EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 500,000 Max Cl/Cd: 92.64 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e343-il-500000.txt Download as CSV file: xf-e343-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 343 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3103 0.10743 0.10525 -0.0267 1.0000 0.0150
-10.250 -0.3076 0.10417 0.10202 -0.0277 1.0000 0.0152
-10.000 -0.3057 0.10076 0.09863 -0.0289 1.0000 0.0152
-9.750 -0.1766 0.07982 0.07726 -0.0525 0.7981 0.0174
-9.500 -0.1814 0.07536 0.07268 -0.0543 0.7706 0.0175
-9.250 -0.1891 0.07011 0.06735 -0.0570 0.7512 0.0175
-9.000 -0.1951 0.06529 0.06247 -0.0597 0.7341 0.0175
-8.750 -0.2097 0.05936 0.05647 -0.0643 0.7215 0.0175
-8.500 -0.2547 0.06720 0.06429 -0.0688 0.7585 0.0172
-8.250 -0.2684 0.06404 0.06097 -0.0676 0.7336 0.0172
-8.000 -0.2887 0.06023 0.05696 -0.0648 0.7161 0.0174
-7.750 -0.2942 0.05711 0.05365 -0.0627 0.6986 0.0175
-7.500 -0.3019 0.05321 0.04948 -0.0598 0.6847 0.0175
-7.000 -0.2742 0.03620 0.03252 -0.0542 0.6338 0.0180
-6.750 -0.2698 0.03375 0.02995 -0.0524 0.6231 0.0182
-6.500 -0.2641 0.03123 0.02729 -0.0506 0.6126 0.0185
-6.250 -0.2570 0.02862 0.02454 -0.0486 0.6031 0.0190
-6.000 -0.2488 0.02594 0.02166 -0.0465 0.5937 0.0196
-5.750 -0.2505 0.03718 0.03239 -0.0460 0.5987 0.0201
-5.250 -0.2275 0.03145 0.02604 -0.0403 0.5806 0.0220
-5.000 -0.2105 0.03007 0.02451 -0.0389 0.5709 0.0226
-4.750 -0.1923 0.02849 0.02274 -0.0371 0.5612 0.0236
-4.500 -0.1769 0.02599 0.01974 -0.0341 0.5536 0.0263
-4.250 -0.1568 0.01924 0.01209 -0.0298 0.5476 0.0148
-4.000 -0.1308 0.01773 0.01033 -0.0289 0.5391 0.0137
-3.750 -0.1037 0.01626 0.00864 -0.0283 0.5310 0.0135
-3.500 -0.0771 0.01534 0.00751 -0.0277 0.5229 0.0138
-3.250 -0.0510 0.01468 0.00672 -0.0271 0.5154 0.0140
-3.000 -0.0267 0.01390 0.00586 -0.0262 0.5076 0.0149
-2.750 -0.0028 0.01347 0.00539 -0.0254 0.5006 0.0155
-2.500 0.0214 0.01309 0.00498 -0.0245 0.4936 0.0165
-2.250 0.0449 0.01280 0.00459 -0.0235 0.4871 0.0179
-2.000 0.0686 0.01249 0.00430 -0.0226 0.4813 0.0197
-1.750 0.0922 0.01218 0.00395 -0.0216 0.4753 0.0219
-1.500 0.1158 0.01195 0.00367 -0.0206 0.4698 0.0258
-1.250 0.1390 0.01163 0.00338 -0.0196 0.4646 0.0377
-1.000 0.1596 0.01111 0.00320 -0.0182 0.4593 0.1182
-0.750 0.1553 0.00925 0.00291 -0.0126 0.4555 0.5676
-0.500 0.1568 0.00890 0.00358 -0.0059 0.4515 0.8714
-0.250 0.1758 0.00929 0.00394 -0.0031 0.4474 0.9013
0.000 0.2072 0.00989 0.00452 -0.0024 0.4427 0.9216
0.250 0.3020 0.01123 0.00563 -0.0147 0.4355 0.9331
0.500 0.3920 0.01197 0.00623 -0.0268 0.4289 0.9418
0.750 0.4350 0.01212 0.00630 -0.0298 0.4244 0.9459
1.000 0.4606 0.01217 0.00627 -0.0294 0.4206 0.9489
1.250 0.4927 0.01225 0.00624 -0.0305 0.4165 0.9502
1.500 0.5226 0.01224 0.00622 -0.0310 0.4135 0.9522
1.750 0.5430 0.01227 0.00623 -0.0296 0.4099 0.9555
2.000 0.5753 0.01227 0.00618 -0.0307 0.4063 0.9566
2.250 0.6052 0.01231 0.00616 -0.0313 0.4029 0.9580
2.500 0.6315 0.01242 0.00621 -0.0312 0.3995 0.9600
2.750 0.6520 0.01243 0.00623 -0.0298 0.3969 0.9626
3.000 0.6836 0.01242 0.00621 -0.0308 0.3935 0.9636
3.250 0.7128 0.01243 0.00621 -0.0313 0.3904 0.9648
