UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Reynolds number: 500,000 Max Cl/Cd: 93.28 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gu255118-il-500000-n5.txt Download as CSV file: xf-gu255118-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF GLASGOW GU25-5(11)8 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
------ -------- --------- --------- -------- -------- --------
-12.250 0.1498 0.08947 0.08460 -0.1618 0.6184 0.0168
-12.000 0.1490 0.08596 0.08110 -0.1630 0.6177 0.0169
-11.750 0.1472 0.08238 0.07753 -0.1642 0.6168 0.0171
-11.500 0.1415 0.07825 0.07343 -0.1656 0.6161 0.0177
-11.250 -0.0592 0.04254 0.03769 -0.1822 0.6168 0.0177
-11.000 -0.1150 0.03692 0.03183 -0.1809 0.6160 0.0177
-10.750 -0.1451 0.03407 0.02879 -0.1766 0.6151 0.0178
-10.500 -0.1720 0.03169 0.02619 -0.1708 0.6142 0.0179
-10.250 -0.1919 0.02986 0.02412 -0.1649 0.6134 0.0180
-10.000 -0.1994 0.02801 0.02199 -0.1606 0.6125 0.0184
-9.500 -0.1932 0.02509 0.01859 -0.1545 0.6109 0.0188
-9.250 -0.1831 0.02397 0.01726 -0.1522 0.6102 0.0191
-9.000 -0.1691 0.02317 0.01628 -0.1503 0.6094 0.0193
-8.750 -0.1556 0.02208 0.01507 -0.1486 0.6087 0.0196
-8.500 -0.1381 0.02143 0.01434 -0.1473 0.6079 0.0198
-8.250 -0.1191 0.02092 0.01378 -0.1462 0.6071 0.0201
-8.000 -0.0997 0.02040 0.01318 -0.1451 0.6063 0.0204
-7.750 -0.0799 0.01983 0.01253 -0.1441 0.6056 0.0206
-7.500 -0.0594 0.01934 0.01195 -0.1431 0.6048 0.0210
-7.250 -0.0387 0.01879 0.01131 -0.1422 0.6041 0.0212
-7.000 -0.0173 0.01830 0.01074 -0.1413 0.6034 0.0216
-6.750 0.0042 0.01780 0.01014 -0.1405 0.6026 0.0220
-6.500 0.0262 0.01736 0.00961 -0.1397 0.6018 0.0224
-6.250 0.0484 0.01693 0.00911 -0.1389 0.6011 0.0228
-6.000 0.0709 0.01656 0.00866 -0.1382 0.6003 0.0231
-5.750 0.0939 0.01626 0.00828 -0.1375 0.5996 0.0235
-5.500 0.1160 0.01587 0.00783 -0.1367 0.5990 0.0240
-5.250 0.1378 0.01548 0.00743 -0.1359 0.5984 0.0245
-5.000 0.1607 0.01522 0.00714 -0.1352 0.5978 0.0250
-4.750 0.1839 0.01499 0.00688 -0.1347 0.5972 0.0256
-4.500 0.2071 0.01476 0.00661 -0.1340 0.5966 0.0261
-4.250 0.2301 0.01453 0.00636 -0.1334 0.5961 0.0266
-4.000 0.2530 0.01433 0.00614 -0.1327 0.5957 0.0273
-3.750 0.2760 0.01414 0.00593 -0.1320 0.5953 0.0279
-3.500 0.2993 0.01399 0.00575 -0.1313 0.5948 0.0285
-3.250 0.3218 0.01379 0.00555 -0.1306 0.5944 0.0293
-3.000 0.3445 0.01360 0.00537 -0.1298 0.5939 0.0304
-2.750 0.3680 0.01349 0.00525 -0.1293 0.5934 0.0315
-2.500 0.3917 0.01338 0.00514 -0.1287 0.5929 0.0325
-2.250 0.4156 0.01330 0.00504 -0.1282 0.5924 0.0337
-2.000 0.4396 0.01323 0.00495 -0.1277 0.5919 0.0348
-1.750 0.4633 0.01314 0.00487 -0.1272 0.5914 0.0369
-1.500 0.4872 0.01308 0.00482 -0.1267 0.5909 0.0400
-1.250 0.5110 0.01302 0.00478 -0.1262 0.5904 0.0464
-1.000 0.5336 0.01289 0.00476 -0.1255 0.5900 0.0737
-0.750 0.5551 0.01270 0.00475 -0.1246 0.5895 0.1289
-0.500 0.5752 0.01243 0.00475 -0.1235 0.5890 0.2167
-0.250 0.5931 0.01206 0.00477 -0.1220 0.5885 0.3436
0.000 0.6092 0.01170 0.00483 -0.1201 0.5881 0.4827
0.250 0.6278 0.01154 0.00491 -0.1186 0.5876 0.5647
0.500 0.6444 0.01135 0.00501 -0.1165 0.5871 0.6488
