EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 500,000 Max Cl/Cd: 74.34 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e340-il-500000-n5.txt Download as CSV file: xf-e340-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 340 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5889 0.08829 0.08614 0.0032 0.8742 0.0064
-10.000 -0.6073 0.08034 0.07793 -0.0036 0.8082 0.0063
-9.500 -0.6447 0.06917 0.06637 -0.0073 0.7524 0.0062
-9.250 -0.6635 0.06443 0.06143 -0.0059 0.7325 0.0062
-9.000 -0.6790 0.06002 0.05682 -0.0034 0.7151 0.0061
-8.750 -0.6904 0.05529 0.05184 -0.0007 0.7001 0.0061
-8.500 -0.6978 0.05024 0.04651 0.0023 0.6864 0.0061
-8.250 -0.7032 0.04467 0.04058 0.0058 0.6740 0.0061
-8.000 -0.7138 0.03663 0.03196 0.0110 0.6650 0.0061
-7.750 -0.7138 0.03078 0.02542 0.0153 0.6540 0.0063
-7.500 -0.7008 0.02794 0.02210 0.0178 0.6399 0.0063
-7.250 -0.6840 0.02571 0.01948 0.0196 0.6258 0.0063
-7.000 -0.6644 0.02382 0.01725 0.0211 0.6122 0.0063
-6.750 -0.6424 0.02231 0.01544 0.0222 0.5989 0.0063
-6.500 -0.6189 0.02098 0.01384 0.0230 0.5865 0.0063
-6.250 -0.5943 0.01984 0.01247 0.0237 0.5747 0.0063
-6.000 -0.5690 0.01885 0.01129 0.0242 0.5637 0.0063
-5.750 -0.5435 0.01800 0.01027 0.0247 0.5529 0.0064
-5.500 -0.5179 0.01724 0.00936 0.0252 0.5415 0.0064
-5.250 -0.4928 0.01648 0.00850 0.0258 0.5308 0.0065
-5.000 -0.4682 0.01576 0.00768 0.0264 0.5211 0.0066
-4.750 -0.4436 0.01518 0.00703 0.0271 0.5118 0.0067
-4.500 -0.4189 0.01470 0.00647 0.0277 0.5033 0.0069
-4.250 -0.3941 0.01427 0.00599 0.0283 0.4946 0.0071
-4.000 -0.3691 0.01391 0.00556 0.0289 0.4865 0.0074
-3.750 -0.3440 0.01357 0.00515 0.0295 0.4776 0.0078
-3.500 -0.3188 0.01327 0.00478 0.0301 0.4698 0.0083
-3.250 -0.2935 0.01298 0.00443 0.0307 0.4619 0.0089
-3.000 -0.2681 0.01272 0.00412 0.0312 0.4551 0.0101
-2.750 -0.2424 0.01249 0.00385 0.0317 0.4485 0.0117
-2.500 -0.2170 0.01228 0.00361 0.0322 0.4417 0.0147
-2.250 -0.1919 0.01205 0.00339 0.0327 0.4355 0.0237
-2.000 -0.1674 0.01176 0.00321 0.0334 0.4288 0.0498
-1.750 -0.1436 0.01147 0.00305 0.0341 0.4227 0.0916
-1.500 -0.1205 0.01109 0.00290 0.0349 0.4177 0.1571
-1.250 -0.1182 0.00948 0.00253 0.0393 0.4135 0.4807
-1.000 -0.1131 0.00854 0.00316 0.0450 0.4093 0.8540
-0.750 -0.0927 0.00888 0.00343 0.0471 0.4048 0.8776
-0.500 -0.0655 0.00923 0.00372 0.0477 0.3996 0.8884
-0.250 -0.0437 0.00951 0.00392 0.0493 0.3944 0.8991
0.000 0.0021 0.01026 0.00458 0.0464 0.3889 0.9038
0.250 0.0352 0.01063 0.00489 0.0458 0.3843 0.9096
0.500 0.0557 0.01066 0.00485 0.0474 0.3799 0.9144
0.750 0.0859 0.01073 0.00483 0.0469 0.3752 0.9151
1.000 0.1158 0.01077 0.00482 0.0464 0.3712 0.9158
1.250 0.1453 0.01081 0.00481 0.0460 0.3672 0.9165
1.500 0.1745 0.01086 0.00480 0.0457 0.3633 0.9173
1.750 0.2029 0.01091 0.00480 0.0455 0.3597 0.9183
2.000 0.2310 0.01096 0.00480 0.0454 0.3564 0.9193
2.250 0.2580 0.01098 0.00480 0.0455 0.3527 0.9206
2.500 0.2837 0.01100 0.00478 0.0459 0.3488 0.9220
2.750 0.3068 0.01101 0.00476 0.0467 0.3453 0.9240
3.000 0.3173 0.01092 0.00463 0.0501 0.3423 0.9281
