EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 200,000 Max Cl/Cd: 60.33 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1210-il-200000.txt Download as CSV file: xf-e1210-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1210 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1955 0.10792 0.10463 -0.0340 1.0000 0.0743
-9.750 -0.1878 0.10564 0.10241 -0.0337 1.0000 0.0760
-9.500 -0.5009 0.03527 0.03094 -0.0931 0.9543 0.0554
-9.000 -0.3437 0.05300 0.04981 -0.0793 0.9377 0.0607
-8.750 -0.3805 0.03061 0.02577 -0.1050 0.8962 0.0648
-8.500 -0.3499 0.02887 0.02370 -0.1071 0.8700 0.0679
-8.250 -0.3207 0.02864 0.02335 -0.1073 0.8447 0.0708
-8.000 -0.3036 0.02696 0.02123 -0.1067 0.8214 0.0741
-7.750 -0.2759 0.02755 0.02189 -0.1059 0.8005 0.0765
-7.500 -0.2601 0.02557 0.01928 -0.1051 0.7828 0.0807
-7.250 -0.2332 0.02596 0.01982 -0.1043 0.7647 0.0829
-7.000 -0.2107 0.02528 0.01890 -0.1035 0.7483 0.0865
-6.750 -0.1888 0.02426 0.01760 -0.1028 0.7336 0.0898
-6.500 -0.1628 0.02430 0.01761 -0.1021 0.7197 0.0926
-6.250 -0.1405 0.02320 0.01604 -0.1014 0.7056 0.0969
-6.000 -0.1153 0.02272 0.01558 -0.1008 0.6927 0.0996
-5.750 -0.0895 0.02243 0.01519 -0.1002 0.6802 0.1029
-5.500 -0.0651 0.02163 0.01399 -0.0995 0.6679 0.1072
-5.250 -0.0391 0.02119 0.01353 -0.0990 0.6570 0.1102
-5.000 -0.0131 0.02084 0.01313 -0.0985 0.6447 0.1140
-4.750 0.0130 0.02032 0.01223 -0.0979 0.6347 0.1182
-4.500 0.0390 0.01978 0.01177 -0.0975 0.6233 0.1217
-4.250 0.0658 0.01954 0.01138 -0.0969 0.6135 0.1259
-4.000 0.0927 0.01925 0.01084 -0.0964 0.6027 0.1301
-3.750 0.1190 0.01865 0.01024 -0.0960 0.5938 0.1342
-3.500 0.1459 0.01839 0.00993 -0.0955 0.5834 0.1388
-3.250 0.1734 0.01826 0.00952 -0.0950 0.5748 0.1434
-3.000 0.1997 0.01767 0.00902 -0.0946 0.5649 0.1480
-2.750 0.2270 0.01751 0.00875 -0.0942 0.5567 0.1532
-2.500 0.2544 0.01738 0.00850 -0.0937 0.5477 0.1583
-2.250 0.2811 0.01693 0.00805 -0.0933 0.5392 0.1637
-2.000 0.3084 0.01681 0.00788 -0.0929 0.5310 0.1698
-1.750 0.3357 0.01669 0.00765 -0.0925 0.5224 0.1756
-1.500 0.3628 0.01643 0.00737 -0.0921 0.5155 0.1824
-1.250 0.3898 0.01630 0.00726 -0.0916 0.5070 0.1898
-1.000 0.4167 0.01608 0.00701 -0.0912 0.4995 0.1976
-0.750 0.4439 0.01604 0.00694 -0.0908 0.4923 0.2067
-0.500 0.4706 0.01586 0.00681 -0.0904 0.4845 0.2167
-0.250 0.4980 0.01584 0.00672 -0.0900 0.4781 0.2290
0.000 0.5245 0.01573 0.00670 -0.0896 0.4709 0.2440
0.250 0.5512 0.01560 0.00665 -0.0891 0.4638 0.2643
0.500 0.5783 0.01555 0.00661 -0.0888 0.4577 0.2957
0.750 0.6039 0.01533 0.00671 -0.0883 0.4511 0.3555
1.000 0.6281 0.01494 0.00682 -0.0876 0.4447 0.4925
1.250 0.6475 0.01444 0.00698 -0.0854 0.4395 0.7127
1.500 0.6906 0.01411 0.00707 -0.0874 0.4321 1.0000
1.750 0.7169 0.01430 0.00712 -0.0869 0.4260 1.0000
2.000 0.7439 0.01456 0.00719 -0.0865 0.4208 1.0000
2.250 0.7698 0.01481 0.00738 -0.0860 0.4151 1.0000
2.500 0.7958 0.01501 0.00752 -0.0855 0.4091 1.0000
2.750 0.8225 0.01524 0.00761 -0.0851 0.4041 1.0000
