EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 332 AIRFOIL (e332-il) Reynolds number: 100,000 Max Cl/Cd: 47.14 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e332-il-100000-n5.txt Download as CSV file: xf-e332-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 332 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4252 0.09482 0.09027 -0.0233 1.0000 0.0445
-8.500 -0.4337 0.09112 0.08658 -0.0259 1.0000 0.0446
-8.250 -0.4407 0.08805 0.08351 -0.0264 1.0000 0.0447
-8.000 -0.4470 0.08487 0.08029 -0.0267 1.0000 0.0448
-7.750 -0.4505 0.08164 0.07700 -0.0266 1.0000 0.0448
-7.500 -0.4489 0.07693 0.07232 -0.0263 1.0000 0.0451
-7.250 -0.4441 0.07272 0.06816 -0.0258 1.0000 0.0455
-7.000 -0.4402 0.06907 0.06453 -0.0249 1.0000 0.0459
-6.750 -0.4363 0.06586 0.06131 -0.0239 1.0000 0.0462
-6.500 -0.4336 0.06266 0.05805 -0.0225 1.0000 0.0463
-6.250 -0.4248 0.05925 0.05441 -0.0223 0.9863 0.0458
-6.000 -0.4018 0.04957 0.04414 -0.0224 0.9431 0.0198
-5.750 -0.3743 0.04577 0.04015 -0.0249 0.9051 0.0193
-5.500 -0.3493 0.04228 0.03629 -0.0259 0.8712 0.0189
-5.000 -0.3112 0.03640 0.02957 -0.0235 0.8140 0.0182
-4.750 -0.2927 0.03391 0.02663 -0.0217 0.7912 0.0178
-4.500 -0.2731 0.03151 0.02377 -0.0198 0.7705 0.0175
-4.250 -0.2516 0.02936 0.02109 -0.0180 0.7519 0.0186
-4.000 -0.2282 0.02748 0.01869 -0.0165 0.7346 0.0191
-3.750 -0.2043 0.02576 0.01659 -0.0153 0.7181 0.0206
-3.500 -0.1793 0.02446 0.01504 -0.0144 0.7020 0.0215
-3.250 -0.1521 0.02296 0.01324 -0.0136 0.6872 0.0225
-3.000 -0.1245 0.02173 0.01176 -0.0130 0.6733 0.0233
-2.750 -0.0975 0.02062 0.01043 -0.0123 0.6593 0.0246
-2.500 -0.0722 0.01965 0.00934 -0.0114 0.6461 0.0270
-2.250 -0.0483 0.01900 0.00864 -0.0105 0.6335 0.0316
-2.000 -0.0253 0.01827 0.00777 -0.0092 0.6219 0.0362
-1.750 -0.0019 0.01770 0.00710 -0.0080 0.6111 0.0473
-1.500 0.0670 0.01478 0.00738 -0.0140 0.5977 0.8604
-1.250 0.2237 0.01583 0.00758 -0.0363 0.5768 0.9929
-1.000 0.2642 0.01560 0.00705 -0.0391 0.5659 1.0000
-0.750 0.2872 0.01559 0.00685 -0.0384 0.5554 1.0000
-0.500 0.3103 0.01561 0.00669 -0.0376 0.5464 1.0000
-0.250 0.3333 0.01564 0.00654 -0.0369 0.5376 1.0000
0.000 0.3567 0.01567 0.00644 -0.0362 0.5288 1.0000
0.250 0.3799 0.01573 0.00633 -0.0354 0.5211 1.0000
0.500 0.4034 0.01580 0.00630 -0.0348 0.5126 1.0000
0.750 0.4267 0.01588 0.00623 -0.0340 0.5057 1.0000
1.000 0.4503 0.01596 0.00626 -0.0334 0.4974 1.0000
1.250 0.4736 0.01607 0.00624 -0.0327 0.4910 1.0000
1.500 0.4972 0.01618 0.00631 -0.0320 0.4832 1.0000
1.750 0.5207 0.01630 0.00633 -0.0313 0.4769 1.0000
2.000 0.5442 0.01643 0.00644 -0.0307 0.4699 1.0000
2.250 0.5676 0.01657 0.00651 -0.0300 0.4633 1.0000
2.500 0.5911 0.01673 0.00664 -0.0293 0.4572 1.0000
2.750 0.6144 0.01688 0.00678 -0.0286 0.4505 1.0000
3.000 0.6378 0.01705 0.00687 -0.0279 0.4453 1.0000
