GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.55 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe174-il-1000000-n5.txt Download as CSV file: xf-goe174-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 174 (ALBATROS 5020) 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3282 0.12025 0.11858 -0.0218 1.0000 0.0048
-10.500 -0.3228 0.11734 0.11568 -0.0226 1.0000 0.0049
-10.250 -0.3180 0.11425 0.11261 -0.0234 1.0000 0.0050
-7.750 -0.2292 0.07570 0.07362 -0.0524 0.8357 0.0068
-6.250 -0.0949 0.01790 0.01396 -0.1134 0.7587 0.0144
-6.000 -0.0689 0.01782 0.01372 -0.1131 0.7234 0.0146
-5.750 -0.0438 0.01786 0.01351 -0.1126 0.6711 0.0148
-5.500 -0.0179 0.01795 0.01343 -0.1123 0.6390 0.0151
-5.250 0.0088 0.01765 0.01298 -0.1123 0.6221 0.0156
-5.000 0.0357 0.01554 0.01044 -0.1127 0.6127 0.0171
-4.750 0.0628 0.01378 0.00825 -0.1128 0.6047 0.0183
-4.500 0.0905 0.01355 0.00796 -0.1129 0.5970 0.0186
-4.250 0.1182 0.01333 0.00766 -0.1129 0.5899 0.0189
-4.000 0.1461 0.01303 0.00727 -0.1129 0.5842 0.0193
-3.750 0.1740 0.01276 0.00692 -0.1129 0.5774 0.0197
-3.500 0.2018 0.01241 0.00646 -0.1129 0.5706 0.0203
-3.250 0.2299 0.01190 0.00581 -0.1129 0.5636 0.0208
-2.750 0.2861 0.01112 0.00480 -0.1129 0.5508 0.0219
-2.500 0.3141 0.01095 0.00453 -0.1128 0.5431 0.0224
-2.250 0.3422 0.01073 0.00423 -0.1128 0.5346 0.0227
-2.000 0.3701 0.01058 0.00398 -0.1127 0.5227 0.0228
-1.750 0.3975 0.01005 0.00335 -0.1126 0.5077 0.0232
-1.500 0.4251 0.00975 0.00296 -0.1126 0.4920 0.0235
-1.250 0.4527 0.00956 0.00271 -0.1125 0.4777 0.0238
-1.000 0.4802 0.00943 0.00251 -0.1124 0.4621 0.0240
-0.750 0.5077 0.00936 0.00236 -0.1123 0.4441 0.0244
-0.500 0.5350 0.00934 0.00225 -0.1121 0.4253 0.0248
-0.250 0.5623 0.00932 0.00214 -0.1120 0.4081 0.0251
0.000 0.5897 0.00930 0.00205 -0.1119 0.3926 0.0255
0.250 0.6172 0.00930 0.00198 -0.1118 0.3785 0.0259
0.500 0.6446 0.00932 0.00194 -0.1117 0.3655 0.0265
0.750 0.6721 0.00935 0.00191 -0.1116 0.3540 0.0271
1.000 0.6994 0.00941 0.00191 -0.1115 0.3433 0.0277
1.250 0.7270 0.00945 0.00191 -0.1114 0.3346 0.0281
1.500 0.7544 0.00950 0.00193 -0.1113 0.3272 0.0285
1.750 0.7818 0.00956 0.00196 -0.1112 0.3187 0.0288
2.000 0.8092 0.00963 0.00200 -0.1111 0.3124 0.0290
2.250 0.8367 0.00968 0.00203 -0.1110 0.3054 0.0303
2.500 0.8638 0.00979 0.00208 -0.1109 0.2964 0.0317
3.000 0.9182 0.00997 0.00224 -0.1107 0.2833 0.0360
3.250 0.9456 0.00988 0.00239 -0.1107 0.2764 0.1868
3.500 0.9724 0.00998 0.00252 -0.1106 0.2685 0.2213
3.750 0.9997 0.00954 0.00277 -0.1110 0.2632 0.5658
4.250 1.0496 0.00901 0.00306 -0.1098 0.2512 1.0000
4.500 1.0763 0.00918 0.00320 -0.1097 0.2438 1.0000
