Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 200,000 Max Cl/Cd: 45.73 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-200000-n5.txt Download as CSV file: xf-supermarine371ii-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5386 0.08579 0.08248 -0.0222 1.0000 0.0090
-8.500 -0.5417 0.08106 0.07780 -0.0258 1.0000 0.0087
-8.250 -0.5480 0.07632 0.07309 -0.0300 1.0000 0.0085
-8.000 -0.5556 0.07223 0.06899 -0.0320 1.0000 0.0084
-7.750 -0.5578 0.06796 0.06468 -0.0338 1.0000 0.0082
-7.500 -0.5581 0.06356 0.06020 -0.0350 1.0000 0.0080
-7.250 -0.5557 0.05946 0.05601 -0.0355 1.0000 0.0078
-6.750 -0.5251 0.04897 0.04503 -0.0404 0.9598 0.0075
-6.500 -0.5063 0.04412 0.03985 -0.0416 0.9462 0.0076
-6.250 -0.4866 0.04005 0.03543 -0.0416 0.9344 0.0089
-6.000 -0.4657 0.03659 0.03159 -0.0408 0.9243 0.0101
-5.750 -0.4479 0.03296 0.02747 -0.0396 0.9152 0.0101
-5.500 -0.4293 0.02954 0.02362 -0.0382 0.9068 0.0101
-5.250 -0.4084 0.02643 0.02003 -0.0369 0.9005 0.0102
-5.000 -0.3860 0.02373 0.01688 -0.0357 0.8938 0.0103
-4.750 -0.3620 0.02153 0.01425 -0.0347 0.8887 0.0107
-4.500 -0.3369 0.01969 0.01207 -0.0338 0.8833 0.0113
-4.250 -0.3134 0.01728 0.00941 -0.0330 0.8785 0.0134
-3.750 -0.2640 0.01538 0.00725 -0.0317 0.8693 0.0194
-3.500 -0.2394 0.01473 0.00646 -0.0311 0.8647 0.0213
-3.250 -0.2176 0.01368 0.00534 -0.0302 0.8610 0.0264
-3.000 -0.1932 0.01309 0.00456 -0.0296 0.8565 0.0288
-2.750 -0.1680 0.01266 0.00396 -0.0292 0.8526 0.0338
-2.500 -0.1437 0.01212 0.00349 -0.0286 0.8493 0.0647
-2.250 -0.1255 0.01078 0.00309 -0.0278 0.8459 0.3081
-2.000 -0.1198 0.00932 0.00344 -0.0229 0.8416 0.7556
-1.750 -0.1000 0.00948 0.00366 -0.0203 0.8383 0.8227
-1.500 -0.0769 0.00956 0.00365 -0.0188 0.8355 0.8471
-1.250 -0.0521 0.00960 0.00363 -0.0178 0.8326 0.8613
-1.000 -0.0248 0.00960 0.00356 -0.0178 0.8295 0.8665
-0.750 0.0026 0.00959 0.00347 -0.0179 0.8266 0.8713
-0.500 0.0301 0.00958 0.00339 -0.0181 0.8242 0.8756
-0.250 0.0578 0.00958 0.00335 -0.0181 0.8220 0.8799
0.000 0.0851 0.00959 0.00332 -0.0182 0.8197 0.8853
0.250 0.1127 0.00961 0.00335 -0.0184 0.8165 0.8898
0.500 0.1404 0.00964 0.00340 -0.0186 0.8139 0.8946
0.750 0.1677 0.00968 0.00345 -0.0187 0.8115 0.9004
1.000 0.1961 0.00971 0.00351 -0.0189 0.8093 0.9050
1.250 0.2241 0.00975 0.00358 -0.0191 0.8073 0.9109
1.500 0.2524 0.00981 0.00373 -0.0195 0.8047 0.9164
1.750 0.2813 0.00988 0.00393 -0.0200 0.8018 0.9218
2.000 0.3098 0.00995 0.00410 -0.0203 0.7991 0.9281
2.250 0.3403 0.00999 0.00426 -0.0210 0.7959 0.9330
2.500 0.3677 0.00988 0.00424 -0.0207 0.7836 0.9398
2.750 0.3931 0.00936 0.00363 -0.0188 0.7348 0.9457
3.000 0.4184 0.00915 0.00334 -0.0176 0.6530 0.9536
3.250 0.4255 0.01167 0.00368 -0.0149 0.1721 0.9657
3.500 0.4520 0.01288 0.00436 -0.0157 0.0474 0.9741
3.750 0.4825 0.01357 0.00512 -0.0166 0.0344 0.9823
4.000 0.5124 0.01438 0.00603 -0.0177 0.0250 0.9916
4.250 0.5395 0.01523 0.00701 -0.0180 0.0207 1.0000
4.500 0.5568 0.01586 0.00763 -0.0164 0.0157 1.0000
4.750 0.5725 0.01740 0.00932 -0.0143 0.0137 1.0000
5.000 0.5936 0.01874 0.01078 -0.0129 0.0127 1.0000
5.250 0.6169 0.02049 0.01271 -0.0117 0.0119 1.0000
5.500 0.6407 0.02172 0.01414 -0.0109 0.0094 1.0000
5.750 0.6638 0.02324 0.01588 -0.0101 0.0080 1.0000
6.000 0.6862 0.02544 0.01840 -0.0090 0.0075 1.0000
6.250 0.7067 0.02806 0.02138 -0.0077 0.0072 1.0000
6.500 0.7251 0.03121 0.02495 -0.0060 0.0071 1.0000
6.750 0.7412 0.03487 0.02905 -0.0040 0.0073 1.0000
7.000 0.7546 0.03906 0.03367 -0.0018 0.0076 1.0000
7.250 0.7645 0.04379 0.03883 0.0007 0.0079 1.0000
7.500 0.7713 0.04857 0.04398 0.0029 0.0083 1.0000
7.750 0.7755 0.05322 0.04893 0.0049 0.0088 1.0000
8.000 0.7764 0.05777 0.05373 0.0065 0.0092 1.0000
8.250 0.7738 0.06224 0.05840 0.0080 0.0096 1.0000
8.500 0.7682 0.06643 0.06275 0.0090 0.0100 1.0000
8.750 0.7576 0.07033 0.06677 0.0102 0.0102 1.0000
9.000 0.7432 0.07421 0.07073 0.0107 0.0104 1.0000
9.250 0.7290 0.07869 0.07526 0.0094 0.0105 1.0000
9.500 0.7162 0.08400 0.08062 0.0063 0.0106 1.0000
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Polar data table (+)
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