UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Reynolds number: 200,000 Max Cl/Cd: 38.32 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gu255118-il-200000-n5.txt Download as CSV file: xf-gu255118-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 0.1565 0.10101 0.09486 -0.1581 0.6551 0.0409
-12.000 0.1509 0.09724 0.09113 -0.1602 0.6541 0.0412
-11.750 0.1509 0.09383 0.08774 -0.1616 0.6531 0.0412
-11.250 0.1431 0.08230 0.07621 -0.1633 0.6512 0.0287
-11.000 0.1457 0.07958 0.07351 -0.1640 0.6502 0.0285
-10.750 0.1428 0.07599 0.06995 -0.1651 0.6493 0.0285
-10.500 0.1419 0.07294 0.06692 -0.1660 0.6482 0.0283
-10.250 0.1350 0.06892 0.06294 -0.1674 0.6474 0.0281
-10.000 0.1018 0.05943 0.05350 -0.1724 0.6466 0.0281
-9.750 0.0733 0.05306 0.04708 -0.1761 0.6457 0.0277
-9.500 0.0372 0.04844 0.04235 -0.1759 0.6448 0.0275
-9.250 0.0064 0.04538 0.03914 -0.1721 0.6440 0.0275
-9.000 -0.0206 0.04304 0.03660 -0.1669 0.6432 0.0276
-8.750 -0.0389 0.04036 0.03362 -0.1626 0.6424 0.0279
-8.500 -0.0481 0.03804 0.03102 -0.1588 0.6415 0.0280
-8.250 -0.0524 0.03587 0.02857 -0.1551 0.6406 0.0282
-8.000 -0.0522 0.03391 0.02629 -0.1518 0.6396 0.0283
-7.750 -0.0465 0.03231 0.02440 -0.1490 0.6386 0.0285
-7.500 -0.0384 0.03089 0.02265 -0.1463 0.6376 0.0288
-7.250 -0.0254 0.02949 0.02109 -0.1446 0.6367 0.0290
-7.000 -0.0096 0.02846 0.01993 -0.1431 0.6357 0.0294
-6.750 0.0074 0.02755 0.01888 -0.1417 0.6347 0.0298
-6.500 0.0258 0.02682 0.01803 -0.1405 0.6336 0.0304
-6.250 0.0452 0.02617 0.01727 -0.1395 0.6327 0.0311
-6.000 0.0653 0.02550 0.01647 -0.1385 0.6318 0.0320
-5.750 0.0861 0.02480 0.01559 -0.1375 0.6310 0.0328
-5.500 0.1078 0.02412 0.01475 -0.1367 0.6303 0.0333
-5.250 0.1303 0.02352 0.01401 -0.1360 0.6296 0.0338
-5.000 0.1532 0.02301 0.01338 -0.1353 0.6290 0.0343
-4.750 0.1758 0.02243 0.01274 -0.1347 0.6284 0.0350
-4.500 0.1980 0.02195 0.01225 -0.1340 0.6278 0.0357
-4.250 0.2204 0.02162 0.01190 -0.1334 0.6272 0.0368
-4.000 0.2430 0.02138 0.01163 -0.1328 0.6267 0.0384
-3.750 0.2604 0.02122 0.01147 -0.1311 0.6259 0.0396
-3.500 0.2773 0.02110 0.01134 -0.1294 0.6251 0.0405
-3.250 0.2937 0.02101 0.01125 -0.1275 0.6243 0.0413
-3.000 0.3086 0.02089 0.01116 -0.1255 0.6234 0.0426
-2.750 0.3243 0.02088 0.01117 -0.1235 0.6225 0.0439
-2.500 0.3400 0.02092 0.01121 -0.1216 0.6216 0.0457
-2.250 0.3557 0.02102 0.01129 -0.1197 0.6208 0.0484
-2.000 0.3706 0.02109 0.01139 -0.1176 0.6199 0.0516
-1.750 0.3859 0.02118 0.01149 -0.1156 0.6189 0.0559
-1.500 0.4015 0.02123 0.01157 -0.1136 0.6178 0.0633
-1.250 0.4168 0.02126 0.01167 -0.1117 0.6169 0.0821
-1.000 0.4293 0.02119 0.01184 -0.1093 0.6161 0.1414
