EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 200,000 Max Cl/Cd: 51.11 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e325-il-200000-n5.txt Download as CSV file: xf-e325-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5842 0.09287 0.08943 -0.0053 1.0000 0.0104
-10.500 -0.5964 0.08483 0.08140 -0.0114 1.0000 0.0104
-10.250 -0.6143 0.07782 0.07432 -0.0155 1.0000 0.0104
-10.000 -0.6208 0.07504 0.07152 -0.0162 1.0000 0.0101
-9.750 -0.6393 0.07031 0.06671 -0.0165 1.0000 0.0101
-9.500 -0.6576 0.06614 0.06244 -0.0153 1.0000 0.0100
-9.250 -0.6726 0.06284 0.05903 -0.0129 1.0000 0.0099
-9.000 -0.6875 0.05958 0.05565 -0.0095 1.0000 0.0098
-8.750 -0.7050 0.05493 0.05076 -0.0050 1.0000 0.0101
-8.500 -0.7112 0.05151 0.04714 -0.0015 1.0000 0.0100
-8.250 -0.7184 0.04688 0.04217 0.0026 1.0000 0.0102
-8.000 -0.7268 0.04153 0.03626 0.0078 1.0000 0.0105
-7.750 -0.7193 0.03968 0.03429 0.0102 1.0000 0.0107
-7.500 -0.7097 0.03791 0.03238 0.0125 1.0000 0.0110
-7.250 -0.7055 0.03313 0.02689 0.0170 1.0000 0.0106
-6.500 -0.6547 0.02643 0.01919 0.0231 1.0000 0.0105
-6.250 -0.6221 0.02440 0.01691 0.0220 0.9642 0.0107
-6.000 -0.5702 0.02227 0.01448 0.0170 0.8985 0.0109
-5.750 -0.5326 0.02093 0.01289 0.0152 0.8466 0.0112
-5.500 -0.5049 0.01993 0.01165 0.0155 0.8077 0.0115
-5.250 -0.4800 0.01905 0.01058 0.0163 0.7768 0.0120
-5.000 -0.4573 0.01828 0.00964 0.0174 0.7506 0.0126
-4.750 -0.4357 0.01762 0.00880 0.0188 0.7275 0.0133
-4.500 -0.4151 0.01704 0.00811 0.0202 0.7069 0.0139
-4.250 -0.3939 0.01658 0.00752 0.0216 0.6881 0.0161
-4.000 -0.3726 0.01615 0.00701 0.0228 0.6705 0.0194
-3.750 -0.3515 0.01571 0.00645 0.0242 0.6541 0.0219
-3.500 -0.3311 0.01521 0.00588 0.0257 0.6390 0.0301
-3.250 -0.3118 0.01469 0.00543 0.0273 0.6247 0.0529
-3.000 -0.2948 0.01403 0.00505 0.0292 0.6111 0.1178
-2.750 -0.2866 0.01292 0.00460 0.0325 0.5993 0.2724
-2.250 -0.2607 0.01207 0.00594 0.0409 0.5767 0.8229
-2.000 -0.2370 0.01277 0.00650 0.0430 0.5646 0.8472
-1.750 -0.1908 0.01375 0.00728 0.0408 0.5511 0.8604
-1.500 -0.1323 0.01479 0.00811 0.0361 0.5371 0.8706
-1.250 -0.1172 0.01490 0.00807 0.0389 0.5276 0.8806
-1.000 -0.0820 0.01495 0.00797 0.0375 0.5160 0.8818
-0.750 -0.0499 0.01496 0.00784 0.0366 0.5057 0.8832
-0.500 -0.0197 0.01497 0.00770 0.0361 0.4960 0.8848
-0.250 0.0095 0.01495 0.00759 0.0358 0.4858 0.8867
0.000 0.0351 0.01493 0.00746 0.0361 0.4773 0.8892
0.250 0.0367 0.01473 0.00720 0.0412 0.4703 0.8961
0.500 0.0682 0.01474 0.00711 0.0404 0.4619 0.8970
0.750 0.0987 0.01474 0.00703 0.0397 0.4530 0.8980
1.000 0.1286 0.01475 0.00696 0.0392 0.4452 0.8992
1.250 0.1575 0.01476 0.00690 0.0388 0.4372 0.9006
1.500 0.1847 0.01476 0.00684 0.0388 0.4300 0.9021
1.750 0.2107 0.01476 0.00680 0.0390 0.4224 0.9039
2.000 0.2328 0.01476 0.00674 0.0400 0.4163 0.9064
2.250 0.2363 0.01461 0.00659 0.0447 0.4110 0.9118
2.500 0.2659 0.01465 0.00658 0.0442 0.4040 0.9126
