EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 329 AIRFOIL (e329-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.77 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e329-il-1000000-n5.txt Download as CSV file: xf-e329-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 329 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2440 0.08830 0.08573 -0.0621 0.7593 0.0075
-9.750 -0.2461 0.08475 0.08205 -0.0631 0.7235 0.0076
-6.750 -0.3656 0.02384 0.01905 -0.0511 0.6002 0.0041
-6.500 -0.3569 0.01954 0.01414 -0.0479 0.5913 0.0040
-6.250 -0.3382 0.01737 0.01159 -0.0463 0.5817 0.0040
-6.000 -0.3159 0.01617 0.01014 -0.0453 0.5718 0.0040
-5.750 -0.2927 0.01515 0.00892 -0.0444 0.5612 0.0040
-5.500 -0.2686 0.01437 0.00797 -0.0436 0.5519 0.0040
-5.250 -0.2445 0.01366 0.00711 -0.0429 0.5428 0.0040
-5.000 -0.2203 0.01299 0.00630 -0.0421 0.5343 0.0040
-4.750 -0.1958 0.01255 0.00575 -0.0415 0.5246 0.0040
-4.500 -0.1712 0.01209 0.00520 -0.0408 0.5163 0.0041
-4.250 -0.1466 0.01174 0.00476 -0.0401 0.5080 0.0041
-4.000 -0.1217 0.01139 0.00435 -0.0395 0.5005 0.0041
-3.750 -0.0970 0.01108 0.00396 -0.0388 0.4930 0.0042
-3.500 -0.0719 0.01080 0.00363 -0.0383 0.4856 0.0042
-3.000 -0.0219 0.01027 0.00298 -0.0371 0.4711 0.0046
-2.750 0.0039 0.01011 0.00277 -0.0366 0.4643 0.0050
-2.500 0.0300 0.00997 0.00260 -0.0362 0.4583 0.0053
-2.250 0.0562 0.00985 0.00244 -0.0359 0.4518 0.0058
-2.000 0.0822 0.00974 0.00230 -0.0355 0.4451 0.0070
-1.750 0.1088 0.00963 0.00217 -0.0352 0.4394 0.0086
-1.500 0.1353 0.00955 0.00207 -0.0349 0.4337 0.0112
-1.250 0.1617 0.00946 0.00199 -0.0346 0.4284 0.0174
-1.000 0.1883 0.00936 0.00191 -0.0344 0.4232 0.0274
-0.750 0.2137 0.00919 0.00186 -0.0340 0.4175 0.0645
-0.500 0.2386 0.00896 0.00180 -0.0335 0.4125 0.1309
-0.250 0.2389 0.00672 0.00155 -0.0291 0.4095 0.7421
0.000 0.2642 0.00674 0.00167 -0.0283 0.4048 0.7981
0.250 0.2910 0.00684 0.00174 -0.0280 0.3995 0.8152
0.500 0.3186 0.00692 0.00179 -0.0278 0.3953 0.8242
0.750 0.3459 0.00700 0.00185 -0.0276 0.3908 0.8321
1.000 0.3729 0.00712 0.00193 -0.0273 0.3863 0.8408
1.250 0.4008 0.00720 0.00195 -0.0274 0.3818 0.8428
1.500 0.4290 0.00725 0.00196 -0.0275 0.3779 0.8438
1.750 0.4570 0.00730 0.00198 -0.0276 0.3740 0.8448
2.000 0.4847 0.00737 0.00201 -0.0276 0.3695 0.8457
2.250 0.5126 0.00743 0.00204 -0.0276 0.3658 0.8467
2.500 0.5406 0.00749 0.00208 -0.0277 0.3621 0.8476
2.750 0.5683 0.00756 0.00213 -0.0278 0.3583 0.8486
3.000 0.5957 0.00765 0.00219 -0.0278 0.3536 0.8498
3.250 0.6234 0.00773 0.00225 -0.0278 0.3503 0.8510
3.500 0.6511 0.00780 0.00231 -0.0279 0.3468 0.8521
3.750 0.6786 0.00789 0.00238 -0.0279 0.3425 0.8531
4.000 0.7058 0.00799 0.00246 -0.0279 0.3383 0.8542
4.250 0.7333 0.00808 0.00254 -0.0280 0.3347 0.8553
4.500 0.7608 0.00816 0.00262 -0.0280 0.3308 0.8564
4.750 0.7879 0.00826 0.00271 -0.0280 0.3267 0.8575
