Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 50,000 Max Cl/Cd: 23.08 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-50000-n5.txt Download as CSV file: xf-supermarine371ii-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-II (tip)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5524 0.09706 0.09070 -0.0221 1.0000 0.1122
-8.500 -0.5499 0.09322 0.08693 -0.0224 1.0000 0.1221
-8.000 -0.5561 0.07996 0.07351 -0.0340 1.0000 0.0459
-7.750 -0.5539 0.07593 0.06949 -0.0344 1.0000 0.0442
-7.500 -0.5549 0.07203 0.06552 -0.0352 1.0000 0.0444
-7.250 -0.5527 0.06821 0.06162 -0.0353 1.0000 0.0430
-7.000 -0.5511 0.06444 0.05771 -0.0353 1.0000 0.0435
-6.750 -0.5473 0.06085 0.05398 -0.0347 1.0000 0.0426
-6.500 -0.5433 0.05742 0.05037 -0.0336 1.0000 0.0422
-6.250 -0.5394 0.05417 0.04691 -0.0319 1.0000 0.0416
-6.000 -0.5353 0.05113 0.04363 -0.0296 1.0000 0.0405
-5.750 -0.5305 0.04816 0.04036 -0.0271 1.0000 0.0394
-5.500 -0.5241 0.04531 0.03697 -0.0244 1.0000 0.0382
-5.250 -0.5154 0.04251 0.03378 -0.0218 1.0000 0.0375
-5.000 -0.5040 0.03983 0.03066 -0.0194 1.0000 0.0370
-4.750 -0.4903 0.03726 0.02766 -0.0172 1.0000 0.0370
-4.500 -0.4742 0.03483 0.02481 -0.0152 1.0000 0.0375
-4.250 -0.4558 0.03254 0.02211 -0.0134 1.0000 0.0383
-4.000 -0.4368 0.03085 0.02004 -0.0119 1.0000 0.0436
-3.750 -0.4155 0.02912 0.01788 -0.0104 1.0000 0.0487
-3.500 -0.3923 0.02724 0.01582 -0.0091 1.0000 0.0512
-3.250 -0.3685 0.02577 0.01415 -0.0075 1.0000 0.0544
-3.000 -0.3421 0.02456 0.01261 -0.0067 0.9981 0.0588
-2.750 -0.3139 0.02334 0.01119 -0.0070 0.9945 0.0661
-2.500 -0.1103 0.01963 0.01004 -0.0294 1.0000 1.0000
-2.250 -0.1104 0.01962 0.00986 -0.0257 1.0000 1.0000
-2.000 -0.1103 0.01959 0.00967 -0.0220 1.0000 1.0000
-1.750 -0.1098 0.01954 0.00946 -0.0183 1.0000 1.0000
-1.500 -0.0963 0.01948 0.00912 -0.0170 0.9968 1.0000
-1.250 -0.0710 0.01948 0.00889 -0.0179 0.9905 1.0000
-1.000 -0.0459 0.01952 0.00873 -0.0187 0.9847 1.0000
-0.750 -0.0217 0.01958 0.00863 -0.0193 0.9790 1.0000
-0.500 0.0005 0.01966 0.00858 -0.0194 0.9736 1.0000
-0.250 0.0243 0.01977 0.00855 -0.0198 0.9685 1.0000
0.000 0.0459 0.01991 0.00860 -0.0197 0.9633 1.0000
0.250 0.0674 0.02007 0.00869 -0.0196 0.9582 1.0000
0.500 0.0939 0.02030 0.00886 -0.0204 0.9542 1.0000
0.750 0.1107 0.02048 0.00902 -0.0192 0.9483 1.0000
1.000 0.1345 0.02074 0.00928 -0.0194 0.9438 1.0000
1.250 0.1599 0.02104 0.00959 -0.0199 0.9397 1.0000
1.500 0.1788 0.02132 0.00989 -0.0191 0.9343 1.0000
1.750 0.2050 0.02166 0.01030 -0.0196 0.9300 1.0000
2.000 0.2291 0.02202 0.01075 -0.0197 0.9254 1.0000
2.250 0.2509 0.02239 0.01129 -0.0194 0.9200 1.0000
2.500 0.2801 0.02282 0.01189 -0.0204 0.9157 1.0000
2.750 0.3010 0.02323 0.01248 -0.0199 0.9097 1.0000
3.000 0.3282 0.02369 0.01316 -0.0205 0.9041 1.0000
3.250 0.3544 0.02415 0.01390 -0.0209 0.8980 1.0000
3.500 0.3815 0.02463 0.01481 -0.0213 0.8908 1.0000
3.750 0.4080 0.02510 0.01567 -0.0215 0.8823 1.0000
4.000 0.4890 0.02119 0.00942 -0.0133 0.1530 1.0000
4.250 0.4973 0.02313 0.01074 -0.0107 0.0870 1.0000
4.500 0.5123 0.02452 0.01219 -0.0085 0.0724 1.0000
4.750 0.5298 0.02600 0.01378 -0.0065 0.0638 1.0000
5.000 0.5548 0.02754 0.01571 -0.0053 0.0547 1.0000
5.250 0.5866 0.02935 0.01770 -0.0051 0.0444 1.0000
5.500 0.6210 0.03180 0.02041 -0.0049 0.0409 1.0000
5.750 0.6497 0.03463 0.02352 -0.0043 0.0388 1.0000
6.000 0.6735 0.03829 0.02744 -0.0037 0.0371 1.0000
6.250 0.6943 0.04065 0.03046 -0.0019 0.0343 1.0000
6.500 0.7122 0.04358 0.03396 -0.0003 0.0317 1.0000
6.750 0.7274 0.04696 0.03781 0.0013 0.0312 1.0000
7.000 0.7397 0.05056 0.04185 0.0030 0.0314 1.0000
7.250 0.7489 0.05429 0.04599 0.0046 0.0316 1.0000
7.500 0.7551 0.05821 0.05027 0.0062 0.0320 1.0000
7.750 0.7589 0.06205 0.05443 0.0075 0.0325 1.0000
8.000 0.7597 0.06601 0.05864 0.0087 0.0331 1.0000
8.250 0.7576 0.07004 0.06288 0.0097 0.0336 1.0000
8.500 0.7535 0.07398 0.06697 0.0104 0.0342 1.0000
8.750 0.7468 0.07794 0.07105 0.0109 0.0347 1.0000
9.000 0.7379 0.08177 0.07494 0.0113 0.0352 1.0000
9.250 0.7301 0.08587 0.07906 0.0111 0.0358 1.0000
9.750 0.6104 0.08670 0.08039 0.0119 0.0357 1.0000
10.000 0.6041 0.09184 0.08552 0.0102 0.0362 1.0000
10.250 0.6939 0.10837 0.10163 -0.0039 0.0426 1.0000
10.500 0.6923 0.11382 0.10702 -0.0069 0.0447 1.0000
10.750 0.6963 0.11858 0.11177 -0.0076 0.0481 1.0000
11.000 0.5713 0.11519 0.10883 -0.0038 0.0434 1.0000
11.250 0.5693 0.11971 0.11332 -0.0055 0.0455 1.0000
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Polar data table (+)
Polar graphs
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