EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 100,000 Max Cl/Cd: 46.65 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e328-il-100000-n5.txt Download as CSV file: xf-e328-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 328 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4157 0.09485 0.09009 -0.0403 1.0000 0.0465
-9.250 -0.4213 0.09112 0.08637 -0.0414 1.0000 0.0464
-9.000 -0.4315 0.08770 0.08295 -0.0416 1.0000 0.0464
-8.750 -0.4513 0.08498 0.08022 -0.0400 1.0000 0.0465
-8.250 -0.4416 0.07330 0.06859 -0.0387 1.0000 0.0302
-8.000 -0.4513 0.07043 0.06571 -0.0366 1.0000 0.0301
-7.750 -0.4545 0.06784 0.06315 -0.0346 1.0000 0.0295
-7.250 -0.4781 0.06011 0.05517 -0.0284 1.0000 0.0244
-7.000 -0.4772 0.05583 0.05058 -0.0271 0.9910 0.0247
-6.750 -0.4573 0.05214 0.04675 -0.0288 0.9675 0.0243
-6.500 -0.4361 0.04834 0.04273 -0.0302 0.9419 0.0237
-6.250 -0.4110 0.04423 0.03825 -0.0317 0.9186 0.0231
-6.000 -0.3847 0.04014 0.03370 -0.0327 0.8954 0.0224
-5.750 -0.3571 0.03644 0.02946 -0.0333 0.8721 0.0219
-5.500 -0.3304 0.03320 0.02564 -0.0331 0.8488 0.0216
-5.250 -0.3042 0.03064 0.02256 -0.0326 0.8254 0.0215
-5.000 -0.2778 0.02850 0.01994 -0.0319 0.8039 0.0216
-4.750 -0.2516 0.02664 0.01768 -0.0311 0.7832 0.0220
-4.500 -0.2242 0.02501 0.01569 -0.0304 0.7640 0.0225
-4.250 -0.1961 0.02363 0.01400 -0.0299 0.7458 0.0234
-4.000 -0.1683 0.02249 0.01263 -0.0294 0.7290 0.0254
-3.750 -0.1423 0.02168 0.01173 -0.0290 0.7128 0.0281
-3.500 -0.1161 0.02076 0.01061 -0.0282 0.6977 0.0303
-3.250 -0.0932 0.01991 0.00973 -0.0272 0.6835 0.0329
-3.000 -0.0702 0.01933 0.00902 -0.0260 0.6702 0.0382
-2.750 -0.0482 0.01873 0.00833 -0.0247 0.6578 0.0466
-2.500 -0.0264 0.01813 0.00774 -0.0234 0.6452 0.0621
-2.250 -0.0047 0.01743 0.00722 -0.0221 0.6336 0.1084
-2.000 0.0095 0.01576 0.00842 -0.0171 0.6242 0.7894
-1.750 0.0284 0.01678 0.00923 -0.0129 0.6132 0.8539
-1.500 0.1426 0.01873 0.01062 -0.0250 0.5969 0.9151
-1.250 0.1870 0.01879 0.01041 -0.0280 0.5851 0.9252
-1.000 0.2121 0.01874 0.01014 -0.0276 0.5758 0.9297
-0.750 0.2352 0.01869 0.00993 -0.0269 0.5661 0.9339
-0.500 0.2664 0.01861 0.00966 -0.0277 0.5568 0.9365
-0.250 0.2952 0.01855 0.00944 -0.0281 0.5481 0.9394
0.000 0.3213 0.01853 0.00929 -0.0280 0.5394 0.9426
0.250 0.3437 0.01854 0.00915 -0.0272 0.5319 0.9462
0.500 0.3702 0.01852 0.00904 -0.0272 0.5237 0.9488
0.750 0.3996 0.01850 0.00888 -0.0278 0.5162 0.9509
1.000 0.4274 0.01850 0.00881 -0.0281 0.5085 0.9532
1.250 0.4535 0.01852 0.00874 -0.0280 0.5016 0.9557
1.500 0.4781 0.01857 0.00872 -0.0276 0.4951 0.9584
1.750 0.4999 0.01865 0.00875 -0.0267 0.4883 0.9610
2.000 0.5286 0.01868 0.00867 -0.0272 0.4825 0.9627
2.250 0.5567 0.01873 0.00874 -0.0276 0.4752 0.9646
2.500 0.5834 0.01880 0.00875 -0.0277 0.4694 0.9664
2.750 0.6096 0.01890 0.00883 -0.0277 0.4634 0.9686
3.000 0.6344 0.01901 0.00894 -0.0275 0.4571 0.9709