5.000 0.8146 0.00840 0.00281 -0.0280 0.3216 0.8586
5.250 0.8420 0.00848 0.00291 -0.0280 0.3179 0.8595
5.500 0.8689 0.00858 0.00302 -0.0280 0.3134 0.8607
5.750 0.8952 0.00871 0.00314 -0.0279 0.3085 0.8621
6.000 0.9217 0.00882 0.00326 -0.0278 0.3039 0.8635
6.250 0.9481 0.00894 0.00339 -0.0277 0.2987 0.8648
6.500 0.9738 0.00910 0.00354 -0.0275 0.2929 0.8662
6.750 1.0001 0.00922 0.00368 -0.0274 0.2873 0.8676
7.000 1.0256 0.00939 0.00384 -0.0272 0.2804 0.8690
7.250 1.0510 0.00956 0.00400 -0.0270 0.2736 0.8705
7.500 1.0761 0.00974 0.00419 -0.0267 0.2662 0.8720
7.750 1.1010 0.00994 0.00438 -0.0265 0.2586 0.8736
8.000 1.1251 0.01018 0.00459 -0.0260 0.2498 0.8751
8.500 1.1725 0.01064 0.00505 -0.0251 0.2320 0.8784
8.750 1.1949 0.01093 0.00532 -0.0244 0.2220 0.8803
9.000 1.2173 0.01120 0.00559 -0.0237 0.2120 0.8825
9.250 1.2383 0.01154 0.00591 -0.0228 0.2007 0.8850
9.500 1.2584 0.01191 0.00625 -0.0218 0.1885 0.8876
9.750 1.2772 0.01235 0.00664 -0.0206 0.1749 0.8901
10.000 1.2955 0.01277 0.00703 -0.0193 0.1633 0.8926
10.250 1.3115 0.01324 0.00748 -0.0176 0.1502 0.8957
10.500 1.3251 0.01373 0.00793 -0.0155 0.1378 0.8994
10.750 1.3359 0.01424 0.00841 -0.0128 0.1261 0.9039
11.000 1.3470 0.01475 0.00892 -0.0103 0.1166 0.9084
11.250 1.3576 0.01526 0.00944 -0.0078 0.1081 0.9141
11.500 1.3663 0.01586 0.01004 -0.0050 0.0992 0.9212
11.750 1.3741 0.01648 0.01068 -0.0022 0.0920 0.9301
12.000 1.3819 0.01714 0.01138 0.0003 0.0843 0.9431
12.250 1.3951 0.01797 0.01225 0.0014 0.0763 0.9634
12.500 1.4201 0.01904 0.01334 -0.0005 0.0683 0.9948
12.750 1.4238 0.02008 0.01439 0.0019 0.0629 1.0000
13.000 1.4287 0.02132 0.01564 0.0037 0.0573 1.0000
13.250 1.4332 0.02272 0.01706 0.0051 0.0530 1.0000
13.500 1.4367 0.02432 0.01869 0.0063 0.0482 1.0000
13.750 1.4365 0.02636 0.02075 0.0073 0.0432 1.0000
14.000 1.4420 0.02810 0.02255 0.0078 0.0412 1.0000
14.250 1.4430 0.03032 0.02482 0.0082 0.0378 1.0000
14.500 1.4421 0.03285 0.02739 0.0084 0.0349 1.0000
14.750 1.4379 0.03582 0.03040 0.0085 0.0308 1.0000
15.000 1.4359 0.03864 0.03328 0.0084 0.0290 1.0000
15.250 1.4339 0.04152 0.03623 0.0082 0.0272 1.0000
15.500 1.4282 0.04484 0.03960 0.0079 0.0252 1.0000
15.750 1.4206 0.04843 0.04326 0.0074 0.0231 1.0000
16.000 1.4198 0.05135 0.04629 0.0069 0.0235 1.0000
16.250 1.4092 0.05546 0.05044 0.0062 0.0207 1.0000
16.500 1.4004 0.05944 0.05448 0.0054 0.0190 1.0000
16.750 1.3938 0.06326 0.05838 0.0045 0.0178 1.0000
17.000 1.3860 0.06727 0.06246 0.0036 0.0167 1.0000
17.250 1.3765 0.07159 0.06683 0.0024 0.0154 1.0000
17.500 1.3720 0.07533 0.07066 0.0014 0.0152 1.0000
17.750 1.3661 0.07930 0.07471 0.0002 0.0146 1.0000
18.000 1.3569 0.08377 0.07924 -0.0012 0.0133 1.0000
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Polar data table (+)
Polar graphs
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