GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe155-il-1000000-n5.txt Download as CSV file: xf-goe155-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4003 0.12071 0.11904 -0.0024 0.9238 0.0041
-10.000 -0.3967 0.11667 0.11499 -0.0038 0.9146 0.0042
-9.750 -0.3930 0.11292 0.11121 -0.0051 0.9049 0.0044
-9.500 -0.3863 0.11003 0.10829 -0.0063 0.8946 0.0045
-9.250 -0.3797 0.10708 0.10530 -0.0076 0.8842 0.0046
-9.000 -0.3739 0.10384 0.10203 -0.0090 0.8734 0.0046
-8.750 -0.3677 0.10069 0.09882 -0.0105 0.8620 0.0047
-8.500 -0.3612 0.09750 0.09561 -0.0121 0.8508 0.0048
-8.250 -0.3544 0.09433 0.09241 -0.0138 0.8404 0.0050
-8.000 -0.3481 0.09099 0.08902 -0.0158 0.8298 0.0051
-7.750 -0.3422 0.08748 0.08548 -0.0182 0.8188 0.0053
-7.500 -0.3331 0.08326 0.08123 -0.0223 0.8086 0.0056
-7.250 -0.3219 0.07718 0.07510 -0.0288 0.7995 0.0061
-7.000 -0.3054 0.07230 0.07017 -0.0348 0.7899 0.0065
-6.750 -0.2854 0.06948 0.06730 -0.0386 0.7803 0.0067
-6.500 -0.2641 0.06631 0.06406 -0.0428 0.7716 0.0070
-6.250 -0.2405 0.06203 0.05973 -0.0485 0.7640 0.0075
-6.000 -0.2091 0.05241 0.04995 -0.0606 0.7578 0.0088
-5.750 -0.1819 0.04955 0.04703 -0.0643 0.7509 0.0091
-5.500 -0.1545 0.04697 0.04434 -0.0676 0.7439 0.0094
-5.250 -0.1152 0.03707 0.03415 -0.0774 0.7388 0.0118
-5.000 -0.0871 0.03513 0.03211 -0.0793 0.7320 0.0121
-4.750 -0.0590 0.03337 0.03024 -0.0809 0.7256 0.0125
-4.500 -0.0210 0.02101 0.01715 -0.0867 0.7210 0.0159
-4.250 0.0068 0.02014 0.01615 -0.0872 0.7143 0.0162
-4.000 0.0347 0.01912 0.01501 -0.0876 0.7094 0.0166
-3.750 0.0629 0.01787 0.01359 -0.0881 0.7049 0.0174
-3.500 0.0922 0.01450 0.00967 -0.0887 0.7004 0.0192
-3.250 0.1209 0.01373 0.00865 -0.0889 0.6953 0.0200
-3.000 0.1495 0.01332 0.00809 -0.0890 0.6878 0.0202
-2.750 0.1779 0.01209 0.00658 -0.0893 0.6802 0.0206
-2.500 0.2062 0.01122 0.00556 -0.0896 0.6726 0.0209
-2.250 0.2347 0.01071 0.00495 -0.0898 0.6667 0.0211
-2.000 0.2632 0.01038 0.00456 -0.0900 0.6589 0.0215
-1.750 0.2917 0.01004 0.00414 -0.0901 0.6498 0.0218
-1.500 0.3202 0.00970 0.00370 -0.0902 0.6390 0.0221
-1.250 0.3486 0.00941 0.00333 -0.0904 0.6260 0.0225
-1.000 0.3771 0.00919 0.00302 -0.0905 0.6104 0.0230
-0.750 0.4054 0.00903 0.00275 -0.0906 0.5906 0.0235
-0.500 0.4336 0.00893 0.00253 -0.0907 0.5648 0.0240
-0.250 0.4617 0.00886 0.00234 -0.0909 0.5403 0.0244
0.000 0.4899 0.00882 0.00220 -0.0910 0.5167 0.0247
0.250 0.5180 0.00880 0.00207 -0.0911 0.4927 0.0249
0.500 0.5460 0.00881 0.00198 -0.0913 0.4708 0.0251
0.750 0.5741 0.00883 0.00191 -0.0914 0.4506 0.0253
1.000 0.6021 0.00886 0.00188 -0.0915 0.4345 0.0257
1.250 0.6303 0.00888 0.00184 -0.0917 0.4219 0.0259
1.500 0.6584 0.00887 0.00179 -0.0918 0.4113 0.0260
1.750 0.6865 0.00888 0.00177 -0.0919 0.4009 0.0260
2.000 0.7147 0.00890 0.00176 -0.0921 0.3916 0.0262
2.250 0.7427 0.00895 0.00178 -0.0922 0.3819 0.0263
2.500 0.7707 0.00898 0.00178 -0.0923 0.3716 0.0271
2.750 0.7987 0.00904 0.00180 -0.0924 0.3610 0.0289
3.000 0.8261 0.00920 0.00188 -0.0925 0.3405 0.0304
