EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e545-il-1000000.txt Download as CSV file: xf-e545-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 545 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
------ -------- --------- --------- -------- -------- --------
-18.250 -0.4822 0.19745 0.19560 -0.0156 1.0000 0.0079
-18.000 -0.4766 0.19335 0.19151 -0.0174 1.0000 0.0082
-11.250 -0.7393 0.03212 0.02811 -0.0722 0.9931 0.0062
-11.000 -0.7277 0.02890 0.02465 -0.0725 0.9870 0.0059
-10.750 -0.7136 0.02628 0.02179 -0.0719 0.9750 0.0055
-10.500 -0.6924 0.02393 0.01916 -0.0717 0.9632 0.0052
-10.250 -0.6592 0.02238 0.01746 -0.0743 0.9552 0.0050
-10.000 -0.6193 0.02092 0.01587 -0.0784 0.9465 0.0050
-9.500 -0.5209 0.01837 0.01311 -0.0910 0.9274 0.0049
-9.250 -0.4802 0.01725 0.01184 -0.0957 0.9059 0.0050
-9.000 -0.4618 0.01647 0.01090 -0.0955 0.8797 0.0051
-8.750 -0.4480 0.01592 0.01023 -0.0940 0.8589 0.0051
-8.500 -0.4369 0.01533 0.00953 -0.0920 0.8420 0.0052
-8.250 -0.4256 0.01478 0.00890 -0.0899 0.8275 0.0052
-7.750 -0.4084 0.01360 0.00755 -0.0848 0.8021 0.0055
-7.500 -0.4023 0.01316 0.00703 -0.0815 0.7909 0.0056
-7.250 -0.3912 0.01282 0.00661 -0.0789 0.7801 0.0058
-7.000 -0.3757 0.01245 0.00617 -0.0771 0.7708 0.0061
-6.500 -0.3417 0.01173 0.00531 -0.0739 0.7510 0.0079
-6.250 -0.3242 0.01131 0.00487 -0.0724 0.7422 0.0129
-6.000 -0.3056 0.01088 0.00449 -0.0712 0.7345 0.0265
-5.750 -0.2851 0.01051 0.00418 -0.0702 0.7268 0.0438
-5.500 -0.2643 0.01016 0.00389 -0.0694 0.7195 0.0662
-5.250 -0.2428 0.00973 0.00359 -0.0687 0.7124 0.0983
-5.000 -0.2218 0.00929 0.00329 -0.0679 0.7049 0.1413
-4.750 -0.2028 0.00856 0.00289 -0.0671 0.6986 0.2275
-4.500 -0.1868 0.00734 0.00228 -0.0661 0.6917 0.3871
-4.250 -0.1670 0.00649 0.00199 -0.0654 0.6847 0.5485
-4.000 -0.1384 0.00652 0.00200 -0.0656 0.6781 0.5729
-3.750 -0.1102 0.00660 0.00205 -0.0657 0.6713 0.5864
-3.500 -0.0819 0.00667 0.00205 -0.0659 0.6649 0.5940
-3.250 -0.0530 0.00673 0.00210 -0.0661 0.6594 0.6002
-3.000 -0.0243 0.00687 0.00216 -0.0663 0.6535 0.6069
-2.750 0.0036 0.00698 0.00225 -0.0663 0.6475 0.6146
-2.500 0.0326 0.00719 0.00245 -0.0665 0.6422 0.6225
-2.250 0.0614 0.00731 0.00251 -0.0668 0.6364 0.6255
-2.000 0.0894 0.00729 0.00242 -0.0670 0.6308 0.6268
-1.750 0.1182 0.00722 0.00233 -0.0673 0.6261 0.6282
-1.500 0.1469 0.00720 0.00227 -0.0677 0.6207 0.6294
-1.250 0.1751 0.00721 0.00224 -0.0679 0.6151 0.6306
-1.000 0.2035 0.00723 0.00222 -0.0681 0.6100 0.6318
-0.750 0.2323 0.00722 0.00221 -0.0685 0.6050 0.6328
-0.500 0.2607 0.00724 0.00219 -0.0687 0.5996 0.6338
-0.250 0.2886 0.00729 0.00218 -0.0689 0.5942 0.6349
0.000 0.3175 0.00728 0.00218 -0.0693 0.5900 0.6359
0.250 0.3461 0.00730 0.00218 -0.0696 0.5852 0.6370
0.500 0.3741 0.00734 0.00218 -0.0698 0.5797 0.6381
0.750 0.4022 0.00738 0.00219 -0.0700 0.5746 0.6393
1.000 0.4310 0.00740 0.00221 -0.0703 0.5700 0.6405
1.250 0.4591 0.00743 0.00222 -0.0706 0.5645 0.6415
1.500 0.4865 0.00751 0.00224 -0.0706 0.5580 0.6424
1.750 0.5150 0.00752 0.00226 -0.0710 0.5513 0.6432
2.000 0.5425 0.00759 0.00229 -0.0711 0.5440 0.6438
2.250 0.5702 0.00759 0.00229 -0.0712 0.5391 0.6455
2.500 0.5985 0.00759 0.00231 -0.0715 0.5341 0.6470
2.750 0.6260 0.00762 0.00235 -0.0716 0.5282 0.6483
3.000 0.6531 0.00769 0.00241 -0.0717 0.5227 0.6495
3.250 0.6813 0.00772 0.00247 -0.0719 0.5176 0.6508
3.500 0.7086 0.00778 0.00253 -0.0720 0.5108 0.6520
