EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 100,000 Max Cl/Cd: 30.37 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e342-il-100000.txt Download as CSV file: xf-e342-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 342 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3491 0.10472 0.10020 -0.0248 1.0000 0.0841
-9.500 -0.3709 0.10096 0.09655 -0.0313 1.0000 0.0859
-9.250 -0.3923 0.09702 0.09266 -0.0365 1.0000 0.0862
-9.000 -0.3646 0.09244 0.08817 -0.0321 1.0000 0.0887
-8.750 -0.3545 0.08948 0.08526 -0.0310 1.0000 0.0910
-8.500 -0.3573 0.08591 0.08177 -0.0325 1.0000 0.0935
-8.250 -0.3698 0.08222 0.07816 -0.0343 1.0000 0.0957
-8.000 -0.3921 0.07944 0.07544 -0.0340 1.0000 0.0975
-7.750 -0.4191 0.07768 0.07372 -0.0314 1.0000 0.0988
-7.500 -0.4539 0.07735 0.07341 -0.0271 1.0000 0.0998
-7.250 -0.4404 0.07157 0.06770 -0.0303 0.9827 0.1024
-7.000 -0.4004 0.06662 0.06279 -0.0349 0.9558 0.1091
-6.750 -0.3841 0.06182 0.05761 -0.0401 0.9230 0.1181
-6.500 -0.3489 0.05779 0.05343 -0.0438 0.8958 0.1280
-6.250 -0.3347 0.05412 0.04952 -0.0442 0.8650 0.1369
-6.000 -0.3319 0.05252 0.04748 -0.0419 0.8375 0.1504
-5.750 -0.3131 0.04947 0.04442 -0.0409 0.8139 0.1575
-5.500 -0.3047 0.04727 0.04202 -0.0387 0.7939 0.1723
-5.250 -0.2950 0.04528 0.03987 -0.0363 0.7757 0.1907
-4.500 -0.2296 0.03480 0.02676 -0.0272 0.7342 0.0728
-4.250 -0.2073 0.03201 0.02324 -0.0245 0.7223 0.0641
-4.000 -0.1816 0.02991 0.02089 -0.0234 0.7081 0.0618
-3.750 -0.1547 0.02802 0.01872 -0.0225 0.6950 0.0601
-3.500 -0.1250 0.02639 0.01676 -0.0219 0.6836 0.0595
-3.250 -0.0938 0.02502 0.01509 -0.0215 0.6722 0.0617
-3.000 -0.0637 0.02381 0.01386 -0.0215 0.6602 0.0673
-2.750 -0.0328 0.02289 0.01274 -0.0212 0.6505 0.0741
-2.500 0.2774 0.02033 0.01278 -0.0630 0.6227 1.0000
-2.250 0.2978 0.02030 0.01250 -0.0621 0.6145 1.0000
-2.000 0.3184 0.02027 0.01230 -0.0614 0.6051 1.0000
-1.750 0.3393 0.02030 0.01210 -0.0605 0.5980 1.0000
-1.500 0.3604 0.02034 0.01203 -0.0599 0.5895 1.0000
-1.250 0.3818 0.02040 0.01187 -0.0590 0.5833 1.0000
-1.000 0.4031 0.02052 0.01193 -0.0584 0.5754 1.0000
-0.750 0.4247 0.02060 0.01187 -0.0576 0.5687 1.0000
-0.500 0.4465 0.02075 0.01187 -0.0569 0.5629 1.0000
-0.250 0.4680 0.02094 0.01203 -0.0562 0.5559 1.0000
0.000 0.4901 0.02110 0.01206 -0.0555 0.5507 1.0000
0.250 0.5121 0.02134 0.01222 -0.0548 0.5454 1.0000
0.500 0.5335 0.02161 0.01248 -0.0541 0.5388 1.0000
0.750 0.5557 0.02179 0.01256 -0.0533 0.5337 1.0000
