UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.44 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gu255118-il-1000000-n5.txt Download as CSV file: xf-gu255118-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.2881 0.04433 0.04003 -0.1821 0.6109 0.0143
-14.250 -0.3364 0.03648 0.03196 -0.1864 0.6103 0.0142
-14.000 -0.3425 0.03396 0.02936 -0.1871 0.6093 0.0143
-13.750 -0.3603 0.03097 0.02623 -0.1867 0.6085 0.0144
-13.500 -0.3746 0.02868 0.02381 -0.1851 0.6074 0.0144
-13.250 -0.3808 0.02713 0.02216 -0.1829 0.6063 0.0145
-13.000 -0.3838 0.02588 0.02079 -0.1804 0.6052 0.0146
-12.750 -0.3840 0.02484 0.01965 -0.1777 0.6040 0.0147
-12.500 -0.3874 0.02365 0.01834 -0.1743 0.6029 0.0148
-12.250 -0.3842 0.02284 0.01742 -0.1713 0.6018 0.0149
-12.000 -0.3806 0.02206 0.01654 -0.1681 0.6008 0.0150
-11.750 -0.3767 0.02134 0.01573 -0.1647 0.5996 0.0151
-11.500 -0.3709 0.02084 0.01512 -0.1614 0.5986 0.0152
-11.250 -0.3621 0.02024 0.01442 -0.1587 0.5974 0.0153
-11.000 -0.3487 0.01973 0.01382 -0.1567 0.5963 0.0154
-10.750 -0.3348 0.01915 0.01315 -0.1548 0.5958 0.0155
-10.500 -0.3188 0.01865 0.01257 -0.1532 0.5952 0.0156
-10.250 -0.3068 0.01780 0.01163 -0.1510 0.5946 0.0158
-10.000 -0.2896 0.01733 0.01111 -0.1495 0.5939 0.0161
-9.750 -0.2711 0.01691 0.01063 -0.1482 0.5932 0.0162
-9.500 -0.2513 0.01656 0.01024 -0.1471 0.5925 0.0164
-9.250 -0.2310 0.01622 0.00985 -0.1460 0.5917 0.0165
-9.000 -0.2098 0.01594 0.00953 -0.1451 0.5910 0.0167
-8.750 -0.1887 0.01563 0.00918 -0.1442 0.5902 0.0169
-8.500 -0.1670 0.01535 0.00886 -0.1433 0.5895 0.0172
-8.250 -0.1452 0.01507 0.00854 -0.1425 0.5889 0.0174
-8.000 -0.1235 0.01477 0.00818 -0.1416 0.5881 0.0177
-7.750 -0.1019 0.01445 0.00781 -0.1407 0.5874 0.0179
-7.500 -0.0797 0.01417 0.00748 -0.1399 0.5867 0.0182
-7.250 -0.0579 0.01387 0.00712 -0.1390 0.5860 0.0184
-7.000 -0.0355 0.01362 0.00683 -0.1382 0.5852 0.0186
-6.750 -0.0132 0.01336 0.00652 -0.1374 0.5845 0.0189
-6.500 0.0095 0.01314 0.00626 -0.1366 0.5837 0.0191
-6.250 0.0325 0.01295 0.00602 -0.1359 0.5829 0.0192
-6.000 0.0540 0.01265 0.00568 -0.1349 0.5822 0.0195
-5.750 0.0759 0.01238 0.00539 -0.1340 0.5814 0.0200
-5.500 0.0993 0.01219 0.00518 -0.1334 0.5811 0.0204
-5.250 0.1231 0.01201 0.00499 -0.1328 0.5808 0.0207
-5.000 0.1472 0.01185 0.00482 -0.1323 0.5805 0.0211
-4.750 0.1715 0.01171 0.00468 -0.1319 0.5801 0.0216
-4.500 0.1956 0.01157 0.00451 -0.1313 0.5798 0.0221
-4.250 0.2196 0.01142 0.00435 -0.1308 0.5794 0.0225
-4.000 0.2439 0.01129 0.00421 -0.1303 0.5790 0.0230
-3.750 0.2682 0.01117 0.00407 -0.1298 0.5786 0.0233
-3.500 0.2927 0.01106 0.00395 -0.1294 0.5782 0.0236
-3.250 0.3161 0.01089 0.00377 -0.1288 0.5777 0.0243
-3.000 0.3400 0.01076 0.00363 -0.1282 0.5773 0.0251
-2.750 0.3644 0.01066 0.00353 -0.1278 0.5769 0.0257
-2.500 0.3890 0.01058 0.00345 -0.1273 0.5765 0.0266
-2.250 0.4136 0.01051 0.00338 -0.1270 0.5761 0.0276
-2.000 0.4383 0.01044 0.00331 -0.1266 0.5757 0.0283
-1.750 0.4630 0.01039 0.00325 -0.1262 0.5752 0.0289
-1.500 0.4871 0.01030 0.00317 -0.1257 0.5748 0.0308
-1.250 0.5117 0.01025 0.00313 -0.1253 0.5744 0.0323
-1.000 0.5362 0.01021 0.00309 -0.1249 0.5740 0.0341
-0.750 0.5605 0.01016 0.00306 -0.1244 0.5736 0.0390
-0.500 0.5831 0.01003 0.00303 -0.1237 0.5732 0.0697
-0.250 0.6054 0.00988 0.00302 -0.1229 0.5728 0.1121
