EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 100,000 Max Cl/Cd: 39.18 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e325-il-100000.txt Download as CSV file: xf-e325-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 325 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5843 0.09720 0.09269 -0.0092 1.0000 0.1034
-9.500 -0.6182 0.09331 0.08876 -0.0116 1.0000 0.1039
-9.250 -0.6510 0.09095 0.08634 -0.0100 1.0000 0.1042
-9.000 -0.5903 0.08422 0.07980 -0.0102 1.0000 0.1108
-8.750 -0.6063 0.08056 0.07614 -0.0101 1.0000 0.1137
-8.500 -0.6307 0.07774 0.07327 -0.0082 1.0000 0.1160
-8.250 -0.6750 0.07728 0.07250 -0.0038 1.0000 0.1188
-8.000 -0.6608 0.07106 0.06643 -0.0038 1.0000 0.1223
-7.750 -0.6520 0.06782 0.06322 -0.0024 1.0000 0.1278
-7.250 -0.6587 0.06168 0.05692 0.0022 1.0000 0.1410
-7.000 -0.6703 0.05975 0.05471 0.0059 1.0000 0.1519
-6.750 -0.6548 0.05619 0.05127 0.0071 1.0000 0.1596
-6.500 -0.6522 0.05334 0.04835 0.0097 1.0000 0.1723
-6.250 -0.6483 0.05078 0.04575 0.0124 1.0000 0.1874
-6.000 -0.6430 0.04828 0.04324 0.0153 1.0000 0.2047
-5.750 -0.6156 0.03864 0.03140 0.0217 1.0000 0.0673
-5.500 -0.6258 0.04402 0.03726 0.0245 1.0000 0.1345
-5.250 -0.5801 0.03249 0.02436 0.0276 1.0000 0.0515
-5.000 -0.5670 0.03041 0.02210 0.0303 1.0000 0.0499
-4.500 -0.4958 0.02643 0.01754 0.0271 0.9821 0.0522
-4.250 -0.4305 0.02342 0.01441 0.0209 0.9678 0.0558
-4.000 -0.3687 0.02112 0.01220 0.0149 0.9474 0.0666
-3.750 -0.3185 0.01918 0.01041 0.0109 0.9204 0.0909
-3.500 -0.1367 0.02376 0.01813 0.0012 0.9432 0.9233
-3.250 0.0617 0.02161 0.01508 -0.0298 0.8680 1.0000
-3.000 0.0869 0.02139 0.01445 -0.0298 0.8167 1.0000
-2.750 0.1075 0.02118 0.01395 -0.0290 0.7840 1.0000
-2.500 0.1279 0.02097 0.01352 -0.0282 0.7567 1.0000
-2.250 0.1470 0.02081 0.01313 -0.0270 0.7347 1.0000
-2.000 0.1665 0.02066 0.01280 -0.0260 0.7139 1.0000
-1.750 0.1866 0.02053 0.01250 -0.0251 0.6957 1.0000
-1.500 0.2073 0.02042 0.01223 -0.0243 0.6787 1.0000
-1.250 0.2282 0.02033 0.01198 -0.0235 0.6632 1.0000
-1.000 0.2491 0.02027 0.01178 -0.0227 0.6487 1.0000
-0.750 0.2701 0.02022 0.01161 -0.0219 0.6354 1.0000
-0.500 0.2910 0.02020 0.01144 -0.0210 0.6231 1.0000
-0.250 0.3125 0.02018 0.01134 -0.0203 0.6104 1.0000
0.000 0.3342 0.02019 0.01129 -0.0196 0.5984 1.0000
0.250 0.3559 0.02023 0.01124 -0.0188 0.5877 1.0000
0.500 0.3775 0.02026 0.01118 -0.0181 0.5774 1.0000
0.750 0.3997 0.02034 0.01124 -0.0175 0.5664 1.0000
1.000 0.4216 0.02043 0.01125 -0.0167 0.5575 1.0000
1.250 0.4437 0.02051 0.01132 -0.0161 0.5474 1.0000
1.500 0.4659 0.02065 0.01146 -0.0154 0.5383 1.0000
1.750 0.4880 0.02077 0.01151 -0.0147 0.5298 1.0000
2.000 0.5103 0.02096 0.01174 -0.0141 0.5205 1.0000
2.250 0.5325 0.02109 0.01180 -0.0133 0.5130 1.0000
2.500 0.5548 0.02133 0.01215 -0.0128 0.5038 1.0000
2.750 0.5770 0.02149 0.01223 -0.0120 0.4968 1.0000
3.000 0.5992 0.02178 0.01263 -0.0114 0.4876 1.0000
