EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 435 AIRFOIL (e435-il) Reynolds number: 200,000 Max Cl/Cd: 78.3 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e435-il-200000-n5.txt Download as CSV file: xf-e435-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 435 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2474 0.05024 0.04590 -0.1389 0.9165 0.0103
-10.250 -0.2485 0.04533 0.04074 -0.1447 0.9059 0.0102
-10.000 -0.2534 0.04059 0.03565 -0.1493 0.8946 0.0102
-9.750 -0.2544 0.03731 0.03206 -0.1512 0.8835 0.0101
-9.500 -0.2633 0.03475 0.02918 -0.1501 0.8713 0.0101
-9.250 -0.2624 0.03218 0.02623 -0.1494 0.8625 0.0101
-9.000 -0.2550 0.03019 0.02392 -0.1484 0.8547 0.0101
-8.750 -0.2420 0.02815 0.02150 -0.1480 0.8491 0.0102
-8.500 -0.2298 0.02660 0.01970 -0.1467 0.8423 0.0103
-8.250 -0.2114 0.02523 0.01814 -0.1463 0.8370 0.0105
-8.000 -0.1909 0.02408 0.01682 -0.1460 0.8324 0.0107
-7.750 -0.1733 0.02311 0.01572 -0.1450 0.8267 0.0111
-7.500 -0.1523 0.02214 0.01460 -0.1445 0.8221 0.0113
-7.250 -0.1290 0.02119 0.01348 -0.1443 0.8184 0.0118
-7.000 -0.1092 0.02037 0.01255 -0.1434 0.8135 0.0123
-6.750 -0.0888 0.01962 0.01167 -0.1426 0.8086 0.0129
-6.500 -0.0663 0.01892 0.01092 -0.1424 0.8047 0.0136
-6.250 -0.0408 0.01836 0.01026 -0.1426 0.8015 0.0151
-6.000 -0.0195 0.01786 0.00972 -0.1419 0.7970 0.0167
-5.750 0.0036 0.01740 0.00919 -0.1416 0.7926 0.0193
-5.500 0.0281 0.01684 0.00858 -0.1415 0.7888 0.0221
-5.250 0.0548 0.01633 0.00799 -0.1419 0.7858 0.0272
-5.000 0.0792 0.01585 0.00755 -0.1418 0.7820 0.0365
-4.750 0.1034 0.01541 0.00715 -0.1417 0.7778 0.0518
-4.500 0.1295 0.01493 0.00678 -0.1420 0.7740 0.0793
-4.250 0.1571 0.01440 0.00642 -0.1428 0.7709 0.1260
-4.000 0.1862 0.01371 0.00602 -0.1441 0.7682 0.2117
-3.750 0.2114 0.01285 0.00572 -0.1449 0.7640 0.3527
-3.500 0.2374 0.01248 0.00595 -0.1450 0.7601 0.5120
-3.250 0.2658 0.01259 0.00602 -0.1451 0.7568 0.5587
-3.000 0.2949 0.01272 0.00609 -0.1452 0.7538 0.5834
-2.750 0.3236 0.01287 0.00614 -0.1453 0.7508 0.6012
-2.500 0.3492 0.01302 0.00625 -0.1448 0.7466 0.6142
-2.250 0.3763 0.01319 0.00635 -0.1446 0.7429 0.6280
-2.000 0.4040 0.01340 0.00649 -0.1444 0.7395 0.6432
-1.750 0.4319 0.01357 0.00662 -0.1442 0.7367 0.6528
-1.500 0.4597 0.01364 0.00660 -0.1444 0.7331 0.6597
-1.250 0.4849 0.01370 0.00666 -0.1439 0.7290 0.6630
-1.000 0.5125 0.01373 0.00664 -0.1440 0.7252 0.6663
-0.750 0.5418 0.01374 0.00657 -0.1444 0.7220 0.6698
-0.500 0.5730 0.01375 0.00646 -0.1453 0.7192 0.6732
-0.250 0.5980 0.01381 0.00651 -0.1451 0.7147 0.6764
0.000 0.6242 0.01385 0.00654 -0.1449 0.7105 0.6786
0.250 0.6524 0.01387 0.00653 -0.1451 0.7068 0.6809
0.500 0.6825 0.01388 0.00648 -0.1457 0.7037 0.6836
0.750 0.7075 0.01396 0.00657 -0.1454 0.6990 0.6868
1.000 0.7341 0.01402 0.00661 -0.1454 0.6943 0.6900
1.250 0.7630 0.01404 0.00659 -0.1458 0.6903 0.6929
1.500 0.7928 0.01405 0.00656 -0.1463 0.6869 0.6949
1.750 0.8151 0.01415 0.00674 -0.1454 0.6813 0.6973
2.000 0.8411 0.01420 0.00681 -0.1452 0.6764 0.7003
2.250 0.8701 0.01423 0.00680 -0.1456 0.6723 0.7035
2.500 0.8952 0.01431 0.00691 -0.1453 0.6668 0.7067
2.750 0.9206 0.01438 0.00700 -0.1451 0.6610 0.7097
3.000 0.9484 0.01439 0.00701 -0.1452 0.6562 0.7120
3.250 0.9715 0.01449 0.00717 -0.1445 0.6500 0.7147
