GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 500,000 Max Cl/Cd: 87.04 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe176-il-500000-n5.txt Download as CSV file: xf-goe176-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 176 (ALBATROS 7020) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3086 0.11707 0.11478 -0.0280 1.0000 0.0079
-10.250 -0.3035 0.11439 0.11211 -0.0283 1.0000 0.0077
-10.000 -0.2996 0.11139 0.10913 -0.0288 1.0000 0.0075
-9.750 -0.2966 0.10825 0.10602 -0.0293 1.0000 0.0074
-9.500 -0.2944 0.10499 0.10278 -0.0299 1.0000 0.0073
-9.250 -0.2870 0.10101 0.09882 -0.0323 0.9987 0.0071
-9.000 -0.2752 0.09637 0.09419 -0.0364 0.9956 0.0071
-8.750 -0.2661 0.09187 0.08969 -0.0399 0.9903 0.0071
-8.250 -0.2533 0.08310 0.08096 -0.0458 0.9512 0.0071
-8.000 -0.2240 0.07535 0.07315 -0.0577 0.9250 0.0073
-7.750 -0.2029 0.06723 0.06490 -0.0692 0.8906 0.0076
-7.500 -0.1907 0.02352 0.01985 -0.1272 0.8613 0.0073
-7.250 -0.1636 0.01980 0.01549 -0.1302 0.8445 0.0075
-7.000 -0.1368 0.01777 0.01301 -0.1312 0.8293 0.0078
-6.750 -0.1099 0.01643 0.01132 -0.1317 0.8134 0.0080
-6.500 -0.0832 0.01515 0.00971 -0.1320 0.7959 0.0083
-6.250 -0.0564 0.01432 0.00866 -0.1321 0.7785 0.0087
-6.000 -0.0293 0.01377 0.00794 -0.1320 0.7623 0.0091
-5.750 -0.0019 0.01328 0.00730 -0.1320 0.7468 0.0096
-5.500 0.0256 0.01288 0.00674 -0.1319 0.7319 0.0104
-5.250 0.0532 0.01249 0.00617 -0.1318 0.7163 0.0112
-5.000 0.0809 0.01193 0.00543 -0.1318 0.7003 0.0119
-4.750 0.1086 0.01150 0.00486 -0.1318 0.6834 0.0130
-4.500 0.1362 0.01126 0.00447 -0.1317 0.6645 0.0141
-4.250 0.1638 0.01105 0.00412 -0.1315 0.6463 0.0155
-4.000 0.1917 0.01080 0.00373 -0.1314 0.6295 0.0175
-3.750 0.2194 0.01061 0.00343 -0.1313 0.6121 0.0202
-3.500 0.2471 0.01050 0.00318 -0.1311 0.5954 0.0229
-3.250 0.2749 0.01033 0.00290 -0.1310 0.5802 0.0275
-3.000 0.3028 0.01024 0.00270 -0.1309 0.5664 0.0322
-2.750 0.3307 0.01013 0.00250 -0.1308 0.5539 0.0388
-2.500 0.3588 0.01000 0.00231 -0.1308 0.5436 0.0523
-2.250 0.3868 0.00962 0.00215 -0.1310 0.5334 0.1287
-2.000 0.4147 0.00955 0.00215 -0.1309 0.5237 0.1714
-1.750 0.4425 0.00960 0.00213 -0.1308 0.5128 0.1872
-1.500 0.4702 0.00965 0.00213 -0.1306 0.5002 0.1989
-1.250 0.4979 0.00971 0.00212 -0.1305 0.4851 0.2055
-1.000 0.5252 0.00981 0.00212 -0.1303 0.4622 0.2137
-0.750 0.5506 0.01009 0.00216 -0.1298 0.4048 0.2229
-0.500 0.5753 0.01051 0.00227 -0.1292 0.3521 0.2293
0.000 0.6290 0.01084 0.00242 -0.1287 0.3257 0.2370
0.250 0.6560 0.01098 0.00250 -0.1285 0.3170 0.2420
0.500 0.6833 0.01109 0.00257 -0.1283 0.3107 0.2481
0.750 0.7105 0.01120 0.00266 -0.1282 0.3057 0.2556
1.000 0.7379 0.01129 0.00273 -0.1280 0.3019 0.2616
1.250 0.7654 0.01135 0.00281 -0.1279 0.2983 0.2670
1.500 0.7926 0.01145 0.00290 -0.1277 0.2932 0.2734