3.250 0.6214 0.02195 0.01273 -0.0106 0.4808 1.0000
3.500 0.6434 0.02230 0.01325 -0.0101 0.4720 1.0000
3.750 0.6657 0.02249 0.01338 -0.0092 0.4653 1.0000
4.000 0.6873 0.02290 0.01395 -0.0086 0.4565 1.0000
4.250 0.7095 0.02310 0.01413 -0.0077 0.4499 1.0000
4.500 0.7308 0.02355 0.01475 -0.0071 0.4413 1.0000
4.750 0.7529 0.02375 0.01494 -0.0062 0.4345 1.0000
5.000 0.7738 0.02424 0.01561 -0.0055 0.4259 1.0000
5.250 0.7958 0.02442 0.01578 -0.0045 0.4189 1.0000
5.500 0.8161 0.02495 0.01650 -0.0037 0.4102 1.0000
5.750 0.8382 0.02511 0.01665 -0.0028 0.4031 1.0000
6.000 0.8577 0.02570 0.01745 -0.0019 0.3942 1.0000
6.250 0.8801 0.02580 0.01752 -0.0008 0.3871 1.0000
6.500 0.8986 0.02642 0.01838 0.0002 0.3777 1.0000
6.750 0.9215 0.02643 0.01831 0.0012 0.3708 1.0000
7.000 0.9388 0.02703 0.01920 0.0025 0.3604 1.0000
7.250 0.9596 0.02723 0.01943 0.0036 0.3523 1.0000
7.500 0.9792 0.02743 0.01975 0.0049 0.3425 1.0000
7.750 0.9967 0.02786 0.02035 0.0063 0.3323 1.0000
8.000 1.0194 0.02768 0.02008 0.0074 0.3236 1.0000
8.250 1.0357 0.02798 0.02059 0.0091 0.3121 1.0000
8.500 1.0520 0.02828 0.02106 0.0107 0.3007 1.0000
8.750 1.0704 0.02834 0.02117 0.0123 0.2898 1.0000
9.000 1.0905 0.02817 0.02092 0.0138 0.2785 1.0000
9.250 1.1048 0.02834 0.02125 0.0158 0.2656 1.0000
9.500 1.1176 0.02859 0.02165 0.0180 0.2521 1.0000
9.750 1.1295 0.02883 0.02198 0.0203 0.2382 1.0000
10.000 1.1394 0.02915 0.02236 0.0229 0.2238 1.0000
10.250 1.1467 0.02958 0.02284 0.0257 0.2092 1.0000
10.500 1.1506 0.03018 0.02348 0.0290 0.1947 1.0000
11.000 1.1467 0.03189 0.02529 0.0368 0.1688 1.0000
11.250 1.1393 0.03291 0.02632 0.0414 0.1582 1.0000
11.500 1.1308 0.03386 0.02718 0.0461 0.1491 1.0000
11.750 1.1114 0.03485 0.02828 0.0523 0.1429 1.0000
12.000 1.0981 0.03572 0.02898 0.0576 0.1365 1.0000
12.250 1.0762 0.03704 0.03047 0.0629 0.1318 1.0000
12.500 1.0702 0.03841 0.03162 0.0660 0.1236 1.0000
12.750 1.0531 0.04061 0.03404 0.0686 0.1184 1.0000
13.000 1.0513 0.04242 0.03567 0.0702 0.1101 1.0000
13.250 1.0369 0.04527 0.03874 0.0711 0.1050 1.0000
13.500 1.0384 0.04727 0.04058 0.0721 0.0972 1.0000
13.750 1.0248 0.05066 0.04421 0.0720 0.0929 1.0000
14.000 1.0318 0.05249 0.04584 0.0729 0.0855 1.0000
14.250 1.0158 0.05647 0.05009 0.0721 0.0827 1.0000
14.500 1.0068 0.05996 0.05372 0.0714 0.0788 1.0000
14.750 1.0127 0.06224 0.05591 0.0719 0.0734 1.0000
15.000 0.9960 0.06687 0.06078 0.0702 0.0716 1.0000
15.250 0.9801 0.07178 0.06590 0.0684 0.0699 1.0000
15.500 0.9644 0.07689 0.07119 0.0663 0.0684 1.0000
15.750 0.9802 0.07819 0.07232 0.0676 0.0634 1.0000
16.000 0.9568 0.08449 0.07884 0.0644 0.0632 1.0000
16.250 0.9318 0.09152 0.08607 0.0607 0.0632 1.0000
16.500 0.9058 0.09931 0.09402 0.0565 0.0635 1.0000
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Polar data table (+)
Polar graphs
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