EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.47 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e549-il-1000000.txt Download as CSV file: xf-e549-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 549 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5749 0.11793 0.11602 -0.0451 1.0000 0.0061
-16.000 -0.5870 0.11035 0.10841 -0.0489 1.0000 0.0062
-15.750 -0.6141 0.09913 0.09706 -0.0552 1.0000 0.0062
-15.500 -0.6196 0.09372 0.09163 -0.0582 1.0000 0.0064
-15.250 -0.6727 0.07918 0.07673 -0.0659 1.0000 0.0056
-15.000 -0.6889 0.07297 0.07040 -0.0690 1.0000 0.0055
-14.750 -0.7117 0.06637 0.06364 -0.0718 1.0000 0.0055
-14.500 -0.7321 0.06068 0.05779 -0.0737 1.0000 0.0054
-14.250 -0.7511 0.05563 0.05256 -0.0749 1.0000 0.0053
-14.000 -0.7643 0.05164 0.04842 -0.0753 1.0000 0.0053
-13.750 -0.7772 0.04793 0.04455 -0.0753 1.0000 0.0052
-13.500 -0.7927 0.04405 0.04046 -0.0747 1.0000 0.0051
-13.250 -0.8002 0.04115 0.03740 -0.0738 1.0000 0.0051
-13.000 -0.8015 0.03902 0.03517 -0.0729 1.0000 0.0050
-12.750 -0.8071 0.03644 0.03241 -0.0714 1.0000 0.0050
-12.500 -0.8089 0.03435 0.03018 -0.0697 1.0000 0.0049
-12.250 -0.8097 0.03247 0.02817 -0.0678 1.0000 0.0049
-12.000 -0.8024 0.03093 0.02654 -0.0670 0.9997 0.0049
-11.750 -0.7785 0.02892 0.02439 -0.0695 0.9974 0.0048
-11.500 -0.7559 0.02716 0.02252 -0.0713 0.9914 0.0049
-11.250 -0.7390 0.02567 0.02095 -0.0717 0.9726 0.0049
-11.000 -0.7073 0.02409 0.01927 -0.0751 0.9591 0.0049
-10.750 -0.6660 0.02256 0.01763 -0.0804 0.9492 0.0049
-10.500 -0.6148 0.02100 0.01595 -0.0878 0.9402 0.0051
-10.250 -0.5628 0.01967 0.01450 -0.0952 0.9220 0.0051
-10.000 -0.5328 0.01873 0.01337 -0.0978 0.8932 0.0053
-9.750 -0.5213 0.01791 0.01239 -0.0964 0.8677 0.0055
-9.250 -0.5011 0.01651 0.01075 -0.0928 0.8324 0.0056
-9.000 -0.4887 0.01594 0.01010 -0.0911 0.8188 0.0058
-8.750 -0.4901 0.01483 0.00888 -0.0877 0.8051 0.0063
-8.500 -0.4842 0.01423 0.00820 -0.0848 0.7933 0.0065
-8.250 -0.4755 0.01387 0.00777 -0.0819 0.7825 0.0072
-8.000 -0.4607 0.01348 0.00730 -0.0801 0.7725 0.0075
-7.750 -0.4432 0.01312 0.00688 -0.0787 0.7638 0.0079
-7.500 -0.4276 0.01266 0.00635 -0.0770 0.7550 0.0088
-7.250 -0.4075 0.01232 0.00598 -0.0760 0.7468 0.0103
-7.000 -0.3887 0.01193 0.00554 -0.0748 0.7385 0.0127
-6.750 -0.3682 0.01154 0.00514 -0.0738 0.7306 0.0180
-6.500 -0.3473 0.01120 0.00480 -0.0730 0.7228 0.0270
-6.250 -0.3253 0.01083 0.00449 -0.0723 0.7154 0.0392
-6.000 -0.3031 0.01050 0.00420 -0.0717 0.7081 0.0552
-5.750 -0.2801 0.01013 0.00391 -0.0712 0.7012 0.0778
-5.500 -0.2585 0.00968 0.00359 -0.0705 0.6939 0.1169
