EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 200,000 Max Cl/Cd: 62.56 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e327-il-200000.txt Download as CSV file: xf-e327-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 327 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4733 0.08724 0.08381 -0.0355 1.0000 0.0403
-9.250 -0.5014 0.08395 0.08043 -0.0355 1.0000 0.0404
-9.000 -0.5168 0.08133 0.07777 -0.0334 1.0000 0.0404
-8.750 -0.4845 0.07547 0.07213 -0.0344 1.0000 0.0418
-8.500 -0.4933 0.07267 0.06933 -0.0330 1.0000 0.0421
-8.250 -0.5032 0.07008 0.06673 -0.0306 1.0000 0.0426
-8.000 -0.5090 0.06737 0.06400 -0.0286 1.0000 0.0434
-7.750 -0.5147 0.06465 0.06123 -0.0264 1.0000 0.0443
-7.500 -0.5201 0.06190 0.05841 -0.0238 1.0000 0.0455
-7.250 -0.5261 0.05938 0.05572 -0.0205 1.0000 0.0476
-7.000 -0.5472 0.06010 0.05583 -0.0132 1.0000 0.0493
-6.750 -0.5451 0.05378 0.04970 -0.0120 1.0000 0.0503
-6.500 -0.5348 0.05090 0.04690 -0.0111 0.9976 0.0513
-6.250 -0.5005 0.04734 0.04325 -0.0148 0.9844 0.0541
-6.000 -0.4752 0.04405 0.03929 -0.0158 0.9580 0.0610
-5.750 -0.4407 0.04011 0.03542 -0.0190 0.9357 0.0636
-4.750 -0.3148 0.02448 0.01729 -0.0172 0.8275 0.0318
-4.500 -0.2863 0.02167 0.01386 -0.0158 0.8041 0.0279
-4.250 -0.2594 0.02077 0.01260 -0.0147 0.7813 0.0270
-4.000 -0.2309 0.01939 0.01100 -0.0142 0.7606 0.0271
-3.750 -0.2024 0.01781 0.00936 -0.0140 0.7419 0.0281
-3.500 -0.1778 0.01698 0.00846 -0.0130 0.7242 0.0292
-3.250 -0.1547 0.01638 0.00775 -0.0118 0.7076 0.0319
-3.000 -0.1338 0.01573 0.00707 -0.0104 0.6921 0.0364
-2.750 -0.1144 0.01506 0.00636 -0.0085 0.6774 0.0441
-2.500 -0.0973 0.01424 0.00561 -0.0062 0.6639 0.0747
-2.250 -0.1092 0.01170 0.00487 0.0005 0.6542 0.4701
-2.000 -0.0972 0.01262 0.00706 0.0080 0.6425 0.8502
-1.750 0.0705 0.01664 0.01053 -0.0123 0.6189 0.9080
-1.500 0.1368 0.01719 0.01080 -0.0185 0.6035 0.9319
-1.250 0.1850 0.01718 0.01056 -0.0222 0.5906 0.9436
-1.000 0.2188 0.01694 0.01016 -0.0236 0.5788 0.9480
-0.750 0.2524 0.01673 0.00982 -0.0251 0.5674 0.9520
-0.500 0.2786 0.01670 0.00964 -0.0250 0.5582 0.9568
-0.250 0.3065 0.01657 0.00941 -0.0254 0.5482 0.9609
0.000 0.3405 0.01634 0.00907 -0.0269 0.5383 0.9641
0.250 0.3697 0.01624 0.00884 -0.0275 0.5299 0.9676
0.500 0.3942 0.01626 0.00882 -0.0272 0.5214 0.9716
0.750 0.4250 0.01610 0.00853 -0.0282 0.5137 0.9743
1.000 0.4569 0.01592 0.00833 -0.0293 0.5049 0.9770
1.250 0.4854 0.01587 0.00817 -0.0298 0.4980 0.9797
1.500 0.5118 0.01586 0.00816 -0.0299 0.4905 0.9826
1.750 0.5391 0.01583 0.00805 -0.0302 0.4836 0.9849
2.000 0.5703 0.01570 0.00790 -0.0313 0.4763 0.9870
2.250 0.5996 0.01563 0.00780 -0.0319 0.4694 0.9891
2.500 0.6271 0.01565 0.00777 -0.0323 0.4633 0.9910
2.750 0.6545 0.01564 0.00778 -0.0326 0.4563 0.9931
3.000 0.6821 0.01567 0.00774 -0.0329 0.4507 0.9947
3.250 0.7107 0.01564 0.00777 -0.0335 0.4440 0.9962
3.500 0.7397 0.01562 0.00774 -0.0341 0.4378 0.9980
3.750 0.7672 0.01571 0.00779 -0.0345 0.4323 0.9994
4.000 0.7919 0.01577 0.00794 -0.0342 0.4258 1.0000