3.250 0.6580 0.01913 0.00901 -0.0269 0.4522 0.9729
3.500 0.6832 0.01927 0.00920 -0.0268 0.4459 0.9747
3.750 0.7112 0.01939 0.00931 -0.0273 0.4400 0.9765
4.000 0.7384 0.01952 0.00939 -0.0275 0.4352 0.9783
4.250 0.7632 0.01971 0.00967 -0.0274 0.4289 0.9801
4.500 0.7879 0.01987 0.00987 -0.0271 0.4236 0.9819
4.750 0.8126 0.02007 0.01006 -0.0269 0.4187 0.9840
5.000 0.8384 0.02029 0.01041 -0.0270 0.4126 0.9861
5.250 0.8655 0.02046 0.01059 -0.0272 0.4073 0.9878
5.500 0.8910 0.02068 0.01087 -0.0272 0.4020 0.9896
5.750 0.9154 0.02094 0.01126 -0.0271 0.3960 0.9916
6.000 0.9406 0.02115 0.01148 -0.0270 0.3910 0.9934
6.250 0.9659 0.02144 0.01189 -0.0271 0.3851 0.9956
6.500 0.9920 0.02170 0.01226 -0.0273 0.3790 0.9979
6.750 1.0188 0.02192 0.01248 -0.0275 0.3741 0.9999
7.000 1.0339 0.02231 0.01307 -0.0256 0.3678 1.0000
7.250 1.0506 0.02259 0.01342 -0.0239 0.3623 1.0000
7.500 1.0673 0.02288 0.01377 -0.0222 0.3573 1.0000
7.750 1.0801 0.02327 0.01434 -0.0200 0.3509 1.0000
8.000 1.0956 0.02351 0.01462 -0.0180 0.3453 1.0000
8.250 1.1073 0.02389 0.01514 -0.0155 0.3393 1.0000
8.500 1.1187 0.02421 0.01560 -0.0129 0.3330 1.0000
8.750 1.1317 0.02446 0.01588 -0.0106 0.3277 1.0000
9.000 1.1376 0.02489 0.01650 -0.0072 0.3207 1.0000
9.250 1.1479 0.02512 0.01677 -0.0043 0.3149 1.0000
9.500 1.1523 0.02554 0.01735 -0.0007 0.3082 1.0000
9.750 1.1595 0.02584 0.01774 0.0025 0.3016 1.0000
10.000 1.1663 0.02624 0.01825 0.0056 0.2947 1.0000
10.250 1.1749 0.02664 0.01875 0.0083 0.2871 1.0000
10.500 1.1832 0.02715 0.01937 0.0108 0.2791 1.0000
10.750 1.1927 0.02761 0.01989 0.0131 0.2712 1.0000
11.000 1.1969 0.02831 0.02076 0.0160 0.2626 1.0000
11.250 1.2030 0.02889 0.02137 0.0186 0.2549 1.0000
11.500 1.2048 0.02985 0.02248 0.0212 0.2457 1.0000
11.750 1.2073 0.03088 0.02360 0.0234 0.2369 1.0000
12.000 1.2088 0.03207 0.02483 0.0253 0.2282 1.0000
12.250 1.2070 0.03374 0.02663 0.0269 0.2188 1.0000
12.500 1.2049 0.03557 0.02853 0.0281 0.2099 1.0000
12.750 1.2013 0.03772 0.03075 0.0289 0.2011 1.0000
13.000 1.1953 0.04036 0.03351 0.0292 0.1921 1.0000
13.250 1.1892 0.04316 0.03635 0.0293 0.1837 1.0000
13.500 1.1813 0.04636 0.03962 0.0291 0.1754 1.0000
13.750 1.1722 0.04987 0.04321 0.0285 0.1671 1.0000
14.000 1.1640 0.05333 0.04667 0.0279 0.1597 1.0000
14.250 1.1533 0.05736 0.05082 0.0269 0.1519 1.0000
14.500 1.1452 0.06101 0.05446 0.0261 0.1452 1.0000
14.750 1.1343 0.06536 0.05892 0.0248 0.1379 1.0000
15.000 1.1268 0.06922 0.06278 0.0237 0.1315 1.0000
15.250 1.1174 0.07362 0.06729 0.0221 0.1248 1.0000
15.500 1.1115 0.07751 0.07117 0.0209 0.1188 1.0000
15.750 1.1030 0.08203 0.07580 0.0192 0.1127 1.0000
16.000 1.0985 0.08584 0.07958 0.0178 0.1070 1.0000
16.250 1.0901 0.09061 0.08450 0.0159 0.1014 1.0000
16.500 1.0865 0.09441 0.08828 0.0144 0.0962 1.0000
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