EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.74 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e326-il-1000000-n5.txt Download as CSV file: xf-e326-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5119 0.08955 0.08797 -0.0149 1.0000 0.0063
-10.000 -0.4517 0.06967 0.06773 -0.0254 0.8052 0.0048
-9.750 -0.5451 0.07462 0.07304 -0.0265 1.0000 0.0061
-9.500 -0.5700 0.06887 0.06721 -0.0279 1.0000 0.0060
-9.250 -0.5892 0.05898 0.05677 -0.0331 0.8495 0.0049
-9.000 -0.6089 0.05651 0.05400 -0.0280 0.7911 0.0049
-8.750 -0.6220 0.05339 0.05066 -0.0241 0.7595 0.0047
-8.500 -0.6288 0.05003 0.04708 -0.0208 0.7356 0.0046
-8.250 -0.6388 0.04539 0.04217 -0.0166 0.7173 0.0043
-8.000 -0.7063 0.02445 0.01974 -0.0014 0.7205 0.0032
-7.750 -0.6930 0.02203 0.01692 0.0010 0.7013 0.0032
-7.500 -0.6758 0.02001 0.01453 0.0029 0.6828 0.0032
-7.250 -0.6549 0.01885 0.01313 0.0041 0.6667 0.0032
-7.000 -0.6331 0.01759 0.01162 0.0052 0.6500 0.0032
-6.750 -0.6102 0.01657 0.01040 0.0061 0.6350 0.0032
-6.500 -0.5870 0.01573 0.00939 0.0069 0.6205 0.0032
-6.250 -0.5633 0.01506 0.00858 0.0077 0.6076 0.0032
-6.000 -0.5398 0.01444 0.00783 0.0085 0.5945 0.0032
-5.750 -0.5165 0.01383 0.00710 0.0094 0.5812 0.0032
-5.500 -0.4930 0.01337 0.00653 0.0103 0.5693 0.0032
-5.250 -0.4697 0.01287 0.00594 0.0112 0.5586 0.0033
-5.000 -0.4462 0.01249 0.00548 0.0120 0.5476 0.0033
-4.750 -0.4226 0.01214 0.00505 0.0129 0.5365 0.0033
-4.500 -0.3989 0.01179 0.00463 0.0137 0.5258 0.0034
-4.250 -0.3748 0.01151 0.00429 0.0145 0.5166 0.0034
-3.750 -0.3273 0.01091 0.00355 0.0162 0.4971 0.0037
-3.500 -0.3029 0.01069 0.00328 0.0169 0.4879 0.0039
-3.250 -0.2780 0.01051 0.00306 0.0175 0.4794 0.0044
-3.000 -0.2529 0.01036 0.00286 0.0181 0.4714 0.0047
-2.750 -0.2279 0.01020 0.00267 0.0187 0.4627 0.0060
-2.500 -0.2024 0.01008 0.00251 0.0192 0.4546 0.0073
-2.250 -0.1772 0.00994 0.00236 0.0197 0.4465 0.0113
-2.000 -0.1519 0.00979 0.00223 0.0202 0.4397 0.0200
-1.750 -0.1269 0.00965 0.00211 0.0208 0.4319 0.0343
-1.500 -0.1038 0.00936 0.00199 0.0216 0.4251 0.0826
-1.250 -0.0817 0.00900 0.00187 0.0226 0.4184 0.1576
-1.000 -0.0772 0.00760 0.00154 0.0267 0.4135 0.4680
-0.750 -0.0798 0.00620 0.00136 0.0329 0.4095 0.7878
-0.500 -0.0534 0.00626 0.00142 0.0333 0.4026 0.8118
-0.250 -0.0263 0.00635 0.00147 0.0336 0.3963 0.8247
0.000 0.0012 0.00643 0.00152 0.0338 0.3906 0.8335
0.250 0.0286 0.00652 0.00157 0.0340 0.3844 0.8407
0.500 0.0564 0.00661 0.00163 0.0341 0.3792 0.8466
0.750 0.0844 0.00668 0.00164 0.0341 0.3731 0.8493
1.000 0.1126 0.00674 0.00163 0.0340 0.3678 0.8506
1.250 0.1409 0.00678 0.00164 0.0338 0.3632 0.8519
1.500 0.1692 0.00683 0.00164 0.0337 0.3572 0.8531
1.750 0.1974 0.00688 0.00166 0.0336 0.3524 0.8541
2.000 0.2259 0.00692 0.00168 0.0334 0.3479 0.8549
2.250 0.2541 0.00698 0.00170 0.0332 0.3425 0.8557
2.500 0.2821 0.00705 0.00174 0.0331 0.3375 0.8566
2.750 0.3105 0.00710 0.00177 0.0330 0.3335 0.8575
3.000 0.3386 0.00717 0.00182 0.0328 0.3284 0.8585
3.250 0.3664 0.00725 0.00187 0.0327 0.3231 0.8595
3.500 0.3947 0.00731 0.00193 0.0325 0.3192 0.8605
3.750 0.4227 0.00738 0.00199 0.0324 0.3141 0.8614