4.250 0.8144 0.01590 0.00804 -0.0335 0.4205 1.0000
4.500 0.8364 0.01607 0.00825 -0.0327 0.4149 1.0000
4.750 0.8583 0.01619 0.00843 -0.0319 0.4088 1.0000
5.000 0.8808 0.01636 0.00856 -0.0312 0.4038 1.0000
5.250 0.9021 0.01653 0.00885 -0.0303 0.3976 1.0000
5.500 0.9238 0.01667 0.00902 -0.0294 0.3918 1.0000
5.750 0.9460 0.01688 0.00921 -0.0286 0.3865 1.0000
6.000 0.9664 0.01702 0.00950 -0.0276 0.3798 1.0000
6.250 0.9881 0.01717 0.00964 -0.0267 0.3742 1.0000
6.500 1.0086 0.01738 0.00995 -0.0256 0.3679 1.0000
6.750 1.0291 0.01753 0.01017 -0.0246 0.3614 1.0000
7.000 1.0505 0.01774 0.01035 -0.0236 0.3558 1.0000
7.250 1.0692 0.01789 0.01069 -0.0223 0.3485 1.0000
7.500 1.0899 0.01804 0.01080 -0.0212 0.3422 1.0000
7.750 1.1079 0.01824 0.01118 -0.0197 0.3348 1.0000
8.000 1.1272 0.01837 0.01131 -0.0185 0.3280 1.0000
8.250 1.1445 0.01858 0.01168 -0.0169 0.3204 1.0000
8.500 1.1625 0.01872 0.01184 -0.0153 0.3131 1.0000
8.750 1.1783 0.01894 0.01220 -0.0135 0.3049 1.0000
9.000 1.1949 0.01910 0.01236 -0.0118 0.2973 1.0000
9.250 1.2084 0.01932 0.01276 -0.0096 0.2883 1.0000
9.500 1.2222 0.01954 0.01300 -0.0074 0.2800 1.0000
9.750 1.2335 0.01976 0.01335 -0.0048 0.2705 1.0000
10.000 1.2434 0.02004 0.01373 -0.0020 0.2611 1.0000
10.250 1.2512 0.02033 0.01403 0.0011 0.2519 1.0000
10.500 1.2559 0.02063 0.01446 0.0048 0.2416 1.0000
10.750 1.2574 0.02097 0.01488 0.0090 0.2318 1.0000
11.000 1.2534 0.02133 0.01522 0.0141 0.2233 1.0000
11.250 1.2456 0.02163 0.01562 0.0199 0.2142 1.0000
11.500 1.2363 0.02202 0.01602 0.0257 0.2059 1.0000
11.750 1.2301 0.02262 0.01657 0.0306 0.1966 1.0000
12.000 1.2296 0.02344 0.01745 0.0340 0.1847 1.0000
12.250 1.2291 0.02454 0.01859 0.0367 0.1729 1.0000
12.500 1.2272 0.02594 0.02001 0.0389 0.1614 1.0000
12.750 1.2238 0.02770 0.02178 0.0406 0.1507 1.0000
13.000 1.2180 0.02987 0.02393 0.0419 0.1412 1.0000
13.250 1.2137 0.03223 0.02634 0.0426 0.1314 1.0000
13.500 1.2087 0.03484 0.02901 0.0429 0.1226 1.0000
13.750 1.1995 0.03797 0.03209 0.0430 0.1155 1.0000
14.000 1.1941 0.04097 0.03519 0.0427 0.1076 1.0000
14.250 1.1856 0.04429 0.03851 0.0424 0.1017 1.0000
14.500 1.1780 0.04773 0.04203 0.0418 0.0950 1.0000
14.750 1.1693 0.05124 0.04552 0.0412 0.0898 1.0000
15.000 1.1622 0.05481 0.04920 0.0403 0.0842 1.0000
15.250 1.1539 0.05838 0.05269 0.0397 0.0796 1.0000
15.500 1.1483 0.06210 0.05658 0.0385 0.0748 1.0000
15.750 1.1408 0.06595 0.06040 0.0373 0.0704 1.0000
16.000 1.1359 0.06959 0.06413 0.0362 0.0662 1.0000
16.250 1.1304 0.07352 0.06813 0.0348 0.0623 1.0000
16.500 1.1276 0.07674 0.07127 0.0340 0.0584 1.0000
16.750 1.1226 0.08085 0.07555 0.0324 0.0553 1.0000
17.000 1.1180 0.08484 0.07960 0.0308 0.0523 1.0000
17.250 1.1182 0.08776 0.08245 0.0301 0.0490 1.0000
17.500 1.1131 0.09210 0.08697 0.0282 0.0467 1.0000
17.750 1.1096 0.09615 0.09110 0.0264 0.0443 1.0000
18.000 1.1117 0.09890 0.09377 0.0255 0.0417 1.0000
18.250 1.1070 0.10327 0.09830 0.0236 0.0399 1.0000
18.500 1.1019 0.10781 0.10299 0.0215 0.0382 1.0000
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