EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 100,000 Max Cl/Cd: 32.09 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e428-il-100000.txt Download as CSV file: xf-e428-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 428 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8444 0.08438 0.07897 -0.0164 1.0000 0.0566
-12.500 -0.8836 0.07317 0.06765 -0.0249 1.0000 0.0557
-12.250 -0.9164 0.06441 0.05870 -0.0318 1.0000 0.0549
-12.000 -0.9463 0.05751 0.05156 -0.0369 1.0000 0.0545
-11.750 -0.9694 0.05261 0.04642 -0.0390 1.0000 0.0544
-11.500 -0.9868 0.04893 0.04248 -0.0385 1.0000 0.0546
-11.250 -0.9962 0.04541 0.03862 -0.0376 1.0000 0.0554
-11.000 -0.9994 0.04207 0.03483 -0.0365 1.0000 0.0565
-10.750 -0.9879 0.03947 0.03225 -0.0357 1.0000 0.0587
-10.500 -0.9762 0.03740 0.03010 -0.0347 1.0000 0.0619
-10.250 -0.9674 0.03472 0.02707 -0.0336 1.0000 0.0662
-10.000 -0.9528 0.03318 0.02559 -0.0326 1.0000 0.0732
-9.750 -0.9398 0.03151 0.02383 -0.0315 1.0000 0.0844
-9.500 -0.9242 0.03058 0.02301 -0.0304 1.0000 0.0996
-9.250 -0.9057 0.03000 0.02236 -0.0295 1.0000 0.1124
-9.000 -0.8868 0.02930 0.02140 -0.0286 1.0000 0.1231
-8.750 -0.8643 0.02943 0.02157 -0.0279 1.0000 0.1333
-8.500 -0.8406 0.02975 0.02204 -0.0272 1.0000 0.1432
-8.250 -0.8186 0.02947 0.02168 -0.0265 1.0000 0.1530
-8.000 -0.7974 0.02904 0.02098 -0.0257 1.0000 0.1631
-7.750 -0.7721 0.02889 0.02107 -0.0250 1.0000 0.1709
-7.500 -0.7513 0.02760 0.01947 -0.0243 1.0000 0.1798
-7.250 -0.7268 0.02699 0.01893 -0.0236 1.0000 0.1872
-7.000 -0.7047 0.02572 0.01741 -0.0228 1.0000 0.1961
-6.750 -0.6806 0.02504 0.01671 -0.0221 1.0000 0.2049
-6.500 -0.6573 0.02417 0.01575 -0.0214 1.0000 0.2144
-6.250 -0.6340 0.02348 0.01482 -0.0206 1.0000 0.2254
-6.000 -0.6097 0.02277 0.01423 -0.0199 1.0000 0.2339
-5.750 -0.5861 0.02199 0.01326 -0.0191 1.0000 0.2444
-5.500 -0.5620 0.02144 0.01274 -0.0184 1.0000 0.2543
-5.250 -0.5382 0.02074 0.01200 -0.0176 1.0000 0.2643
-5.000 -0.5147 0.02026 0.01134 -0.0168 1.0000 0.2764
-4.750 -0.4910 0.01970 0.01094 -0.0160 1.0000 0.2873
-4.500 -0.4675 0.01911 0.01036 -0.0151 1.0000 0.2987
-4.250 -0.4439 0.01859 0.00971 -0.0143 1.0000 0.3104
-4.000 -0.4204 0.01800 0.00926 -0.0134 1.0000 0.3205
-3.750 -0.3970 0.01744 0.00871 -0.0126 1.0000 0.3313
-3.500 -0.3739 0.01699 0.00821 -0.0118 1.0000 0.3427
-3.250 -0.3515 0.01650 0.00787 -0.0108 1.0000 0.3537
-3.000 -0.3297 0.01609 0.00752 -0.0098 1.0000 0.3660
-2.750 -0.3086 0.01576 0.00721 -0.0087 1.0000 0.3791
-2.500 -0.2886 0.01546 0.00701 -0.0076 1.0000 0.3925
-2.250 -0.2699 0.01521 0.00689 -0.0063 1.0000 0.4066
-2.000 -0.2521 0.01504 0.00685 -0.0051 1.0000 0.4227
-1.750 -0.2348 0.01495 0.00688 -0.0039 1.0000 0.4412
-1.500 -0.2038 0.01487 0.00700 -0.0054 0.9943 0.4671
-1.250 -0.1431 0.01457 0.00701 -0.0118 0.9739 0.5145
-1.000 -0.0824 0.01408 0.00697 -0.0174 0.9535 0.5796