0.750 0.6579 0.01111 0.00511 -0.1137 0.5866 0.7508
1.250 0.8276 0.01131 0.00572 -0.1391 0.5858 0.9342
1.500 0.8612 0.01147 0.00585 -0.1408 0.5854 0.9453
2.000 0.9247 0.01180 0.00613 -0.1433 0.5846 0.9630
2.500 0.9897 0.01213 0.00642 -0.1463 0.5839 0.9752
2.750 1.0225 0.01230 0.00657 -0.1479 0.5835 0.9803
3.000 1.0560 0.01247 0.00672 -0.1497 0.5831 0.9842
3.250 1.0922 0.01263 0.00687 -0.1521 0.5828 0.9871
3.500 1.1268 0.01281 0.00704 -0.1542 0.5824 0.9902
3.750 1.1606 0.01300 0.00723 -0.1561 0.5820 0.9932
4.000 1.1961 0.01318 0.00741 -0.1584 0.5816 0.9955
4.250 1.2310 0.01337 0.00761 -0.1606 0.5812 0.9980
4.500 1.2630 0.01354 0.00783 -0.1623 0.5807 1.0000
4.750 1.2781 0.01374 0.00807 -0.1602 0.5802 1.0000
5.000 1.2933 0.01395 0.00832 -0.1582 0.5797 1.0000
5.250 1.3081 0.01417 0.00858 -0.1562 0.5792 1.0000
5.500 1.3214 0.01441 0.00886 -0.1538 0.5785 1.0000
5.750 1.3321 0.01463 0.00913 -0.1509 0.5774 1.0000
6.000 1.3420 0.01484 0.00939 -0.1479 0.5762 1.0000
6.250 1.3500 0.01504 0.00963 -0.1444 0.5752 1.0000
6.500 1.3571 0.01524 0.00986 -0.1408 0.5742 1.0000
6.750 1.3668 0.01544 0.01011 -0.1377 0.5732 1.0000
7.000 1.3789 0.01565 0.01036 -0.1352 0.5723 1.0000
7.250 1.3935 0.01586 0.01060 -0.1332 0.5713 1.0000
7.500 1.4104 0.01604 0.01080 -0.1317 0.5704 1.0000
7.750 1.4295 0.01621 0.01101 -0.1307 0.5695 1.0000
8.000 1.4522 0.01631 0.01113 -0.1303 0.5685 1.0000
8.250 1.4779 0.01639 0.01122 -0.1305 0.5674 1.0000
8.500 1.4918 0.01667 0.01154 -0.1285 0.5660 1.0000
8.750 1.4617 0.01780 0.01282 -0.1192 0.5631 1.0000
9.000 1.4492 0.01890 0.01401 -0.1134 0.5602 1.0000
9.250 1.4560 0.01949 0.01465 -0.1109 0.5576 1.0000
9.500 1.4805 0.01937 0.01454 -0.1108 0.5551 1.0000
9.750 1.5132 0.01894 0.01410 -0.1120 0.5526 1.0000
10.000 1.4851 0.02121 0.01650 -0.1050 0.5490 1.0000
10.250 1.4428 0.02474 0.02017 -0.0971 0.5429 1.0000
10.500 1.4764 0.02404 0.01945 -0.0982 0.5390 1.0000
11.250 1.2607 0.04566 0.04137 -0.0718 0.4896 1.0000
11.500 1.2909 0.04514 0.04086 -0.0725 0.4856 1.0000
12.000 1.3581 0.04345 0.03912 -0.0743 0.4691 1.0000
12.250 1.3873 0.04285 0.03842 -0.0747 0.4545 1.0000
12.500 1.3969 0.04388 0.03935 -0.0735 0.4354 1.0000
12.750 1.3983 0.04563 0.04100 -0.0717 0.4170 1.0000
13.000 1.3851 0.04864 0.04384 -0.0687 0.3908 1.0000
13.250 1.3668 0.05220 0.04722 -0.0655 0.3624 1.0000
13.500 1.3554 0.05531 0.05022 -0.0631 0.3401 1.0000
13.750 1.3408 0.05878 0.05355 -0.0605 0.3147 1.0000
14.000 1.3358 0.06149 0.05617 -0.0588 0.2961 1.0000
14.250 1.3236 0.06489 0.05943 -0.0566 0.2709 1.0000
14.500 1.3167 0.06787 0.06229 -0.0549 0.2491 1.0000
14.750 1.3125 0.07063 0.06496 -0.0535 0.2289 1.0000
15.000 1.3053 0.07375 0.06797 -0.0519 0.2061 1.0000
15.250 1.3011 0.07660 0.07070 -0.0506 0.1846 1.0000
15.500 1.2981 0.07936 0.07336 -0.0495 0.1653 1.0000
15.750 1.2942 0.08225 0.07615 -0.0484 0.1455 1.0000
16.000 1.2883 0.08539 0.07913 -0.0472 0.1208 1.0000
16.250 1.2872 0.08810 0.08177 -0.0464 0.1051 1.0000
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Polar data table (+)
Polar graphs
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