4.750 1.1026 0.00938 0.00336 -0.1095 0.2342 1.0000
5.000 1.1286 0.00962 0.00353 -0.1092 0.2236 1.0000
5.250 1.1544 0.00987 0.00373 -0.1089 0.2114 1.0000
5.500 1.1796 0.01017 0.00395 -0.1086 0.1967 1.0000
5.750 1.2039 0.01056 0.00424 -0.1081 0.1756 1.0000
6.000 1.2228 0.01153 0.00489 -0.1068 0.1219 1.0000
6.250 1.2470 0.01191 0.00521 -0.1063 0.1105 1.0000
6.500 1.2715 0.01225 0.00551 -0.1058 0.1036 1.0000
6.750 1.2961 0.01255 0.00580 -0.1054 0.0961 1.0000
7.000 1.3154 0.01341 0.00644 -0.1042 0.0560 1.0000
7.250 1.3390 0.01379 0.00681 -0.1036 0.0510 1.0000
7.500 1.3625 0.01417 0.00720 -0.1030 0.0455 1.0000
7.750 1.3864 0.01448 0.00754 -0.1024 0.0426 1.0000
8.000 1.4086 0.01496 0.00800 -0.1017 0.0355 1.0000
8.250 1.4272 0.01575 0.00865 -0.1003 0.0156 1.0000
8.500 1.4485 0.01625 0.00917 -0.0994 0.0120 1.0000
8.750 1.4702 0.01669 0.00964 -0.0986 0.0107 1.0000
9.000 1.4909 0.01719 0.01017 -0.0976 0.0095 1.0000
9.250 1.5110 0.01772 0.01074 -0.0965 0.0084 1.0000
9.500 1.5312 0.01820 0.01126 -0.0955 0.0078 1.0000
9.750 1.5504 0.01873 0.01182 -0.0943 0.0071 1.0000
10.000 1.5682 0.01933 0.01245 -0.0929 0.0065 1.0000
10.250 1.5843 0.02000 0.01319 -0.0912 0.0060 1.0000
10.500 1.6004 0.02059 0.01383 -0.0896 0.0057 1.0000
10.750 1.6134 0.02122 0.01452 -0.0873 0.0054 1.0000
11.000 1.6254 0.02192 0.01527 -0.0851 0.0052 1.0000
11.250 1.6365 0.02269 0.01610 -0.0828 0.0049 1.0000
11.500 1.6463 0.02357 0.01705 -0.0805 0.0047 1.0000
11.750 1.6547 0.02458 0.01813 -0.0781 0.0044 1.0000
12.000 1.6607 0.02583 0.01945 -0.0758 0.0042 1.0000
12.250 1.6662 0.02722 0.02092 -0.0736 0.0041 1.0000
12.500 1.6732 0.02858 0.02237 -0.0719 0.0040 1.0000
12.750 1.6795 0.03009 0.02397 -0.0704 0.0038 1.0000
13.000 1.6846 0.03182 0.02579 -0.0690 0.0037 1.0000
13.250 1.6881 0.03379 0.02785 -0.0678 0.0036 1.0000
13.500 1.6906 0.03597 0.03012 -0.0668 0.0035 1.0000
13.750 1.6914 0.03845 0.03270 -0.0659 0.0034 1.0000
14.000 1.6909 0.04119 0.03554 -0.0653 0.0033 1.0000
14.250 1.6892 0.04425 0.03871 -0.0651 0.0032 1.0000
14.500 1.6861 0.04762 0.04218 -0.0650 0.0031 1.0000
14.750 1.6808 0.05138 0.04605 -0.0652 0.0031 1.0000
15.000 1.6739 0.05543 0.05021 -0.0656 0.0030 1.0000
15.250 1.6649 0.05980 0.05469 -0.0660 0.0030 1.0000
15.500 1.6540 0.06449 0.05949 -0.0667 0.0029 1.0000
15.750 1.6412 0.06962 0.06474 -0.0675 0.0029 1.0000
16.000 1.6273 0.07501 0.07025 -0.0686 0.0028 1.0000
16.250 1.6123 0.08069 0.07604 -0.0699 0.0028 1.0000
16.500 1.5961 0.08671 0.08218 -0.0714 0.0028 1.0000
16.750 1.5807 0.09270 0.08830 -0.0730 0.0027 1.0000
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Polar data table (+)
Polar graphs
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