-0.750 -0.0338 0.01363 0.00692 -0.0203 0.9325 0.6542
-0.500 0.0077 0.01330 0.00689 -0.0214 0.9116 0.7231
-0.250 0.0448 0.01304 0.00683 -0.0212 0.8898 0.7815
0.000 0.0739 0.01288 0.00679 -0.0195 0.8631 0.8321
0.250 0.1062 0.01276 0.00670 -0.0183 0.8375 0.8796
0.500 0.1454 0.01271 0.00661 -0.0187 0.8069 0.9230
0.750 0.1975 0.01269 0.00647 -0.0219 0.7726 0.9574
1.000 0.2557 0.01266 0.00626 -0.0268 0.7328 0.9857
1.250 0.2903 0.01263 0.00605 -0.0281 0.6932 1.0000
1.500 0.3054 0.01269 0.00592 -0.0258 0.6576 1.0000
1.750 0.3227 0.01282 0.00583 -0.0236 0.6175 1.0000
2.000 0.3415 0.01303 0.00577 -0.0216 0.5704 1.0000
2.250 0.3611 0.01334 0.00576 -0.0197 0.5166 1.0000
2.500 0.3817 0.01379 0.00583 -0.0181 0.4636 1.0000
2.750 0.4037 0.01432 0.00602 -0.0168 0.4207 1.0000
3.000 0.4270 0.01486 0.00627 -0.0158 0.3901 1.0000
3.250 0.4513 0.01538 0.00662 -0.0151 0.3661 1.0000
3.500 0.4760 0.01592 0.00697 -0.0144 0.3473 1.0000
3.750 0.5012 0.01647 0.00739 -0.0138 0.3316 1.0000
4.000 0.5269 0.01706 0.00790 -0.0132 0.3187 1.0000
4.250 0.5527 0.01771 0.00842 -0.0127 0.3077 1.0000
4.500 0.5785 0.01832 0.00896 -0.0123 0.2968 1.0000
4.750 0.6045 0.01900 0.00968 -0.0118 0.2873 1.0000
5.000 0.6307 0.01975 0.01030 -0.0114 0.2790 1.0000
5.250 0.6564 0.02048 0.01114 -0.0110 0.2702 1.0000
5.500 0.6825 0.02127 0.01183 -0.0106 0.2624 1.0000
5.750 0.7075 0.02207 0.01280 -0.0101 0.2541 1.0000
6.000 0.7332 0.02285 0.01346 -0.0097 0.2455 1.0000
6.250 0.7573 0.02363 0.01445 -0.0090 0.2364 1.0000
6.500 0.7829 0.02448 0.01515 -0.0087 0.2283 1.0000
6.750 0.8062 0.02532 0.01628 -0.0080 0.2198 1.0000
7.000 0.8314 0.02618 0.01706 -0.0075 0.2124 1.0000
7.250 0.8538 0.02731 0.01848 -0.0068 0.2046 1.0000
7.500 0.8782 0.02819 0.01938 -0.0063 0.1974 1.0000
7.750 0.8997 0.02957 0.02100 -0.0055 0.1902 1.0000
8.000 0.9229 0.03051 0.02202 -0.0048 0.1827 1.0000
8.250 0.9443 0.03197 0.02360 -0.0042 0.1763 1.0000
8.500 0.9637 0.03351 0.02545 -0.0032 0.1696 1.0000
8.750 0.9877 0.03465 0.02654 -0.0028 0.1647 1.0000
9.000 1.0011 0.03718 0.02953 -0.0016 0.1595 1.0000
9.250 1.0181 0.03887 0.03147 -0.0007 0.1539 1.0000
9.500 1.0460 0.03935 0.03168 -0.0005 0.1487 1.0000
9.750 1.0485 0.04251 0.03552 0.0012 0.1438 1.0000
10.000 1.0739 0.04227 0.03519 0.0018 0.1371 1.0000
10.250 1.0869 0.04373 0.03682 0.0028 0.1313 1.0000
10.500 1.1042 0.04423 0.03744 0.0039 0.1248 1.0000
10.750 1.1266 0.04456 0.03768 0.0045 0.1195 1.0000
11.000 1.1195 0.04808 0.04174 0.0063 0.1154 1.0000
11.250 1.1643 0.04563 0.03874 0.0063 0.1081 1.0000
11.500 1.1426 0.05003 0.04385 0.0087 0.1047 1.0000
11.750 0.9181 0.08186 0.07659 -0.0040 0.1226 1.0000
12.000 0.8924 0.09152 0.08625 -0.0096 0.1214 1.0000
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Polar data table (+)
Polar graphs
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