3.250 0.8533 0.00942 0.00199 -0.0925 0.3140 0.0317
3.500 0.8804 0.00962 0.00212 -0.0926 0.2938 0.0330
4.000 0.9340 0.01011 0.00248 -0.0926 0.2505 0.0679
4.250 0.9611 0.01028 0.00264 -0.0927 0.2385 0.0872
4.500 0.9883 0.01037 0.00284 -0.0927 0.2310 0.1511
4.750 1.0154 0.01052 0.00303 -0.0928 0.2238 0.1809
5.250 1.0646 0.00959 0.00359 -0.0922 0.2027 1.0000
5.750 1.1166 0.01021 0.00406 -0.0920 0.1690 1.0000
6.000 1.1351 0.01164 0.00495 -0.0911 0.0701 1.0000
6.250 1.1578 0.01238 0.00551 -0.0906 0.0339 1.0000
6.500 1.1830 0.01274 0.00585 -0.0903 0.0273 1.0000
6.750 1.2084 0.01302 0.00616 -0.0901 0.0249 1.0000
7.000 1.2329 0.01343 0.00655 -0.0898 0.0189 1.0000
7.250 1.2575 0.01380 0.00692 -0.0895 0.0155 1.0000
7.500 1.2814 0.01424 0.00734 -0.0891 0.0122 1.0000
7.750 1.3056 0.01461 0.00774 -0.0887 0.0110 1.0000
8.000 1.3292 0.01503 0.00818 -0.0882 0.0097 1.0000
8.250 1.3519 0.01555 0.00870 -0.0877 0.0082 1.0000
8.500 1.3751 0.01597 0.00917 -0.0872 0.0076 1.0000
8.750 1.3976 0.01644 0.00968 -0.0866 0.0070 1.0000
9.000 1.4194 0.01695 0.01022 -0.0859 0.0064 1.0000
9.250 1.4401 0.01754 0.01085 -0.0851 0.0058 1.0000
9.500 1.4597 0.01822 0.01158 -0.0841 0.0054 1.0000
9.750 1.4796 0.01880 0.01223 -0.0832 0.0052 1.0000
10.000 1.4986 0.01942 0.01291 -0.0821 0.0049 1.0000
10.250 1.5167 0.02006 0.01361 -0.0810 0.0046 1.0000
10.500 1.5339 0.02072 0.01431 -0.0797 0.0043 1.0000
10.750 1.5489 0.02145 0.01510 -0.0781 0.0040 1.0000
11.000 1.5588 0.02232 0.01603 -0.0758 0.0038 1.0000
11.250 1.5649 0.02350 0.01732 -0.0731 0.0036 1.0000
11.500 1.5737 0.02459 0.01849 -0.0710 0.0035 1.0000
11.750 1.5826 0.02574 0.01972 -0.0692 0.0034 1.0000
12.000 1.5905 0.02703 0.02111 -0.0674 0.0034 1.0000
12.250 1.5974 0.02847 0.02264 -0.0657 0.0033 1.0000
12.500 1.6032 0.03007 0.02434 -0.0641 0.0032 1.0000
12.750 1.6081 0.03183 0.02620 -0.0627 0.0031 1.0000
13.000 1.6124 0.03373 0.02821 -0.0614 0.0030 1.0000
13.250 1.6154 0.03583 0.03041 -0.0602 0.0029 1.0000
13.500 1.6179 0.03807 0.03275 -0.0592 0.0028 1.0000
13.750 1.6190 0.04052 0.03530 -0.0584 0.0028 1.0000
14.000 1.6190 0.04317 0.03805 -0.0576 0.0027 1.0000
14.250 1.6179 0.04604 0.04103 -0.0571 0.0027 1.0000
14.500 1.6160 0.04904 0.04414 -0.0566 0.0026 1.0000
14.750 1.6124 0.05237 0.04757 -0.0564 0.0026 1.0000
15.000 1.6075 0.05598 0.05130 -0.0564 0.0025 1.0000
15.250 1.6021 0.05982 0.05524 -0.0566 0.0025 1.0000
15.500 1.5953 0.06402 0.05956 -0.0571 0.0024 1.0000
15.750 1.5869 0.06861 0.06428 -0.0579 0.0024 1.0000
16.000 1.5775 0.07348 0.06927 -0.0589 0.0024 1.0000
16.250 1.5666 0.07872 0.07463 -0.0601 0.0023 1.0000
16.500 1.5550 0.08422 0.08025 -0.0616 0.0023 1.0000
16.750 1.5423 0.08994 0.08609 -0.0632 0.0023 1.0000
17.000 1.5276 0.09607 0.09236 -0.0651 0.0022 1.0000
17.250 1.5132 0.10225 0.09867 -0.0671 0.0022 1.0000
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Polar data table (+)
Polar graphs
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