-0.750 0.4386 0.02094 0.01204 -0.1064 0.6153 0.2670
-0.500 0.4446 0.02062 0.01232 -0.1029 0.6146 0.4320
-0.250 0.4530 0.02053 0.01263 -0.0995 0.6138 0.5539
0.000 0.4634 0.02049 0.01294 -0.0963 0.6132 0.6550
0.500 0.6949 0.02091 0.01390 -0.1324 0.6133 0.9647
0.750 0.7311 0.02127 0.01417 -0.1348 0.6129 0.9760
1.000 0.7687 0.02160 0.01443 -0.1375 0.6125 0.9849
1.250 0.8084 0.02193 0.01467 -0.1407 0.6121 0.9919
1.500 0.8499 0.02218 0.01484 -0.1443 0.6116 0.9975
4.000 0.5324 0.04944 0.04255 -0.0692 0.5554 1.0000
4.250 0.5553 0.04973 0.04279 -0.0689 0.5544 1.0000
4.500 0.5796 0.04992 0.04293 -0.0687 0.5536 1.0000
4.750 0.6046 0.05005 0.04300 -0.0687 0.5528 1.0000
5.000 0.6301 0.05013 0.04305 -0.0686 0.5522 1.0000
5.500 0.6292 0.05383 0.04676 -0.0644 0.5399 1.0000
5.750 0.6540 0.05395 0.04684 -0.0643 0.5390 1.0000
6.000 0.6789 0.05407 0.04694 -0.0643 0.5382 1.0000
6.250 0.7047 0.05410 0.04694 -0.0643 0.5376 1.0000
6.750 0.7090 0.05757 0.05044 -0.0608 0.5253 1.0000
7.000 0.7347 0.05755 0.05041 -0.0609 0.5245 1.0000
7.250 0.7604 0.05755 0.05040 -0.0609 0.5238 1.0000
7.750 0.7691 0.06081 0.05371 -0.0581 0.5117 1.0000
8.000 0.7944 0.06080 0.05371 -0.0581 0.5109 1.0000
8.500 0.8078 0.06383 0.05679 -0.0558 0.4993 1.0000
8.750 0.8330 0.06377 0.05674 -0.0558 0.4981 1.0000
9.000 0.8582 0.06372 0.05671 -0.0559 0.4973 1.0000
9.500 0.8744 0.06657 0.05964 -0.0540 0.4855 1.0000
9.750 0.8993 0.06652 0.05961 -0.0540 0.4845 1.0000
10.000 0.9253 0.06633 0.05946 -0.0542 0.4837 1.0000
10.500 0.9428 0.06916 0.06238 -0.0524 0.4717 1.0000
10.750 0.9687 0.06893 0.06218 -0.0526 0.4706 1.0000
12.750 1.0884 0.07561 0.06933 -0.0492 0.4336 1.0000
13.000 1.1104 0.07568 0.06946 -0.0492 0.4301 1.0000
13.250 1.1372 0.07523 0.06908 -0.0494 0.4280 1.0000
13.500 1.1670 0.07445 0.06837 -0.0498 0.4264 1.0000
14.000 1.1951 0.07634 0.07039 -0.0490 0.4127 1.0000
14.500 1.2363 0.07671 0.07087 -0.0488 0.3978 1.0000
14.750 1.2532 0.07725 0.07144 -0.0486 0.3852 1.0000
15.000 1.2759 0.07712 0.07129 -0.0485 0.3711 1.0000
15.250 1.3043 0.07624 0.07030 -0.0486 0.3514 1.0000
15.500 1.3159 0.07728 0.07125 -0.0481 0.3312 1.0000
15.750 1.3251 0.07857 0.07245 -0.0474 0.3109 1.0000
16.000 1.3288 0.08045 0.07419 -0.0464 0.2883 1.0000
16.250 1.3284 0.08285 0.07649 -0.0454 0.2657 1.0000
16.500 1.3241 0.08573 0.07924 -0.0443 0.2433 1.0000
16.750 1.3194 0.08873 0.08213 -0.0433 0.2217 1.0000
17.000 1.3133 0.09193 0.08523 -0.0424 0.2016 1.0000
17.250 1.3049 0.09546 0.08863 -0.0415 0.1788 1.0000
17.500 1.2969 0.09902 0.09208 -0.0407 0.1584 1.0000
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Polar data table (+)
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