EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 200,000 Max Cl/Cd: 55.5 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e326-il-200000-n5.txt Download as CSV file: xf-e326-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 326 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4231 0.08602 0.08282 -0.0170 1.0000 0.0129
-10.000 -0.5284 0.08113 0.07766 -0.0242 1.0000 0.0130
-9.750 -0.5342 0.07774 0.07426 -0.0254 1.0000 0.0129
-9.500 -0.5461 0.07371 0.07021 -0.0265 1.0000 0.0127
-9.250 -0.5583 0.07023 0.06667 -0.0264 1.0000 0.0126
-9.000 -0.5716 0.06694 0.06333 -0.0252 1.0000 0.0125
-8.750 -0.5859 0.06391 0.06023 -0.0227 1.0000 0.0123
-8.500 -0.5980 0.06112 0.05735 -0.0196 1.0000 0.0121
-8.000 -0.6314 0.04833 0.04388 -0.0105 1.0000 0.0100
-7.750 -0.6309 0.04576 0.04116 -0.0074 1.0000 0.0099
-7.500 -0.6304 0.04277 0.03794 -0.0040 1.0000 0.0098
-7.250 -0.6257 0.04040 0.03540 -0.0010 1.0000 0.0096
-7.000 -0.6221 0.03743 0.03216 0.0027 1.0000 0.0095
-6.750 -0.6015 0.03363 0.02793 0.0031 0.9706 0.0094
-6.500 -0.5684 0.02978 0.02353 0.0014 0.9194 0.0093
-6.250 -0.5312 0.02649 0.01962 -0.0005 0.8758 0.0092
-6.000 -0.5012 0.02425 0.01689 -0.0006 0.8366 0.0092
-5.750 -0.4734 0.02243 0.01461 -0.0001 0.8045 0.0094
-5.500 -0.4471 0.02112 0.01299 0.0006 0.7765 0.0096
-5.250 -0.4207 0.01992 0.01148 0.0013 0.7527 0.0100
-5.000 -0.3966 0.01898 0.01039 0.0021 0.7310 0.0103
-4.750 -0.3736 0.01827 0.00956 0.0030 0.7112 0.0108
-4.500 -0.3509 0.01762 0.00877 0.0041 0.6933 0.0117
-4.250 -0.3281 0.01714 0.00813 0.0052 0.6761 0.0130
-4.000 -0.3064 0.01662 0.00756 0.0063 0.6601 0.0148
-3.750 -0.2844 0.01617 0.00697 0.0075 0.6452 0.0167
-3.250 -0.2417 0.01521 0.00583 0.0102 0.6175 0.0224
-3.000 -0.2203 0.01480 0.00538 0.0115 0.6048 0.0323
-2.750 -0.2009 0.01424 0.00495 0.0131 0.5930 0.0650
-2.500 -0.1835 0.01362 0.00462 0.0149 0.5818 0.1427
-2.250 -0.1879 0.01180 0.00410 0.0203 0.5725 0.4475
-2.000 -0.1735 0.01155 0.00532 0.0252 0.5625 0.8096
-1.750 -0.1486 0.01226 0.00588 0.0272 0.5520 0.8420
-1.500 -0.1134 0.01304 0.00650 0.0271 0.5405 0.8600
-1.250 -0.0703 0.01385 0.00715 0.0254 0.5288 0.8738
-1.000 -0.0370 0.01431 0.00743 0.0251 0.5189 0.8848
-0.750 -0.0002 0.01446 0.00743 0.0235 0.5087 0.8872
-0.500 0.0287 0.01445 0.00729 0.0232 0.4992 0.8891
-0.250 0.0545 0.01444 0.00713 0.0236 0.4909 0.8917
0.250 0.0905 0.01427 0.00677 0.0273 0.4757 0.8994
0.500 0.1205 0.01427 0.00669 0.0268 0.4672 0.9005
1.000 0.1773 0.01428 0.00654 0.0263 0.4522 0.9033
1.250 0.2038 0.01430 0.00646 0.0264 0.4453 0.9051
1.500 0.2285 0.01428 0.00641 0.0269 0.4383 0.9071
1.750 0.2493 0.01427 0.00633 0.0282 0.4320 0.9100
2.000 0.2616 0.01418 0.00619 0.0311 0.4268 0.9140
2.250 0.2909 0.01421 0.00619 0.0307 0.4198 0.9149
2.750 0.3473 0.01430 0.00622 0.0302 0.4074 0.9171
3.000 0.3739 0.01435 0.00623 0.0302 0.4015 0.9184
