EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 50,000 Max Cl/Cd: 36.55 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e852-il-50000.txt Download as CSV file: xf-e852-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E852 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4054 0.10973 0.10298 -0.0287 1.0000 0.2591
-8.750 -0.4204 0.10874 0.10214 -0.0285 1.0000 0.2696
-8.500 -0.4181 0.10585 0.09930 -0.0272 1.0000 0.2824
-8.250 -0.4128 0.10258 0.09610 -0.0258 1.0000 0.2954
-8.000 -0.4092 0.09957 0.09316 -0.0243 1.0000 0.3084
-7.750 -0.4053 0.09652 0.09018 -0.0227 1.0000 0.3211
-7.500 -0.4006 0.09332 0.08705 -0.0210 1.0000 0.3319
-7.250 -0.4030 0.09072 0.08455 -0.0192 1.0000 0.3419
-7.000 -0.4100 0.08854 0.08250 -0.0169 1.0000 0.3535
-6.750 -0.4236 0.08704 0.08114 -0.0138 1.0000 0.3650
-6.500 -0.4249 0.08454 0.07873 -0.0108 1.0000 0.3794
-5.750 -0.5236 0.05772 0.05131 -0.0474 1.0000 0.1333
-5.500 -0.5086 0.05177 0.04493 -0.0495 1.0000 0.1151
-5.250 -0.4886 0.04655 0.03903 -0.0513 1.0000 0.1030
-5.000 -0.4630 0.04209 0.03349 -0.0528 1.0000 0.0943
-4.750 -0.4397 0.03851 0.02951 -0.0529 1.0000 0.0925
-4.500 -0.4132 0.03536 0.02579 -0.0528 1.0000 0.0927
-4.250 -0.3891 0.03295 0.02312 -0.0526 1.0000 0.1030
-4.000 -0.3630 0.03058 0.02040 -0.0520 1.0000 0.1128
-3.750 -0.3377 0.02847 0.01810 -0.0506 1.0000 0.1244
-3.500 -0.3149 0.02666 0.01642 -0.0496 1.0000 0.1588
-3.250 -0.2894 0.02425 0.01443 -0.0488 1.0000 0.2193
-3.000 -0.2833 0.02283 0.01547 -0.0416 1.0000 0.6232
-2.750 -0.2848 0.02344 0.01612 -0.0330 1.0000 0.7010
-2.500 -0.2855 0.02365 0.01631 -0.0253 1.0000 0.7547
-2.250 -0.2861 0.02357 0.01617 -0.0178 1.0000 0.8003
-2.000 -0.2870 0.02329 0.01571 -0.0108 1.0000 0.8478
-1.750 -0.2861 0.02283 0.01522 -0.0038 1.0000 0.9022
-1.500 -0.2016 0.02315 0.01497 -0.0135 1.0000 0.9789
-1.250 -0.1669 0.02273 0.01424 -0.0181 1.0000 1.0000
-1.000 -0.1603 0.02211 0.01345 -0.0177 1.0000 1.0000
-0.750 -0.1360 0.02196 0.01301 -0.0202 1.0000 1.0000
-0.500 -0.1057 0.02207 0.01274 -0.0235 1.0000 1.0000
-0.250 -0.0747 0.02234 0.01271 -0.0264 1.0000 1.0000
0.000 -0.0451 0.02269 0.01280 -0.0289 1.0000 1.0000
0.250 -0.0172 0.02311 0.01297 -0.0307 1.0000 1.0000
0.500 0.0091 0.02356 0.01321 -0.0320 1.0000 1.0000
0.750 0.0339 0.02406 0.01348 -0.0330 1.0000 1.0000
1.000 0.0579 0.02459 0.01385 -0.0338 1.0000 1.0000
1.250 0.0810 0.02515 0.01428 -0.0344 1.0000 1.0000
1.500 0.1035 0.02574 0.01477 -0.0348 1.0000 1.0000
1.750 0.1255 0.02637 0.01532 -0.0352 1.0000 1.0000
2.000 0.1469 0.02704 0.01593 -0.0355 1.0000 1.0000
2.250 0.1679 0.02774 0.01658 -0.0358 1.0000 1.0000
2.500 0.1885 0.02848 0.01729 -0.0360 1.0000 1.0000
2.750 0.2086 0.02926 0.01807 -0.0362 1.0000 1.0000
3.000 0.2284 0.03009 0.01890 -0.0363 1.0000 1.0000
3.250 0.2476 0.03096 0.01981 -0.0365 1.0000 1.0000
3.500 0.2664 0.03189 0.02082 -0.0367 1.0000 1.0000
3.750 0.2848 0.03288 0.02186 -0.0369 1.0000 1.0000
4.000 0.3027 0.03394 0.02299 -0.0371 1.0000 1.0000
4.250 0.3464 0.03591 0.02512 -0.0424 0.9851 1.0000
4.500 0.3977 0.03788 0.02731 -0.0487 0.9621 1.0000
4.750 0.4456 0.03955 0.02930 -0.0539 0.9391 1.0000
5.000 0.4940 0.04103 0.03106 -0.0588 0.9147 1.0000
5.250 0.5412 0.04221 0.03257 -0.0629 0.8881 1.0000
5.500 0.5885 0.04303 0.03377 -0.0663 0.8580 1.0000
5.750 0.6528 0.04298 0.03438 -0.0706 0.8211 1.0000
6.000 0.7467 0.03968 0.03196 -0.0744 0.7671 1.0000
6.250 0.8830 0.02416 0.01630 -0.0623 0.3800 1.0000
6.500 0.8697 0.02798 0.01831 -0.0560 0.2373 1.0000
6.750 0.9055 0.03206 0.02170 -0.0560 0.1519 1.0000
7.000 0.9663 0.03677 0.02616 -0.0593 0.1077 1.0000
7.250 0.9960 0.04044 0.02995 -0.0592 0.0883 1.0000
7.500 1.0256 0.04453 0.03458 -0.0582 0.0830 1.0000
7.750 1.0513 0.04921 0.03942 -0.0576 0.0792 1.0000
8.000 1.0614 0.05299 0.04381 -0.0548 0.0766 1.0000
8.250 1.0673 0.05655 0.04799 -0.0516 0.0748 1.0000
8.500 1.0705 0.06048 0.05242 -0.0487 0.0740 1.0000
8.750 1.0720 0.06480 0.05715 -0.0460 0.0750 1.0000
9.000 1.0748 0.06973 0.06234 -0.0439 0.0769 1.0000
9.250 1.0672 0.07378 0.06688 -0.0408 0.0806 1.0000
9.500 1.0416 0.07795 0.07151 -0.0373 0.0842 1.0000
9.750 1.0243 0.08227 0.07602 -0.0348 0.0869 1.0000
10.000 1.0244 0.08770 0.08157 -0.0339 0.0926 1.0000
10.250 0.9878 0.09147 0.08554 -0.0326 0.0937 1.0000
10.500 0.9494 0.09718 0.09139 -0.0346 0.0964 1.0000
10.750 0.9259 0.10511 0.09941 -0.0387 0.1074 1.0000
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Polar data table (+)
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