EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 500,000 Max Cl/Cd: 94.93 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e344-il-500000.txt Download as CSV file: xf-e344-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 344 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1065 0.08711 0.08450 -0.0595 0.8053 0.0167
-10.000 -0.1045 0.08425 0.08148 -0.0597 0.7705 0.0171
-9.750 -0.1034 0.08110 0.07822 -0.0602 0.7466 0.0175
-9.500 -0.1031 0.07760 0.07463 -0.0612 0.7273 0.0176
-9.250 -0.1039 0.07393 0.07090 -0.0622 0.7113 0.0181
-9.000 -0.1080 0.06957 0.06650 -0.0640 0.6984 0.0190
-8.750 -0.1118 0.06537 0.06226 -0.0657 0.6857 0.0191
-8.500 -0.1636 0.07157 0.06848 -0.0754 0.7264 0.0178
-8.250 -0.1744 0.06754 0.06437 -0.0779 0.7075 0.0177
-8.000 -0.1869 0.06412 0.06086 -0.0781 0.6917 0.0182
-7.750 -0.1993 0.06138 0.05802 -0.0764 0.6771 0.0180
-7.500 -0.2058 0.05820 0.05471 -0.0753 0.6641 0.0186
-7.250 -0.2225 0.05168 0.04775 -0.0727 0.6575 0.0197
-6.750 -0.2139 0.04648 0.04237 -0.0697 0.6327 0.0200
-6.500 -0.2046 0.04470 0.04050 -0.0683 0.6210 0.0203
-6.250 -0.1942 0.04291 0.03857 -0.0668 0.6104 0.0207
-6.000 -0.1830 0.04079 0.03631 -0.0651 0.6002 0.0212
-5.750 -0.1708 0.03856 0.03388 -0.0633 0.5913 0.0220
-5.500 -0.1631 0.03444 0.02927 -0.0594 0.5839 0.0242
-5.250 -0.1468 0.03303 0.02779 -0.0584 0.5748 0.0246
-5.000 -0.1296 0.03168 0.02633 -0.0572 0.5655 0.0253
-4.750 -0.1114 0.03075 0.02481 -0.0538 0.5577 0.0284
-4.500 -0.0970 0.02740 0.02133 -0.0523 0.5500 0.0291
-4.250 -0.0768 0.02604 0.01990 -0.0514 0.5416 0.0297
-4.000 -0.0555 0.02487 0.01862 -0.0504 0.5335 0.0307
-3.750 -0.0326 0.02557 0.01875 -0.0479 0.5262 0.0341
-3.250 0.0162 0.01703 0.00950 -0.0447 0.5139 0.0186
-3.000 0.0443 0.01545 0.00753 -0.0437 0.5077 0.0162
-2.750 0.0707 0.01475 0.00674 -0.0432 0.5007 0.0161
-2.500 0.0957 0.01408 0.00598 -0.0424 0.4943 0.0160
-2.250 0.1196 0.01334 0.00521 -0.0415 0.4884 0.0164
-2.000 0.1428 0.01287 0.00472 -0.0405 0.4823 0.0169
-1.750 0.1662 0.01260 0.00438 -0.0395 0.4769 0.0179
-1.500 0.1910 0.01231 0.00408 -0.0388 0.4718 0.0194
-1.250 0.2148 0.01201 0.00377 -0.0379 0.4667 0.0223
-1.000 0.2390 0.01184 0.00355 -0.0370 0.4618 0.0270
-0.750 0.2624 0.01150 0.00333 -0.0361 0.4574 0.0553
-0.500 0.2811 0.01077 0.00320 -0.0346 0.4529 0.2311
-0.250 0.2678 0.00896 0.00357 -0.0260 0.4499 0.8598
0.000 0.2862 0.00955 0.00410 -0.0229 0.4459 0.8968
0.250 0.3066 0.01018 0.00470 -0.0199 0.4421 0.9190
0.500 0.3416 0.01079 0.00526 -0.0200 0.4379 0.9361
0.750 0.4644 0.01170 0.00592 -0.0387 0.4309 0.9463
1.000 0.5178 0.01196 0.00605 -0.0438 0.4264 0.9540
1.250 0.5515 0.01194 0.00600 -0.0451 0.4227 0.9559
1.500 0.5802 0.01195 0.00596 -0.0454 0.4194 0.9581
1.750 0.6040 0.01200 0.00595 -0.0447 0.4163 0.9609
2.000 0.6220 0.01210 0.00598 -0.0428 0.4132 0.9640
2.250 0.6541 0.01210 0.00594 -0.0439 0.4100 0.9649
2.500 0.6856 0.01208 0.00591 -0.0449 0.4069 0.9660
2.750 0.7154 0.01209 0.00590 -0.0455 0.4038 0.9672
3.000 0.7432 0.01212 0.00590 -0.0457 0.4010 0.9685
3.250 0.7701 0.01221 0.00592 -0.0457 0.3982 0.9701
3.500 0.7943 0.01232 0.00600 -0.0452 0.3951 0.9716