3.500 0.9961 0.01456 0.00729 -0.1440 0.6438 0.7179
3.750 1.0244 0.01459 0.00730 -0.1442 0.6386 0.7215
4.000 1.0460 0.01473 0.00751 -0.1433 0.6311 0.7253
4.250 1.0720 0.01477 0.00757 -0.1431 0.6249 0.7281
4.500 1.0934 0.01489 0.00776 -0.1420 0.6171 0.7311
4.750 1.1177 0.01496 0.00786 -0.1415 0.6097 0.7344
5.000 1.1394 0.01509 0.00805 -0.1405 0.6014 0.7382
5.250 1.1635 0.01520 0.00816 -0.1400 0.5931 0.7423
5.500 1.1824 0.01534 0.00839 -0.1385 0.5837 0.7457
5.750 1.2039 0.01547 0.00854 -0.1374 0.5744 0.7496
6.000 1.2220 0.01564 0.00878 -0.1357 0.5635 0.7541
6.250 1.2394 0.01584 0.00900 -0.1340 0.5524 0.7587
6.500 1.2560 0.01604 0.00923 -0.1320 0.5410 0.7625
6.750 1.2725 0.01629 0.00951 -0.1301 0.5286 0.7669
7.000 1.2872 0.01661 0.00986 -0.1279 0.5149 0.7721
7.250 1.3014 0.01697 0.01025 -0.1257 0.5005 0.7774
7.500 1.3142 0.01738 0.01067 -0.1233 0.4852 0.7829
7.750 1.3261 0.01787 0.01117 -0.1208 0.4687 0.7893
8.000 1.3362 0.01844 0.01172 -0.1181 0.4514 0.7953
8.250 1.3450 0.01909 0.01236 -0.1153 0.4339 0.8021
8.500 1.3531 0.01983 0.01309 -0.1125 0.4158 0.8094
8.750 1.3599 0.02064 0.01390 -0.1096 0.3979 0.8175
9.000 1.3663 0.02154 0.01480 -0.1068 0.3803 0.8271
9.250 1.3715 0.02252 0.01579 -0.1040 0.3626 0.8387
9.500 1.3757 0.02358 0.01685 -0.1011 0.3453 0.8528
10.000 1.3795 0.02571 0.01908 -0.0947 0.3131 0.9151
10.250 1.3823 0.02694 0.02030 -0.0922 0.2970 1.0000
10.500 1.3880 0.02842 0.02174 -0.0904 0.2804 1.0000
10.750 1.3933 0.02998 0.02326 -0.0886 0.2642 1.0000
11.000 1.3982 0.03162 0.02487 -0.0870 0.2483 1.0000
11.250 1.4029 0.03332 0.02655 -0.0854 0.2328 1.0000
11.500 1.4073 0.03512 0.02832 -0.0839 0.2177 1.0000
11.750 1.4118 0.03695 0.03014 -0.0825 0.2034 1.0000
12.000 1.4162 0.03886 0.03204 -0.0811 0.1896 1.0000
12.250 1.4205 0.04084 0.03401 -0.0799 0.1765 1.0000
12.500 1.4243 0.04292 0.03608 -0.0788 0.1641 1.0000
12.750 1.4277 0.04509 0.03825 -0.0777 0.1523 1.0000
13.250 1.4349 0.04959 0.04277 -0.0759 0.1294 1.0000
13.500 1.4387 0.05191 0.04511 -0.0752 0.1193 1.0000
13.750 1.4414 0.05440 0.04761 -0.0745 0.1099 1.0000
14.000 1.4431 0.05705 0.05027 -0.0739 0.1012 1.0000
14.250 1.4470 0.05954 0.05283 -0.0735 0.0931 1.0000
14.500 1.4487 0.06233 0.05566 -0.0731 0.0858 1.0000
14.750 1.4501 0.06521 0.05857 -0.0728 0.0787 1.0000
15.000 1.4522 0.06807 0.06150 -0.0726 0.0725 1.0000
15.250 1.4518 0.07132 0.06478 -0.0726 0.0668 1.0000
15.500 1.4539 0.07430 0.06786 -0.0726 0.0613 1.0000
15.750 1.4524 0.07782 0.07142 -0.0728 0.0566 1.0000
16.000 1.4537 0.08102 0.07473 -0.0730 0.0520 1.0000
16.250 1.4512 0.08482 0.07857 -0.0735 0.0483 1.0000
16.500 1.4519 0.08823 0.08210 -0.0740 0.0446 1.0000
16.750 1.4488 0.09225 0.08618 -0.0747 0.0416 1.0000
17.000 1.4479 0.09598 0.09003 -0.0755 0.0387 1.0000
17.250 1.4455 0.10001 0.09416 -0.0764 0.0361 1.0000
17.500 1.4414 0.10435 0.09858 -0.0776 0.0340 1.0000
17.750 1.4400 0.10832 0.10269 -0.0788 0.0318 1.0000
18.000 1.4360 0.11276 0.10722 -0.0802 0.0299 1.0000
18.250 1.4314 0.11733 0.11189 -0.0819 0.0284 1.0000
18.500 1.4291 0.12156 0.11626 -0.0835 0.0267 1.0000
18.750 1.4249 0.12615 0.12095 -0.0854 0.0253 1.0000
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Polar data table (+)
Polar graphs
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