-5.250 -0.2373 0.00908 0.00323 -0.0699 0.6871 0.1772
-5.000 -0.2200 0.00803 0.00267 -0.0690 0.6800 0.3026
-4.750 -0.2026 0.00685 0.00215 -0.0681 0.6738 0.4793
-4.500 -0.1750 0.00678 0.00214 -0.0682 0.6670 0.5171
-4.250 -0.1469 0.00682 0.00214 -0.0683 0.6605 0.5329
-4.000 -0.1179 0.00684 0.00210 -0.0686 0.6539 0.5412
-3.750 -0.0896 0.00689 0.00210 -0.0687 0.6472 0.5482
-3.500 -0.0606 0.00696 0.00209 -0.0690 0.6411 0.5549
-3.250 -0.0323 0.00699 0.00210 -0.0692 0.6345 0.5606
-3.000 -0.0037 0.00711 0.00215 -0.0693 0.6282 0.5675
-2.750 0.0248 0.00720 0.00224 -0.0695 0.6214 0.5761
-2.500 0.0530 0.00736 0.00233 -0.0695 0.6147 0.5826
-2.250 0.0821 0.00737 0.00230 -0.0699 0.6090 0.5841
-2.000 0.1107 0.00740 0.00226 -0.0701 0.6033 0.5851
-1.750 0.1389 0.00737 0.00218 -0.0703 0.5978 0.5869
-1.500 0.1677 0.00734 0.00214 -0.0707 0.5920 0.5883
-1.250 0.1961 0.00735 0.00211 -0.0709 0.5863 0.5895
-1.000 0.2246 0.00737 0.00210 -0.0711 0.5812 0.5908
-0.750 0.2533 0.00738 0.00209 -0.0714 0.5759 0.5922
-0.500 0.2816 0.00742 0.00209 -0.0716 0.5706 0.5936
-0.250 0.3101 0.00745 0.00209 -0.0719 0.5658 0.5950
0.000 0.3388 0.00747 0.00209 -0.0722 0.5610 0.5964
0.250 0.3670 0.00751 0.00209 -0.0724 0.5560 0.5976
0.500 0.3953 0.00756 0.00211 -0.0726 0.5513 0.5989
0.750 0.4241 0.00758 0.00212 -0.0729 0.5467 0.6000
1.500 0.5086 0.00766 0.00217 -0.0735 0.5338 0.6046
1.750 0.5369 0.00769 0.00221 -0.0738 0.5296 0.6061
2.000 0.5648 0.00774 0.00226 -0.0739 0.5253 0.6075
2.250 0.5925 0.00781 0.00231 -0.0741 0.5210 0.6090
2.500 0.6210 0.00784 0.00236 -0.0744 0.5168 0.6106
2.750 0.6489 0.00789 0.00241 -0.0745 0.5125 0.6121
3.000 0.6764 0.00798 0.00248 -0.0746 0.5083 0.6136
3.250 0.7043 0.00804 0.00255 -0.0748 0.5047 0.6151
3.500 0.7325 0.00809 0.00261 -0.0750 0.5004 0.6163
3.750 0.7598 0.00814 0.00267 -0.0751 0.4955 0.6183
4.000 0.7866 0.00821 0.00275 -0.0751 0.4904 0.6204
4.250 0.8145 0.00824 0.00283 -0.0753 0.4855 0.6224
4.500 0.8414 0.00832 0.00291 -0.0753 0.4798 0.6242
4.750 0.8681 0.00841 0.00301 -0.0752 0.4739 0.6261
5.000 0.8953 0.00848 0.00310 -0.0753 0.4675 0.6280
5.250 0.9213 0.00860 0.00321 -0.0751 0.4617 0.6299
5.500 0.9485 0.00867 0.00331 -0.0752 0.4562 0.6316
5.750 0.9748 0.00876 0.00341 -0.0751 0.4497 0.6336
6.000 1.0005 0.00885 0.00353 -0.0749 0.4431 0.6361
6.250 1.0264 0.00895 0.00366 -0.0747 0.4349 0.6384
6.500 1.0516 0.00907 0.00380 -0.0744 0.4267 0.6408
6.750 1.0762 0.00922 0.00395 -0.0741 0.4171 0.6434
7.000 1.1007 0.00937 0.00411 -0.0737 0.4057 0.6459
7.250 1.1241 0.00957 0.00429 -0.0731 0.3932 0.6481
7.500 1.1459 0.00979 0.00449 -0.0722 0.3775 0.6511
