01032 0.00431 -0.0947 0.2045 1.0000
6.500 1.2423 0.01046 0.00448 -0.0945 0.2033 1.0000
6.750 1.2691 0.01062 0.00465 -0.0943 0.2013 1.0000
7.000 1.2955 0.01081 0.00483 -0.0941 0.1966 1.0000
7.250 1.3215 0.01105 0.00505 -0.0939 0.1911 1.0000
7.500 1.3477 0.01126 0.00524 -0.0936 0.1825 1.0000
7.750 1.3713 0.01177 0.00558 -0.0931 0.1534 1.0000
8.000 1.3891 0.01299 0.00651 -0.0919 0.1066 1.0000
8.250 1.4123 0.01352 0.00700 -0.0913 0.0927 1.0000
8.500 1.4305 0.01464 0.00789 -0.0901 0.0537 1.0000
8.750 1.4533 0.01517 0.00840 -0.0894 0.0455 1.0000
9.000 1.4762 0.01565 0.00888 -0.0888 0.0400 1.0000
9.250 1.4989 0.01613 0.00936 -0.0881 0.0352 1.0000
9.500 1.5206 0.01670 0.00991 -0.0874 0.0292 1.0000
9.750 1.5414 0.01731 0.01049 -0.0865 0.0222 1.0000
10.000 1.5617 0.01795 0.01111 -0.0856 0.0169 1.0000
10.250 1.5820 0.01855 0.01172 -0.0846 0.0143 1.0000
10.500 1.6022 0.01912 0.01232 -0.0837 0.0129 1.0000
10.750 1.6211 0.01977 0.01299 -0.0826 0.0116 1.0000
11.000 1.6400 0.02037 0.01364 -0.0815 0.0107 1.0000
11.250 1.6579 0.02101 0.01432 -0.0803 0.0100 1.0000
11.500 1.6742 0.02172 0.01507 -0.0789 0.0092 1.0000
11.750 1.6880 0.02252 0.01592 -0.0771 0.0086 1.0000
12.000 1.6994 0.02328 0.01675 -0.0750 0.0082 1.0000
12.250 1.7100 0.02411 0.01764 -0.0728 0.0079 1.0000
12.500 1.7192 0.02507 0.01867 -0.0707 0.0076 1.0000
12.750 1.7271 0.02617 0.01983 -0.0687 0.0073 1.0000
13.000 1.7334 0.02746 0.02119 -0.0668 0.0070 1.0000
13.250 1.7382 0.02899 0.02280 -0.0651 0.0067 1.0000
13.500 1.7408 0.03087 0.02477 -0.0636 0.0065 1.0000
13.750 1.7409 0.03321 0.02720 -0.0626 0.0062 1.0000
14.000 1.7427 0.03562 0.02972 -0.0621 0.0061 1.0000
14.250 1.7430 0.03841 0.03261 -0.0620 0.0060 1.0000
14.500 1.7410 0.04162 0.03593 -0.0621 0.0059 1.0000
14.750 1.7363 0.04530 0.03972 -0.0626 0.0057 1.0000
15.000 1.7287 0.04946 0.04400 -0.0632 0.0056 1.0000
15.250 1.7176 0.05428 0.04895 -0.0642 0.0055 1.0000
15.500 1.7030 0.05968 0.05448 -0.0654 0.0055 1.0000
15.750 1.6852 0.06567 0.06061 -0.0669 0.0054 1.0000
16.000 1.6646 0.07208 0.06716 -0.0685 0.0054 1.0000
16.250 1.6423 0.07891 0.07412 -0.0704 0.0054 1.0000
16.500 1.6197 0.08595 0.08129 -0.0724 0.0054 1.0000
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Polar data table (+)
Polar graphs
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