3.750 0.7354 0.00786 0.00260 -0.0720 0.5040 0.6533
4.000 0.7629 0.00792 0.00268 -0.0721 0.4965 0.6547
4.250 0.7891 0.00803 0.00277 -0.0719 0.4886 0.6562
4.500 0.8166 0.00809 0.00285 -0.0721 0.4816 0.6577
4.750 0.8425 0.00821 0.00295 -0.0719 0.4723 0.6590
5.000 0.8691 0.00830 0.00305 -0.0719 0.4628 0.6602
5.250 0.8944 0.00844 0.00317 -0.0716 0.4508 0.6612
5.500 0.9186 0.00863 0.00331 -0.0711 0.4331 0.6621
5.750 0.9401 0.00888 0.00347 -0.0701 0.4058 0.6641
6.000 0.9596 0.00924 0.00370 -0.0689 0.3732 0.6661
6.250 0.9765 0.00971 0.00402 -0.0671 0.3359 0.6678
6.500 0.9922 0.01022 0.00437 -0.0652 0.2987 0.6695
6.750 1.0083 0.01070 0.00472 -0.0633 0.2700 0.6711
7.000 1.0251 0.01111 0.00504 -0.0615 0.2456 0.6728
7.250 1.0399 0.01148 0.00533 -0.0594 0.2280 0.6745
7.500 1.0557 0.01179 0.00561 -0.0574 0.2172 0.6763
7.750 1.0718 0.01212 0.00592 -0.0554 0.2093 0.6780
8.000 1.0894 0.01242 0.00623 -0.0538 0.2023 0.6796
8.250 1.1056 0.01278 0.00658 -0.0520 0.1955 0.6814
8.500 1.1230 0.01306 0.00690 -0.0505 0.1897 0.6842
8.750 1.1415 0.01333 0.00721 -0.0491 0.1830 0.6865
9.000 1.1569 0.01370 0.00760 -0.0473 0.1733 0.6888
9.250 1.1638 0.01441 0.00813 -0.0442 0.1371 0.6911
9.500 1.1681 0.01523 0.00886 -0.0409 0.1213 0.6934
9.750 1.1766 0.01594 0.00956 -0.0383 0.1129 0.6957
10.000 1.1871 0.01660 0.01023 -0.0361 0.1051 0.6978
10.250 1.1971 0.01731 0.01093 -0.0340 0.0955 0.7000
10.500 1.2051 0.01813 0.01174 -0.0317 0.0845 0.7034
10.750 1.2110 0.01911 0.01268 -0.0293 0.0728 0.7064
11.000 1.2177 0.02012 0.01367 -0.0272 0.0634 0.7095
11.250 1.2249 0.02117 0.01470 -0.0252 0.0560 0.7126
11.500 1.2322 0.02226 0.01580 -0.0234 0.0495 0.7157
11.750 1.2392 0.02341 0.01695 -0.0217 0.0437 0.7191
12.000 1.2462 0.02460 0.01817 -0.0201 0.0386 0.7234
12.250 1.2524 0.02590 0.01949 -0.0186 0.0337 0.7276
12.500 1.2591 0.02723 0.02084 -0.0172 0.0300 0.7320
12.750 1.2651 0.02866 0.02228 -0.0159 0.0262 0.7359
13.000 1.2714 0.03008 0.02377 -0.0147 0.0236 0.7413
13.250 1.2782 0.03153 0.02526 -0.0137 0.0214 0.7468
13.500 1.2843 0.03309 0.02687 -0.0127 0.0192 0.7526
13.750 1.2899 0.03471 0.02856 -0.0117 0.0174 0.7594
14.000 1.2960 0.03635 0.03027 -0.0109 0.0158 0.7672
14.250 1.3012 0.03811 0.03211 -0.0102 0.0144 0.7759
14.500 1.3056 0.03999 0.03406 -0.0095 0.0130 0.7866
14.750 1.3109 0.04182 0.03599 -0.0090 0.0118 0.7998
15.000 1.3132 0.04396 0.03823 -0.0084 0.0105 0.8172
15.250 1.3175 0.04585 0.04028 -0.0078 0.0095 0.8457
15.500 1.3223 0.04804 0.04280 -0.0081 0.0084 1.0000
15.750 1.3271 0.05026 0.04507 -0.0080 0.0075 1.0000
16.000 1.3269 0.05306 0.04792 -0.0080 0.0065 1.0000
16.250 1.3300 0.05556 0.05049 -0.0081 0.0060 1.0000
16.500 1.3297 0.05850 0.05349 -0.0084 0.0054 1.0000
16.750 1.3289 0.06160 0.05666 -0.0088 0.0050 1.0000
17.000 1.3302 0.06453 0.05967 -0.0092 0.0046 1.0000
17.250 1.3310 0.06756 0.06277 -0.0098 0.0044 1.0000
17.500 1.3263 0.07141 0.06669 -0.0106 0.0039 1.0000
17.750 1.3214 0.07538 0.07076 -0.0116 0.0036 1.0000
18.000 1.3192 0.07909 0.07455 -0.0127 0.0036 1.0000
18.250 1.3194 0.08251 0.07807 -0.0138 0.0034 1.0000
18.500 1.3171 0.08639 0.08203 -0.0152 0.0032 1.0000
18.750 1.3123 0.09073 0.08648 -0.0167 0.0031 1.0000
19.000 1.3080 0.09509 0.09093 -0.0185 0.0030 1.0000
19.250 1.3030 0.09960 0.09552 -0.0203 0.0028 1.0000
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Polar data table (+)
Polar graphs
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