3.250 0.3999 0.01440 0.00626 0.0304 0.3959 0.9198
3.500 0.4255 0.01445 0.00631 0.0306 0.3899 0.9217
3.750 0.4483 0.01451 0.00634 0.0314 0.3847 0.9238
4.000 0.4679 0.01452 0.00637 0.0328 0.3794 0.9263
4.250 0.4853 0.01452 0.00638 0.0347 0.3741 0.9291
4.500 0.5136 0.01463 0.00646 0.0344 0.3689 0.9301
4.750 0.5422 0.01473 0.00662 0.0340 0.3630 0.9312
5.000 0.5699 0.01484 0.00675 0.0337 0.3573 0.9324
5.250 0.5963 0.01497 0.00686 0.0337 0.3523 0.9337
5.500 0.6222 0.01506 0.00704 0.0338 0.3462 0.9352
5.750 0.6467 0.01517 0.00717 0.0342 0.3406 0.9370
6.000 0.6697 0.01529 0.00732 0.0349 0.3353 0.9391
6.250 0.6901 0.01537 0.00748 0.0361 0.3292 0.9418
6.500 0.7116 0.01550 0.00762 0.0370 0.3239 0.9443
6.750 0.7401 0.01566 0.00787 0.0365 0.3172 0.9455
7.000 0.7674 0.01583 0.00809 0.0362 0.3104 0.9468
7.250 0.7940 0.01600 0.00835 0.0361 0.3037 0.9483
7.500 0.8196 0.01618 0.00859 0.0361 0.2966 0.9500
7.750 0.8440 0.01636 0.00886 0.0364 0.2896 0.9521
8.000 0.8662 0.01654 0.00911 0.0370 0.2819 0.9547
8.250 0.8844 0.01672 0.00935 0.0385 0.2748 0.9582
8.750 0.9395 0.01724 0.01006 0.0374 0.2561 0.9612
9.000 0.9655 0.01754 0.01044 0.0371 0.2459 0.9633
9.250 0.9894 0.01789 0.01083 0.0372 0.2356 0.9659
9.500 1.0113 0.01822 0.01127 0.0376 0.2243 0.9691
9.750 1.0320 0.01862 0.01174 0.0382 0.2124 0.9724
10.000 1.0574 0.01913 0.01231 0.0376 0.1983 0.9743
10.250 1.0808 0.01973 0.01295 0.0372 0.1833 0.9769
10.500 1.1009 0.02043 0.01368 0.0373 0.1678 0.9805
10.750 1.1188 0.02124 0.01451 0.0376 0.1527 0.9847
11.000 1.1396 0.02221 0.01551 0.0371 0.1368 0.9882
11.250 1.1556 0.02328 0.01660 0.0372 0.1224 0.9939
11.500 1.1667 0.02443 0.01779 0.0377 0.1100 1.0000
11.750 1.1455 0.02500 0.01839 0.0448 0.1063 1.0000
12.000 1.1323 0.02618 0.01958 0.0492 0.1007 1.0000
12.250 1.1283 0.02762 0.02108 0.0515 0.0938 1.0000
12.500 1.1224 0.02965 0.02312 0.0530 0.0873 1.0000
12.750 1.1206 0.03172 0.02526 0.0537 0.0809 1.0000
13.000 1.1149 0.03437 0.02794 0.0539 0.0757 1.0000
13.250 1.1123 0.03691 0.03058 0.0539 0.0704 1.0000
13.500 1.1054 0.04006 0.03376 0.0535 0.0659 1.0000
13.750 1.1009 0.04305 0.03685 0.0530 0.0620 1.0000
14.000 1.0943 0.04639 0.04026 0.0524 0.0579 1.0000
14.250 1.0851 0.05011 0.04403 0.0514 0.0551 1.0000
14.500 1.0793 0.05351 0.04753 0.0506 0.0518 1.0000
14.750 1.0721 0.05714 0.05125 0.0495 0.0492 1.0000
15.000 1.0617 0.06131 0.05547 0.0482 0.0463 1.0000
15.250 1.0537 0.06533 0.05956 0.0468 0.0446 1.0000
15.500 1.0482 0.06916 0.06350 0.0454 0.0418 1.0000
15.750 1.0406 0.07338 0.06781 0.0438 0.0396 1.0000
16.000 1.0321 0.07781 0.07230 0.0421 0.0379 1.0000
16.250 1.0239 0.08233 0.07688 0.0402 0.0362 1.0000
16.500 1.0195 0.08636 0.08103 0.0386 0.0345 1.0000
16.750 1.0130 0.09080 0.08556 0.0367 0.0327 1.0000
17.000 1.0061 0.09538 0.09020 0.0346 0.0314 1.0000
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