3.250 0.3459 0.01095 0.00465 0.0498 0.3392 0.9285
3.500 0.3740 0.01098 0.00468 0.0497 0.3362 0.9290
3.750 0.4018 0.01102 0.00472 0.0495 0.3330 0.9295
4.000 0.4298 0.01110 0.00477 0.0493 0.3298 0.9301
4.250 0.4574 0.01120 0.00483 0.0492 0.3264 0.9308
4.500 0.4848 0.01124 0.00489 0.0491 0.3234 0.9314
4.750 0.5116 0.01128 0.00496 0.0492 0.3200 0.9321
5.000 0.5379 0.01134 0.00501 0.0493 0.3164 0.9328
5.250 0.5635 0.01142 0.00508 0.0495 0.3134 0.9337
5.500 0.5886 0.01151 0.00517 0.0499 0.3104 0.9346
5.750 0.6142 0.01156 0.00526 0.0501 0.3074 0.9358
6.000 0.6384 0.01161 0.00533 0.0507 0.3039 0.9370
6.250 0.6614 0.01166 0.00539 0.0514 0.3005 0.9383
6.500 0.6831 0.01172 0.00546 0.0524 0.2969 0.9397
6.750 0.7050 0.01177 0.00552 0.0533 0.2935 0.9411
7.000 0.7298 0.01182 0.00562 0.0536 0.2897 0.9419
7.250 0.7562 0.01193 0.00576 0.0536 0.2855 0.9424
7.500 0.7821 0.01207 0.00590 0.0537 0.2812 0.9430
7.750 0.8086 0.01219 0.00607 0.0536 0.2769 0.9436
8.000 0.8347 0.01231 0.00624 0.0536 0.2716 0.9444
8.250 0.8596 0.01247 0.00641 0.0538 0.2668 0.9451
8.500 0.8847 0.01260 0.00660 0.0540 0.2623 0.9459
8.750 0.9094 0.01274 0.00678 0.0542 0.2562 0.9467
9.000 0.9329 0.01294 0.00698 0.0546 0.2498 0.9477
9.250 0.9570 0.01309 0.00719 0.0549 0.2430 0.9487
9.500 0.9794 0.01332 0.00743 0.0554 0.2362 0.9499
9.750 1.0024 0.01352 0.00767 0.0558 0.2282 0.9511
10.000 1.0240 0.01379 0.00794 0.0564 0.2196 0.9524
10.250 1.0459 0.01407 0.00825 0.0569 0.2101 0.9536
10.500 1.0680 0.01441 0.00861 0.0573 0.2007 0.9544
10.750 1.0884 0.01483 0.00904 0.0579 0.1896 0.9555
11.000 1.1075 0.01531 0.00952 0.0586 0.1784 0.9569
11.250 1.1256 0.01583 0.01004 0.0595 0.1668 0.9584
11.500 1.1419 0.01641 0.01062 0.0604 0.1542 0.9601
11.750 1.1558 0.01711 0.01130 0.0616 0.1410 0.9622
12.000 1.1659 0.01786 0.01204 0.0633 0.1288 0.9644
12.250 1.1755 0.01876 0.01296 0.0648 0.1180 0.9665
12.500 1.1834 0.01987 0.01409 0.0660 0.1078 0.9691
12.750 1.1891 0.02128 0.01552 0.0667 0.0989 0.9722
13.000 1.1952 0.02302 0.01730 0.0666 0.0906 0.9747
13.250 1.2019 0.02504 0.01938 0.0658 0.0833 0.9773
13.500 1.2050 0.02762 0.02201 0.0645 0.0767 0.9807
13.750 1.2083 0.03022 0.02468 0.0632 0.0709 0.9854
14.000 1.2069 0.03335 0.02787 0.0618 0.0662 0.9901
14.250 1.2072 0.03644 0.03104 0.0603 0.0620 0.9941
14.750 1.2033 0.04372 0.03847 0.0558 0.0548 0.9971
15.000 1.1983 0.04761 0.04245 0.0536 0.0515 0.9983
15.500 1.1768 0.05516 0.05013 0.0518 0.0468 1.0000
15.750 1.1673 0.05905 0.05408 0.0507 0.0444 1.0000
16.000 1.1568 0.06326 0.05835 0.0494 0.0420 1.0000
16.250 1.1494 0.06716 0.06232 0.0481 0.0398 1.0000
16.500 1.1422 0.07115 0.06636 0.0467 0.0373 1.0000
16.750 1.1326 0.07552 0.07078 0.0451 0.0351 1.0000
17.000 1.1264 0.07950 0.07483 0.0436 0.0333 1.0000
17.250 1.1199 0.08357 0.07896 0.0421 0.0310 1.0000
17.750 1.1061 0.09197 0.08747 0.0388 0.0273 1.0000
18.000 1.0994 0.09622 0.09176 0.0371 0.0253 1.0000
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Polar data table (+)
Polar graphs
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