3.000 0.8492 0.01558 0.00783 -0.0848 0.3992 1.0000
3.250 0.8746 0.01582 0.00807 -0.0842 0.3939 1.0000
3.500 0.9008 0.01605 0.00823 -0.0838 0.3888 1.0000
3.750 0.9277 0.01635 0.00839 -0.0835 0.3842 1.0000
4.000 0.9532 0.01668 0.00870 -0.0830 0.3794 1.0000
4.250 0.9784 0.01694 0.00896 -0.0824 0.3744 1.0000
4.500 1.0045 0.01722 0.00917 -0.0820 0.3701 1.0000
4.750 1.0314 0.01758 0.00940 -0.0818 0.3661 1.0000
5.000 1.0563 0.01796 0.00979 -0.0813 0.3618 1.0000
5.250 1.0807 0.01825 0.01011 -0.0806 0.3571 1.0000
5.500 1.1061 0.01853 0.01035 -0.0801 0.3528 1.0000
5.750 1.1326 0.01889 0.01060 -0.0799 0.3490 1.0000
6.000 1.1579 0.01937 0.01106 -0.0795 0.3453 1.0000
6.250 1.1809 0.01973 0.01150 -0.0787 0.3413 1.0000
6.500 1.2052 0.02007 0.01184 -0.0781 0.3372 1.0000
6.750 1.2307 0.02040 0.01211 -0.0777 0.3336 1.0000
7.000 1.2582 0.02094 0.01252 -0.0777 0.3300 1.0000
7.250 1.2789 0.02135 0.01306 -0.0766 0.3264 1.0000
7.500 1.3011 0.02178 0.01355 -0.0758 0.3226 1.0000
7.750 1.3248 0.02218 0.01396 -0.0752 0.3192 1.0000
8.000 1.3500 0.02258 0.01430 -0.0748 0.3161 1.0000
8.250 1.3779 0.02323 0.01483 -0.0750 0.3128 1.0000
8.500 1.3951 0.02370 0.01548 -0.0735 0.3095 1.0000
8.750 1.4149 0.02419 0.01606 -0.0724 0.3059 1.0000
9.000 1.4369 0.02465 0.01654 -0.0716 0.3027 1.0000
9.250 1.4610 0.02510 0.01696 -0.0712 0.2999 1.0000
9.500 1.4880 0.02569 0.01747 -0.0713 0.2971 1.0000
9.750 1.5059 0.02643 0.01831 -0.0701 0.2943 1.0000
10.000 1.5207 0.02707 0.01910 -0.0684 0.2911 1.0000
10.250 1.5382 0.02764 0.01975 -0.0671 0.2880 1.0000
10.500 1.5588 0.02815 0.02027 -0.0662 0.2852 1.0000
10.750 1.5829 0.02866 0.02075 -0.0659 0.2827 1.0000
11.000 1.6123 0.02948 0.02147 -0.0665 0.2800 1.0000
11.250 1.6190 0.03031 0.02252 -0.0639 0.2777 1.0000
11.500 1.6260 0.03116 0.02354 -0.0614 0.2749 1.0000
11.750 1.6363 0.03191 0.02438 -0.0593 0.2721 1.0000
12.000 1.6504 0.03256 0.02508 -0.0577 0.2697 1.0000
12.250 1.6716 0.03309 0.02559 -0.0570 0.2674 1.0000
12.500 1.7052 0.03372 0.02612 -0.0582 0.2647 1.0000
12.750 1.7035 0.03487 0.02744 -0.0548 0.2626 1.0000
13.000 1.6933 0.03624 0.02901 -0.0506 0.2604 1.0000
13.250 1.6874 0.03768 0.03061 -0.0476 0.2580 1.0000
13.500 1.6890 0.03895 0.03198 -0.0455 0.2555 1.0000
13.750 1.7019 0.03976 0.03282 -0.0444 0.2532 1.0000
14.000 1.7305 0.04001 0.03300 -0.0446 0.2508 1.0000
14.250 1.7532 0.04093 0.03391 -0.0445 0.2483 1.0000
14.500 1.7226 0.04388 0.03713 -0.0409 0.2463 1.0000
14.750 1.6912 0.04765 0.04115 -0.0386 0.2439 1.0000
15.000 1.6674 0.05145 0.04514 -0.0374 0.2412 1.0000
15.250 1.6657 0.05370 0.04747 -0.0369 0.2387 1.0000
15.500 1.6995 0.05300 0.04670 -0.0366 0.2365 1.0000
15.750 1.7562 0.05111 0.04464 -0.0369 0.2338 1.0000
16.000 1.6423 0.06335 0.05740 -0.0367 0.2313 1.0000
17.000 1.6011 0.07899 0.07339 -0.0396 0.2199 1.0000
17.250 0.7813 0.19737 0.19343 -0.0991 0.1721 1.0000
17.500 0.7959 0.19848 0.19456 -0.0991 0.1691 1.0000
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