2.750 0.2946 0.01468 0.00660 0.0438 0.3973 0.9135
3.000 0.3230 0.01472 0.00662 0.0435 0.3907 0.9144
3.250 0.3514 0.01479 0.00664 0.0431 0.3847 0.9156
3.500 0.3792 0.01483 0.00671 0.0429 0.3780 0.9169
3.750 0.4046 0.01489 0.00675 0.0432 0.3721 0.9183
4.000 0.4284 0.01493 0.00681 0.0438 0.3663 0.9200
4.250 0.4500 0.01496 0.00685 0.0448 0.3604 0.9221
4.500 0.4638 0.01498 0.00685 0.0474 0.3556 0.9258
4.750 0.4848 0.01501 0.00693 0.0486 0.3500 0.9277
5.000 0.5129 0.01510 0.00705 0.0482 0.3437 0.9286
5.250 0.5404 0.01522 0.00717 0.0480 0.3380 0.9295
5.500 0.5678 0.01531 0.00735 0.0478 0.3311 0.9305
5.750 0.5942 0.01544 0.00747 0.0478 0.3250 0.9317
6.000 0.6209 0.01556 0.00768 0.0477 0.3183 0.9332
6.250 0.6460 0.01569 0.00785 0.0480 0.3118 0.9350
6.500 0.6688 0.01581 0.00803 0.0486 0.3056 0.9370
6.750 0.6882 0.01590 0.00819 0.0500 0.2989 0.9396
7.000 0.7034 0.01600 0.00831 0.0522 0.2934 0.9426
7.250 0.7316 0.01616 0.00859 0.0517 0.2854 0.9436
7.500 0.7587 0.01636 0.00882 0.0514 0.2778 0.9447
7.750 0.7857 0.01654 0.00912 0.0512 0.2688 0.9459
8.000 0.8120 0.01676 0.00942 0.0510 0.2600 0.9475
8.250 0.8367 0.01700 0.00970 0.0511 0.2503 0.9495
8.500 0.8599 0.01723 0.01004 0.0515 0.2399 0.9518
8.750 0.8786 0.01747 0.01035 0.0527 0.2308 0.9547
9.000 0.8964 0.01776 0.01067 0.0541 0.2207 0.9577
9.250 0.9228 0.01812 0.01114 0.0536 0.2078 0.9590
9.500 0.9480 0.01855 0.01164 0.0533 0.1943 0.9606
9.750 0.9712 0.01906 0.01219 0.0532 0.1796 0.9626
10.250 1.0070 0.02027 0.01346 0.0548 0.1489 0.9696
10.500 1.0268 0.02107 0.01429 0.0548 0.1326 0.9724
10.750 1.0471 0.02203 0.01527 0.0544 0.1162 0.9750
11.000 1.0633 0.02308 0.01635 0.0546 0.1022 0.9788
11.250 1.0750 0.02421 0.01750 0.0554 0.0900 0.9838
11.500 1.0887 0.02549 0.01885 0.0552 0.0791 0.9880
11.750 1.0973 0.02698 0.02040 0.0552 0.0703 0.9939
12.000 1.1072 0.02898 0.02247 0.0537 0.0626 0.9998
12.250 1.0871 0.03030 0.02386 0.0584 0.0605 1.0000
12.500 1.0720 0.03212 0.02572 0.0614 0.0577 1.0000
12.750 1.0604 0.03453 0.02817 0.0629 0.0548 1.0000
13.000 1.0530 0.03708 0.03080 0.0635 0.0517 1.0000
13.250 1.0459 0.03989 0.03369 0.0637 0.0485 1.0000
13.500 1.0359 0.04325 0.03709 0.0633 0.0457 1.0000
13.750 1.0290 0.04643 0.04036 0.0629 0.0433 1.0000
14.000 1.0219 0.04976 0.04379 0.0622 0.0409 1.0000
14.250 1.0122 0.05350 0.04760 0.0613 0.0390 1.0000
14.500 1.0013 0.05750 0.05165 0.0601 0.0373 1.0000
14.750 0.9945 0.06108 0.05534 0.0591 0.0353 1.0000
15.000 0.9866 0.06497 0.05932 0.0579 0.0338 1.0000
15.250 0.9774 0.06922 0.06364 0.0563 0.0323 1.0000
15.500 0.9666 0.07382 0.06826 0.0545 0.0308 1.0000
15.750 0.9615 0.07774 0.07230 0.0530 0.0294 1.0000
16.000 0.9545 0.08199 0.07665 0.0513 0.0279 1.0000
16.250 0.9468 0.08649 0.08122 0.0494 0.0267 1.0000
16.500 0.9388 0.09111 0.08590 0.0475 0.0259 1.0000
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