3.500 0.7391 0.01248 0.00623 -0.0312 0.3876 0.9662
3.750 0.7609 0.01262 0.00631 -0.0301 0.3844 0.9684
4.000 0.7847 0.01267 0.00636 -0.0295 0.3817 0.9698
4.250 0.8139 0.01266 0.00639 -0.0300 0.3789 0.9706
4.500 0.8431 0.01269 0.00643 -0.0306 0.3760 0.9716
4.750 0.8699 0.01273 0.00646 -0.0306 0.3729 0.9728
5.000 0.8940 0.01281 0.00652 -0.0302 0.3701 0.9738
5.250 0.9172 0.01301 0.00668 -0.0295 0.3670 0.9751
5.500 0.9356 0.01307 0.00679 -0.0278 0.3648 0.9770
5.750 0.9632 0.01308 0.00685 -0.0280 0.3620 0.9776
6.000 0.9899 0.01312 0.00691 -0.0281 0.3589 0.9782
6.250 1.0169 0.01318 0.00699 -0.0283 0.3558 0.9790
6.500 1.0441 0.01331 0.00710 -0.0285 0.3526 0.9800
6.750 1.0689 0.01347 0.00727 -0.0283 0.3496 0.9808
7.000 1.0922 0.01351 0.00739 -0.0277 0.3467 0.9817
7.250 1.1147 0.01358 0.00751 -0.0269 0.3435 0.9826
7.500 1.1362 0.01367 0.00763 -0.0260 0.3404 0.9837
7.750 1.1558 0.01382 0.00778 -0.0247 0.3372 0.9852
8.000 1.1797 0.01400 0.00798 -0.0243 0.3336 0.9859
8.250 1.2054 0.01404 0.00812 -0.0243 0.3302 0.9866
8.500 1.2306 0.01412 0.00826 -0.0242 0.3265 0.9872
8.750 1.2550 0.01423 0.00839 -0.0240 0.3226 0.9880
9.000 1.2785 0.01447 0.00862 -0.0237 0.3185 0.9889
9.250 1.3019 0.01454 0.00881 -0.0233 0.3148 0.9898
9.500 1.3256 0.01464 0.00898 -0.0229 0.3101 0.9911
9.750 1.3481 0.01482 0.00918 -0.0224 0.3058 0.9924
10.000 1.3681 0.01501 0.00943 -0.0214 0.3011 0.9935
10.250 1.3901 0.01515 0.00966 -0.0208 0.2963 0.9946
10.500 1.4139 0.01534 0.00988 -0.0207 0.2907 0.9955
10.750 1.4371 0.01556 0.01017 -0.0205 0.2851 0.9966
11.000 1.4600 0.01576 0.01045 -0.0202 0.2786 0.9978
11.250 1.4807 0.01609 0.01079 -0.0197 0.2724 0.9991
11.500 1.5003 0.01632 0.01113 -0.0188 0.2650 1.0000
11.750 1.4986 0.01664 0.01144 -0.0138 0.2596 1.0000
12.000 1.4922 0.01681 0.01169 -0.0078 0.2547 1.0000
12.250 1.4800 0.01702 0.01196 -0.0009 0.2496 1.0000
12.500 1.4621 0.01735 0.01228 0.0067 0.2451 1.0000
12.750 1.4602 0.01773 0.01273 0.0112 0.2391 1.0000
13.000 1.4583 0.01845 0.01344 0.0150 0.2315 1.0000
13.250 1.4629 0.01924 0.01428 0.0174 0.2227 1.0000
13.500 1.4636 0.02041 0.01546 0.0198 0.2140 1.0000
13.750 1.4645 0.02179 0.01686 0.0217 0.2044 1.0000
14.000 1.4655 0.02333 0.01844 0.0232 0.1952 1.0000
14.250 1.4616 0.02539 0.02051 0.0245 0.1867 1.0000
14.500 1.4577 0.02765 0.02280 0.0255 0.1773 1.0000
14.750 1.4529 0.03013 0.02532 0.0263 0.1692 1.0000
15.250 1.4346 0.03626 0.03151 0.0272 0.1534 1.0000
15.500 1.4199 0.04002 0.03530 0.0274 0.1467 1.0000
15.750 1.4095 0.04347 0.03880 0.0274 0.1395 1.0000
16.000 1.3935 0.04759 0.04296 0.0272 0.1340 1.0000
16.250 1.3832 0.05129 0.04671 0.0268 0.1273 1.0000
16.500 1.3650 0.05597 0.05141 0.0261 0.1218 1.0000
16.750 1.3561 0.05972 0.05522 0.0255 0.1158 1.0000
17.000 1.3408 0.06435 0.05988 0.0246 0.1108 1.0000
17.250 1.3316 0.06832 0.06390 0.0237 0.1052 1.0000
17.500 1.3196 0.07271 0.06832 0.0226 0.1003 1.0000
17.750 1.3099 0.07692 0.07258 0.0214 0.0960 1.0000
18.000 1.3005 0.08118 0.07687 0.0202 0.0908 1.0000
18.250 1.2872 0.08600 0.08171 0.0187 0.0864 1.0000
18.500 1.2840 0.08956 0.08534 0.0175 0.0822 1.0000
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