7.750 1.1654 0.01009 0.00475 -0.0709 0.3574 0.6540
8.000 1.1825 0.01049 0.00506 -0.0692 0.3303 0.6569
8.250 1.1929 0.01103 0.00545 -0.0663 0.2982 0.6599
8.500 1.2029 0.01153 0.00585 -0.0633 0.2786 0.6629
8.750 1.2155 0.01198 0.00627 -0.0608 0.2652 0.6661
9.000 1.2295 0.01240 0.00668 -0.0587 0.2522 0.6697
9.250 1.2440 0.01281 0.00709 -0.0566 0.2373 0.6736
9.500 1.2537 0.01340 0.00759 -0.0539 0.2138 0.6775
9.750 1.2593 0.01416 0.00824 -0.0507 0.1923 0.6816
10.000 1.2654 0.01490 0.00893 -0.0477 0.1741 0.6863
10.250 1.2720 0.01568 0.00967 -0.0449 0.1589 0.6916
10.500 1.2763 0.01661 0.01054 -0.0419 0.1421 0.6967
10.750 1.2818 0.01753 0.01145 -0.0394 0.1289 0.7026
11.000 1.2875 0.01852 0.01242 -0.0370 0.1172 0.7090
11.250 1.2925 0.01960 0.01350 -0.0346 0.1061 0.7157
11.500 1.2961 0.02083 0.01471 -0.0324 0.0947 0.7236
11.750 1.3000 0.02211 0.01599 -0.0303 0.0851 0.7322
12.000 1.3023 0.02356 0.01743 -0.0282 0.0744 0.7422
12.250 1.3089 0.02480 0.01873 -0.0267 0.0686 0.7541
12.500 1.3110 0.02638 0.02033 -0.0249 0.0608 0.7680
12.750 1.3143 0.02793 0.02194 -0.0234 0.0539 0.7856
13.000 1.3173 0.02951 0.02361 -0.0219 0.0481 0.8103
13.250 1.3178 0.03112 0.02538 -0.0201 0.0433 0.8580
13.500 1.3277 0.03275 0.02725 -0.0203 0.0379 1.0000
13.750 1.3293 0.03483 0.02931 -0.0194 0.0332 1.0000
14.000 1.3351 0.03661 0.03112 -0.0187 0.0307 1.0000
14.250 1.3375 0.03875 0.03327 -0.0181 0.0276 1.0000
14.500 1.3420 0.04077 0.03533 -0.0176 0.0251 1.0000
14.750 1.3449 0.04297 0.03755 -0.0171 0.0228 1.0000
15.000 1.3479 0.04524 0.03985 -0.0168 0.0207 1.0000
15.250 1.3522 0.04743 0.04209 -0.0166 0.0191 1.0000
15.500 1.3538 0.04996 0.04464 -0.0164 0.0173 1.0000
15.750 1.3567 0.05240 0.04714 -0.0164 0.0161 1.0000
16.000 1.3595 0.05489 0.04967 -0.0165 0.0147 1.0000
16.250 1.3608 0.05760 0.05243 -0.0166 0.0136 1.0000
16.500 1.3627 0.06033 0.05521 -0.0168 0.0125 1.0000
16.750 1.3651 0.06305 0.05798 -0.0172 0.0116 1.0000
17.000 1.3653 0.06606 0.06105 -0.0176 0.0107 1.0000
17.250 1.3643 0.06930 0.06434 -0.0181 0.0098 1.0000
17.500 1.3664 0.07223 0.06734 -0.0188 0.0092 1.0000
17.750 1.3667 0.07542 0.07060 -0.0195 0.0086 1.0000
18.000 1.3652 0.07888 0.07411 -0.0203 0.0079 1.0000
18.250 1.3627 0.08258 0.07788 -0.0213 0.0073 1.0000
18.500 1.3624 0.08603 0.08141 -0.0224 0.0070 1.0000
18.750 1.3620 0.08953 0.08496 -0.0235 0.0062 1.0000
19.000 1.3588 0.09351 0.08902 -0.0248 0.0060 1.0000
19.250 1.3506 0.09830 0.09390 -0.0265 0.0055 1.0000
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Polar data table (+)
Polar graphs
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