0.000 0.6261 0.00968 0.00302 -0.1218 0.5724 0.1832
0.500 0.6647 0.00920 0.00304 -0.1192 0.5716 0.3638
0.750 0.6808 0.00892 0.00308 -0.1171 0.5713 0.4795
1.000 0.6971 0.00871 0.00314 -0.1151 0.5709 0.5686
1.250 0.7126 0.00853 0.00320 -0.1128 0.5705 0.6509
1.500 0.7240 0.00832 0.00329 -0.1095 0.5700 0.7458
1.750 0.7410 0.00807 0.00343 -0.1074 0.5696 0.8645
2.000 0.8881 0.00837 0.00384 -0.1344 0.5694 0.9419
2.250 0.9290 0.00851 0.00396 -0.1377 0.5689 0.9500
2.750 0.9921 0.00879 0.00421 -0.1402 0.5680 0.9654
3.000 1.0196 0.00891 0.00432 -0.1406 0.5676 0.9719
3.250 1.0541 0.00905 0.00445 -0.1425 0.5671 0.9751
3.500 1.0861 0.00919 0.00458 -0.1439 0.5667 0.9790
4.000 1.1488 0.00944 0.00484 -0.1466 0.5662 0.9849
4.250 1.1824 0.00955 0.00497 -0.1484 0.5660 0.9869
4.500 1.2146 0.00967 0.00510 -0.1499 0.5658 0.9891
4.750 1.2454 0.00979 0.00524 -0.1512 0.5655 0.9913
5.000 1.2752 0.00992 0.00539 -0.1522 0.5653 0.9934
5.250 1.3087 0.01003 0.00552 -0.1541 0.5649 0.9951
5.500 1.3415 0.01013 0.00565 -0.1558 0.5645 0.9968
5.750 1.3746 0.01023 0.00579 -0.1577 0.5639 0.9984
6.000 1.4086 0.01034 0.00592 -0.1597 0.5632 0.9998
6.250 1.4247 0.01041 0.00603 -0.1578 0.5623 1.0000
6.500 1.4353 0.01048 0.00613 -0.1547 0.5614 1.0000
6.750 1.4480 0.01056 0.00624 -0.1521 0.5606 1.0000
7.000 1.4615 0.01065 0.00637 -0.1497 0.5597 1.0000
7.250 1.4761 0.01075 0.00650 -0.1475 0.5588 1.0000
7.500 1.4900 0.01085 0.00662 -0.1452 0.5575 1.0000
7.750 1.5009 0.01093 0.00672 -0.1423 0.5553 1.0000
8.000 1.5173 0.01104 0.00681 -0.1407 0.5524 1.0000
8.250 1.5308 0.01123 0.00705 -0.1385 0.5511 1.0000
8.500 1.5378 0.01147 0.00736 -0.1351 0.5489 1.0000
8.750 1.5439 0.01175 0.00769 -0.1317 0.5449 1.0000
9.000 1.5554 0.01203 0.00802 -0.1294 0.5419 1.0000
9.250 1.5655 0.01240 0.00837 -0.1269 0.5378 1.0000
9.500 1.5761 0.01286 0.00892 -0.1247 0.5337 1.0000
9.750 1.5832 0.01348 0.00957 -0.1221 0.5265 1.0000
10.000 1.5893 0.01425 0.01038 -0.1195 0.5170 1.0000
10.250 1.5861 0.01554 0.01166 -0.1157 0.5007 1.0000
10.500 1.5669 0.01782 0.01387 -0.1102 0.4803 1.0000
10.750 1.5194 0.02202 0.01797 -0.1017 0.4543 1.0000
11.000 1.4795 0.02620 0.02209 -0.0948 0.4318 1.0000
11.250 1.4606 0.02927 0.02514 -0.0905 0.4184 1.0000
11.500 1.4260 0.03356 0.02936 -0.0849 0.3973 1.0000
11.750 1.3926 0.03799 0.03371 -0.0797 0.3737 1.0000
12.000 1.3763 0.04125 0.03691 -0.0763 0.3568 1.0000
12.250 1.3526 0.04518 0.04073 -0.0724 0.3331 1.0000
12.500 1.3328 0.04885 0.04426 -0.0690 0.3064 1.0000
12.750 1.3258 0.05160 0.04694 -0.0668 0.2893 1.0000
13.000 1.3105 0.05504 0.05021 -0.0640 0.2592 1.0000
13.250 1.3033 0.05787 0.05293 -0.0620 0.2363 1.0000
13.500 1.2979 0.06056 0.05548 -0.0601 0.2119 1.0000
13.750 1.2920 0.06337 0.05816 -0.0584 0.1888 1.0000
14.000 1.2932 0.06557 0.06027 -0.0571 0.1717 1.0000
14.250 1.2905 0.06810 0.06266 -0.0557 0.1483 1.0000
14.500 1.2887 0.07063 0.06508 -0.0544 0.1275 1.0000
14.750 1.2875 0.07317 0.06751 -0.0532 0.1092 1.0000
15.250 1.2785 0.07891 0.07295 -0.0505 0.0625 1.0000
15.500 1.2810 0.08118 0.07517 -0.0497 0.0519 1.0000
15.750 1.2803 0.08377 0.07767 -0.0488 0.0365 1.0000
16.000 1.2718 0.08725 0.08101 -0.0475 0.0151 1.0000
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Polar data table (+)
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