3.250 0.6610 0.01724 0.00711 -0.0272 0.4384 1.0000
3.500 0.6841 0.01742 0.00728 -0.0265 0.4327 1.0000
3.750 0.7071 0.01764 0.00750 -0.0257 0.4269 1.0000
4.000 0.7299 0.01786 0.00775 -0.0250 0.4207 1.0000
4.250 0.7529 0.01807 0.00791 -0.0242 0.4159 1.0000
4.500 0.7752 0.01833 0.00830 -0.0234 0.4093 1.0000
4.750 0.7977 0.01857 0.00855 -0.0225 0.4038 1.0000
5.000 0.8199 0.01884 0.00885 -0.0217 0.3984 1.0000
5.250 0.8417 0.01912 0.00922 -0.0208 0.3921 1.0000
5.500 0.8639 0.01937 0.00948 -0.0199 0.3871 1.0000
5.750 0.8850 0.01969 0.00993 -0.0189 0.3808 1.0000
6.000 0.9064 0.01997 0.01028 -0.0179 0.3749 1.0000
6.250 0.9277 0.02027 0.01063 -0.0168 0.3696 1.0000
6.500 0.9479 0.02061 0.01112 -0.0157 0.3629 1.0000
6.750 0.9690 0.02088 0.01141 -0.0146 0.3575 1.0000
7.000 0.9882 0.02127 0.01196 -0.0134 0.3505 1.0000
7.250 1.0082 0.02156 0.01234 -0.0121 0.3443 1.0000
7.500 1.0270 0.02192 0.01284 -0.0108 0.3376 1.0000
7.750 1.0458 0.02224 0.01326 -0.0094 0.3307 1.0000
8.000 1.0638 0.02260 0.01375 -0.0079 0.3238 1.0000
8.250 1.0813 0.02294 0.01423 -0.0063 0.3164 1.0000
8.500 1.0980 0.02332 0.01474 -0.0046 0.3088 1.0000
8.750 1.1144 0.02365 0.01517 -0.0028 0.3010 1.0000
9.000 1.1290 0.02408 0.01577 -0.0009 0.2925 1.0000
9.250 1.1446 0.02438 0.01614 0.0010 0.2848 1.0000
9.500 1.1566 0.02489 0.01685 0.0033 0.2749 1.0000
9.750 1.1688 0.02535 0.01743 0.0056 0.2659 1.0000
10.000 1.1804 0.02576 0.01791 0.0079 0.2568 1.0000
10.250 1.1892 0.02636 0.01868 0.0105 0.2460 1.0000
10.500 1.1969 0.02698 0.01941 0.0132 0.2356 1.0000
10.750 1.2029 0.02764 0.02015 0.0161 0.2253 1.0000
11.000 1.2066 0.02839 0.02097 0.0191 0.2152 1.0000
11.250 1.2066 0.02932 0.02200 0.0224 0.2045 1.0000
11.500 1.2039 0.03038 0.02315 0.0258 0.1950 1.0000
11.750 1.1998 0.03173 0.02454 0.0286 0.1854 1.0000
12.000 1.1947 0.03345 0.02631 0.0307 0.1761 1.0000
12.250 1.1893 0.03559 0.02854 0.0319 0.1666 1.0000
12.500 1.1827 0.03811 0.03112 0.0326 0.1580 1.0000
12.750 1.1745 0.04103 0.03406 0.0328 0.1500 1.0000
13.000 1.1666 0.04422 0.03737 0.0326 0.1418 1.0000
13.250 1.1569 0.04772 0.04088 0.0321 0.1349 1.0000
13.500 1.1477 0.05141 0.04467 0.0314 0.1277 1.0000
13.750 1.1376 0.05524 0.04854 0.0306 0.1214 1.0000
14.000 1.1277 0.05925 0.05263 0.0295 0.1150 1.0000
14.250 1.1177 0.06326 0.05665 0.0285 0.1095 1.0000
14.500 1.1078 0.06749 0.06099 0.0272 0.1034 1.0000
14.750 1.0987 0.07159 0.06509 0.0260 0.0984 1.0000
15.000 1.0906 0.07592 0.06957 0.0245 0.0927 1.0000
15.250 1.0828 0.08014 0.07378 0.0230 0.0881 1.0000
15.500 1.0758 0.08448 0.07823 0.0215 0.0831 1.0000
15.750 1.0686 0.08893 0.08275 0.0198 0.0785 1.0000
16.000 1.0632 0.09306 0.08687 0.0182 0.0744 1.0000
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Polar data table (+)
Polar graphs
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