1.750 0.8196 0.01158 0.00301 -0.1275 0.2867 0.2802
2.000 0.8469 0.01166 0.00310 -0.1274 0.2805 0.2896
2.250 0.8739 0.01177 0.00321 -0.1272 0.2755 0.2997
2.500 0.9010 0.01186 0.00333 -0.1271 0.2715 0.3116
2.750 0.9283 0.01192 0.00345 -0.1270 0.2667 0.3273
3.000 0.9552 0.01202 0.00359 -0.1268 0.2605 0.3504
3.250 0.9822 0.01208 0.00374 -0.1267 0.2532 0.3923
3.500 1.0087 0.01215 0.00391 -0.1266 0.2424 0.4625
3.750 1.0349 0.01189 0.00415 -0.1266 0.2259 0.7053
4.250 1.0699 0.01292 0.00503 -0.1228 0.1212 1.0000
4.500 1.0949 0.01325 0.00532 -0.1223 0.1122 1.0000
4.750 1.1197 0.01358 0.00560 -0.1218 0.1046 1.0000
5.000 1.1447 0.01388 0.00587 -0.1213 0.0963 1.0000
5.250 1.1665 0.01452 0.00633 -0.1204 0.0627 1.0000
5.500 1.1908 0.01487 0.00668 -0.1199 0.0606 1.0000
5.750 1.2149 0.01523 0.00703 -0.1193 0.0584 1.0000
6.000 1.2390 0.01557 0.00739 -0.1187 0.0563 1.0000
6.250 1.2627 0.01594 0.00779 -0.1180 0.0533 1.0000
6.500 1.2866 0.01627 0.00816 -0.1174 0.0517 1.0000
6.750 1.3101 0.01662 0.00856 -0.1167 0.0503 1.0000
7.000 1.3329 0.01702 0.00900 -0.1160 0.0479 1.0000
7.250 1.3546 0.01751 0.00952 -0.1151 0.0451 1.0000
7.500 1.3767 0.01793 0.00999 -0.1142 0.0429 1.0000
7.750 1.3997 0.01824 0.01033 -0.1135 0.0397 1.0000
8.000 1.4195 0.01881 0.01078 -0.1124 0.0200 1.0000
8.250 1.4371 0.01955 0.01151 -0.1108 0.0131 1.0000
8.500 1.4551 0.02022 0.01226 -0.1093 0.0111 1.0000
8.750 1.4709 0.02100 0.01314 -0.1075 0.0094 1.0000
9.000 1.4879 0.02162 0.01384 -0.1059 0.0086 1.0000
9.250 1.5017 0.02231 0.01461 -0.1037 0.0079 1.0000
9.500 1.5136 0.02310 0.01547 -0.1013 0.0073 1.0000
9.750 1.5232 0.02405 0.01651 -0.0987 0.0068 1.0000
10.000 1.5326 0.02504 0.01760 -0.0962 0.0064 1.0000
10.250 1.5429 0.02599 0.01864 -0.0940 0.0061 1.0000
10.500 1.5518 0.02707 0.01981 -0.0917 0.0057 1.0000
10.750 1.5597 0.02829 0.02111 -0.0896 0.0054 1.0000
11.000 1.5663 0.02968 0.02261 -0.0876 0.0051 1.0000
11.250 1.5706 0.03135 0.02438 -0.0856 0.0049 1.0000
11.500 1.5717 0.03343 0.02657 -0.0838 0.0047 1.0000
11.750 1.5694 0.03601 0.02927 -0.0821 0.0046 1.0000
12.000 1.5708 0.03837 0.03175 -0.0810 0.0045 1.0000
12.250 1.5704 0.04104 0.03455 -0.0800 0.0043 1.0000
12.500 1.5685 0.04403 0.03767 -0.0793 0.0042 1.0000
12.750 1.5644 0.04739 0.04116 -0.0789 0.0041 1.0000
13.000 1.5592 0.05105 0.04495 -0.0787 0.0040 1.0000
13.250 1.5521 0.05509 0.04912 -0.0788 0.0040 1.0000
13.500 1.5439 0.05937 0.05354 -0.0790 0.0039 1.0000
13.750 1.5344 0.06397 0.05827 -0.0795 0.0038 1.0000
14.000 1.5241 0.06881 0.06324 -0.0802 0.0038 1.0000
14.250 1.5135 0.07378 0.06833 -0.0811 0.0037 1.0000
14.500 1.5017 0.07906 0.07374 -0.0821 0.0037 1.0000
14.750 1.4908 0.08432 0.07912 -0.0833 0.0036 1.0000
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Polar data table (+)
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