4.000 0.4504 0.00748 0.00205 0.0323 0.3089 0.8624
4.250 0.4784 0.00755 0.00212 0.0321 0.3047 0.8633
4.500 0.5063 0.00764 0.00219 0.0320 0.2992 0.8643
4.750 0.5338 0.00775 0.00229 0.0319 0.2937 0.8652
5.000 0.5617 0.00783 0.00237 0.0317 0.2886 0.8661
5.250 0.5892 0.00794 0.00246 0.0316 0.2824 0.8669
5.500 0.6165 0.00806 0.00257 0.0315 0.2766 0.8678
5.750 0.6439 0.00815 0.00267 0.0315 0.2703 0.8690
6.000 0.6708 0.00829 0.00280 0.0314 0.2636 0.8702
6.250 0.6980 0.00840 0.00293 0.0314 0.2575 0.8714
6.750 0.7515 0.00869 0.00322 0.0314 0.2432 0.8736
7.000 0.7777 0.00888 0.00339 0.0314 0.2342 0.8747
7.250 0.8040 0.00905 0.00356 0.0315 0.2254 0.8759
7.500 0.8299 0.00925 0.00374 0.0316 0.2161 0.8772
7.750 0.8553 0.00948 0.00396 0.0317 0.2065 0.8785
8.000 0.8806 0.00973 0.00418 0.0319 0.1952 0.8798
8.250 0.9056 0.00998 0.00441 0.0321 0.1843 0.8811
8.500 0.9299 0.01028 0.00469 0.0324 0.1719 0.8824
8.750 0.9533 0.01062 0.00499 0.0328 0.1582 0.8838
9.000 0.9757 0.01101 0.00533 0.0333 0.1430 0.8855
9.250 0.9978 0.01141 0.00569 0.0340 0.1296 0.8873
9.500 1.0184 0.01188 0.00612 0.0348 0.1143 0.8894
9.750 1.0385 0.01238 0.00656 0.0356 0.1000 0.8916
10.000 1.0583 0.01287 0.00701 0.0365 0.0875 0.8937
10.250 1.0784 0.01331 0.00744 0.0374 0.0784 0.8959
10.500 1.0971 0.01382 0.00793 0.0384 0.0683 0.8980
10.750 1.1156 0.01427 0.00839 0.0395 0.0615 0.9004
11.000 1.1317 0.01481 0.00892 0.0410 0.0540 0.9034
11.250 1.1482 0.01528 0.00942 0.0424 0.0486 0.9066
11.500 1.1624 0.01582 0.00998 0.0441 0.0434 0.9104
11.750 1.1704 0.01641 0.01058 0.0469 0.0377 0.9149
12.000 1.1791 0.01693 0.01116 0.0496 0.0345 0.9207
12.250 1.1850 0.01761 0.01188 0.0525 0.0308 0.9281
12.500 1.1913 0.01830 0.01265 0.0551 0.0281 0.9379
12.750 1.1967 0.01923 0.01364 0.0572 0.0247 0.9524
13.000 1.2122 0.02042 0.01491 0.0566 0.0212 0.9682
13.250 1.2343 0.02196 0.01651 0.0540 0.0182 0.9818
13.500 1.2519 0.02357 0.01818 0.0521 0.0164 1.0000
13.750 1.2521 0.02551 0.02015 0.0528 0.0145 1.0000
14.000 1.2558 0.02736 0.02208 0.0530 0.0138 1.0000
14.250 1.2556 0.02970 0.02448 0.0530 0.0122 1.0000
14.500 1.2539 0.03235 0.02718 0.0528 0.0110 1.0000
14.750 1.2542 0.03485 0.02977 0.0524 0.0106 1.0000
15.000 1.2531 0.03760 0.03259 0.0519 0.0103 1.0000
15.250 1.2467 0.04093 0.03598 0.0512 0.0091 1.0000
15.500 1.2413 0.04423 0.03936 0.0505 0.0088 1.0000
15.750 1.2375 0.04738 0.04261 0.0497 0.0089 1.0000
16.000 1.2303 0.05095 0.04625 0.0488 0.0082 1.0000
16.250 1.2224 0.05468 0.05007 0.0478 0.0077 1.0000
16.500 1.2157 0.05842 0.05389 0.0466 0.0076 1.0000
16.750 1.2083 0.06235 0.05791 0.0453 0.0074 1.0000
17.000 1.1997 0.06647 0.06210 0.0439 0.0070 1.0000
17.250 1.1905 0.07078 0.06648 0.0424 0.0066 1.0000
17.500 1.1824 0.07504 0.07083 0.0408 0.0064 1.0000
17.750 1.1753 0.07921 0.07508 0.0392 0.0063 1.0000
18.000 1.1682 0.08344 0.07939 0.0375 0.0060 1.0000
18.250 1.1609 0.08780 0.08383 0.0358 0.0059 1.0000
18.500 1.1523 0.09239 0.08850 0.0338 0.0056 1.0000
18.750 1.1443 0.09700 0.09319 0.0319 0.0055 1.0000
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Polar data table (+)
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