3.750 0.8159 0.01236 0.00606 -0.0441 0.3928 0.9736
4.000 0.8350 0.01241 0.00613 -0.0425 0.3903 0.9753
4.250 0.8637 0.01242 0.00614 -0.0430 0.3873 0.9759
4.500 0.8933 0.01247 0.00616 -0.0436 0.3845 0.9768
4.750 0.9215 0.01259 0.00624 -0.0440 0.3818 0.9777
5.000 0.9474 0.01271 0.00635 -0.0439 0.3790 0.9784
5.250 0.9726 0.01275 0.00645 -0.0437 0.3766 0.9793
5.500 0.9986 0.01281 0.00653 -0.0436 0.3738 0.9805
5.750 1.0231 0.01288 0.00661 -0.0432 0.3710 0.9816
6.000 1.0455 0.01298 0.00671 -0.0424 0.3684 0.9826
6.250 1.0673 0.01315 0.00686 -0.0415 0.3655 0.9835
6.500 1.0878 0.01330 0.00703 -0.0403 0.3631 0.9849
6.750 1.1116 0.01335 0.00715 -0.0399 0.3604 0.9858
7.000 1.1375 0.01342 0.00727 -0.0399 0.3575 0.9864
7.250 1.1630 0.01351 0.00738 -0.0398 0.3545 0.9870
7.500 1.1880 0.01364 0.00751 -0.0396 0.3514 0.9877
7.750 1.2128 0.01386 0.00773 -0.0395 0.3482 0.9884
8.000 1.2372 0.01393 0.00789 -0.0392 0.3453 0.9894
8.250 1.2624 0.01403 0.00805 -0.0391 0.3419 0.9905
8.500 1.2855 0.01415 0.00822 -0.0386 0.3388 0.9916
8.750 1.3076 0.01433 0.00838 -0.0380 0.3354 0.9925
9.000 1.3292 0.01453 0.00864 -0.0372 0.3321 0.9935
9.250 1.3502 0.01464 0.00885 -0.0363 0.3287 0.9946
9.500 1.3751 0.01475 0.00902 -0.0363 0.3246 0.9955
9.750 1.3988 0.01494 0.00921 -0.0361 0.3203 0.9965
10.000 1.4222 0.01514 0.00948 -0.0358 0.3162 0.9976
10.250 1.4462 0.01528 0.00972 -0.0357 0.3115 0.9989
10.500 1.4695 0.01548 0.00996 -0.0355 0.3070 1.0000
10.750 1.4767 0.01571 0.01022 -0.0320 0.3030 1.0000
11.000 1.4821 0.01583 0.01044 -0.0281 0.2988 1.0000
11.250 1.4771 0.01592 0.01059 -0.0222 0.2953 1.0000
11.500 1.4660 0.01601 0.01069 -0.0152 0.2919 1.0000
11.750 1.4606 0.01618 0.01090 -0.0096 0.2883 1.0000
12.000 1.4706 0.01641 0.01123 -0.0070 0.2829 1.0000
12.250 1.4812 0.01683 0.01166 -0.0049 0.2769 1.0000
12.500 1.4952 0.01726 0.01217 -0.0035 0.2703 1.0000
12.750 1.5057 0.01787 0.01280 -0.0018 0.2632 1.0000
13.000 1.5180 0.01850 0.01350 -0.0005 0.2560 1.0000
13.250 1.5247 0.01943 0.01443 0.0013 0.2482 1.0000
13.500 1.5341 0.02032 0.01539 0.0026 0.2397 1.0000
13.750 1.5380 0.02159 0.01668 0.0042 0.2317 1.0000
14.000 1.5394 0.02314 0.01824 0.0057 0.2220 1.0000
14.250 1.5419 0.02475 0.01991 0.0069 0.2133 1.0000
14.500 1.5385 0.02692 0.02209 0.0081 0.2048 1.0000
14.750 1.5347 0.02928 0.02449 0.0090 0.1959 1.0000
15.000 1.5304 0.03180 0.02705 0.0097 0.1879 1.0000
15.250 1.5182 0.03514 0.03040 0.0103 0.1801 1.0000
15.500 1.5121 0.03805 0.03338 0.0106 0.1722 1.0000
15.750 1.4982 0.04181 0.03716 0.0108 0.1651 1.0000
16.000 1.4852 0.04562 0.04101 0.0108 0.1574 1.0000
16.250 1.4717 0.04963 0.04507 0.0106 0.1507 1.0000
16.500 1.4575 0.05385 0.04933 0.0101 0.1441 1.0000
16.750 1.4443 0.05810 0.05362 0.0095 0.1382 1.0000
17.000 1.4302 0.06258 0.05813 0.0087 0.1318 1.0000
17.250 1.4178 0.06694 0.06254 0.0079 0.1261 1.0000
17.500 1.4058 0.07138 0.06701 0.0068 0.1201 1.0000
17.750 1.3933 0.07598 0.07165 0.0056 0.1146 1.0000
18.000 1.3841 0.08022 0.07593 0.0045 0.1091 1.0000
18.250 1.3716 0.08499 0.08072 0.0031 0.1038 1.0000
18.500 1.3640 0.08920 0.08499 0.0017 0.0985 1.0000
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