1.000 0.5779 0.02208 0.01276 -0.0526 0.5292 1.0000
1.250 0.5989 0.02250 0.01325 -0.0519 0.5234 1.0000
1.500 0.6209 0.02279 0.01350 -0.0512 0.5184 1.0000
1.750 0.6435 0.02303 0.01363 -0.0504 0.5144 1.0000
2.000 0.6639 0.02355 0.01423 -0.0497 0.5090 1.0000
2.250 0.6848 0.02402 0.01474 -0.0489 0.5040 1.0000
2.500 0.7069 0.02435 0.01502 -0.0481 0.4998 1.0000
2.750 0.7299 0.02465 0.01523 -0.0474 0.4964 1.0000
3.000 0.7474 0.02546 0.01623 -0.0465 0.4906 1.0000
3.250 0.7677 0.02599 0.01679 -0.0456 0.4858 1.0000
3.500 0.7897 0.02635 0.01712 -0.0448 0.4822 1.0000
3.750 0.8122 0.02674 0.01745 -0.0440 0.4789 1.0000
4.000 0.8258 0.02789 0.01886 -0.0427 0.4727 1.0000
4.250 0.8449 0.02852 0.01953 -0.0416 0.4683 1.0000
4.500 0.8672 0.02884 0.01982 -0.0408 0.4649 1.0000
4.750 0.8870 0.02947 0.02046 -0.0397 0.4612 1.0000
5.000 0.8953 0.03106 0.02233 -0.0379 0.4551 1.0000
5.250 0.9132 0.03173 0.02305 -0.0367 0.4508 1.0000
5.500 0.9369 0.03190 0.02318 -0.0358 0.4476 1.0000
5.750 0.9481 0.03321 0.02462 -0.0340 0.4428 1.0000
6.000 0.9507 0.03516 0.02681 -0.0316 0.4368 1.0000
6.250 0.9699 0.03562 0.02729 -0.0303 0.4329 1.0000
6.500 0.9983 0.03541 0.02701 -0.0298 0.4300 1.0000
6.750 0.9802 0.03889 0.03082 -0.0256 0.4229 1.0000
7.000 0.9850 0.04036 0.03239 -0.0231 0.4177 1.0000
7.250 1.0160 0.03981 0.03182 -0.0227 0.4146 1.0000
7.500 1.0242 0.04114 0.03323 -0.0204 0.4103 1.0000
7.750 0.9426 0.04853 0.04091 -0.0114 0.4009 1.0000
8.000 0.9941 0.04645 0.03882 -0.0121 0.3985 1.0000
8.250 1.0610 0.04352 0.03583 -0.0145 0.3965 1.0000
8.500 0.6802 0.07371 0.06597 0.0054 0.3764 1.0000
8.750 0.6374 0.07949 0.07174 0.0068 0.3705 1.0000
9.000 0.6709 0.07846 0.07075 0.0086 0.3658 1.0000
9.250 0.7400 0.07415 0.06652 0.0107 0.3635 1.0000
9.500 0.6229 0.08734 0.07964 0.0104 0.3552 1.0000
9.750 0.6556 0.08640 0.07875 0.0123 0.3498 1.0000
10.000 0.6377 0.09045 0.08280 0.0129 0.3434 1.0000
10.250 0.6205 0.09468 0.08705 0.0130 0.3389 1.0000
10.500 0.6762 0.09132 0.08374 0.0156 0.3328 1.0000
10.750 0.6308 0.09858 0.09100 0.0146 0.3265 1.0000
11.000 0.6329 0.10099 0.09344 0.0150 0.3209 1.0000
11.250 0.6624 0.10041 0.09292 0.0167 0.3141 1.0000
11.500 0.6319 0.10659 0.09910 0.0153 0.3090 1.0000
11.750 0.6828 0.10349 0.09609 0.0180 0.3020 1.0000
12.000 0.6459 0.11070 0.10331 0.0159 0.2960 1.0000
12.250 0.6533 0.11275 0.10541 0.0161 0.2899 1.0000
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