EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.78 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e341-il-1000000.txt Download as CSV file: xf-e341-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 341 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3765 0.08362 0.08138 -0.0106 0.6936 0.0106
-9.500 -0.3873 0.07754 0.07528 -0.0132 0.6843 0.0109
-9.250 -0.4015 0.07089 0.06862 -0.0169 0.6770 0.0109
-9.000 -0.4277 0.06297 0.06066 -0.0233 0.6726 0.0106
-8.750 -0.4536 0.05719 0.05479 -0.0250 0.6656 0.0104
-8.500 -0.4766 0.05250 0.05001 -0.0242 0.6572 0.0105
-8.250 -0.4948 0.04828 0.04565 -0.0220 0.6480 0.0106
-8.000 -0.5071 0.04379 0.04102 -0.0195 0.6388 0.0108
-7.750 -0.5247 0.03385 0.03062 -0.0151 0.6363 0.0116
-7.500 -0.5443 0.02702 0.02349 -0.0107 0.6296 0.0119
-7.250 -0.5343 0.02501 0.02137 -0.0091 0.6170 0.0120
-7.000 -0.5236 0.02288 0.01910 -0.0074 0.6057 0.0121
-6.750 -0.5111 0.02090 0.01696 -0.0057 0.5948 0.0123
-6.500 -0.4974 0.01893 0.01483 -0.0041 0.5838 0.0126
-6.250 -0.4833 0.01679 0.01248 -0.0023 0.5735 0.0129
-6.000 -0.4686 0.01447 0.00989 -0.0001 0.5641 0.0137
-5.750 -0.4603 0.01085 0.00564 0.0039 0.5564 0.0152
-5.500 -0.4391 0.00989 0.00462 0.0046 0.5465 0.0155
-5.250 -0.4178 0.00901 0.00362 0.0055 0.5368 0.0159
-5.000 -0.4135 0.01591 0.00924 0.0117 0.5390 0.0092
-4.750 -0.3866 0.01557 0.00879 0.0121 0.5293 0.0090
-4.500 -0.3600 0.01453 0.00766 0.0125 0.5195 0.0088
-4.250 -0.3341 0.01362 0.00666 0.0130 0.5105 0.0087
-4.000 -0.3088 0.01295 0.00590 0.0136 0.5011 0.0086
-3.750 -0.2836 0.01240 0.00528 0.0143 0.4929 0.0086
-3.500 -0.2586 0.01195 0.00476 0.0149 0.4845 0.0086
-3.250 -0.2332 0.01157 0.00432 0.0155 0.4772 0.0087
-3.000 -0.2078 0.01125 0.00394 0.0161 0.4694 0.0089
-2.750 -0.1830 0.01084 0.00346 0.0168 0.4626 0.0093
-2.500 -0.1574 0.01057 0.00316 0.0174 0.4552 0.0099
-2.250 -0.1312 0.01039 0.00294 0.0178 0.4483 0.0113
-2.000 -0.1052 0.01017 0.00270 0.0182 0.4416 0.0137
-1.750 -0.0798 0.00995 0.00249 0.0188 0.4350 0.0264
-1.500 -0.0549 0.00964 0.00235 0.0194 0.4299 0.0672
-1.250 -0.0299 0.00939 0.00225 0.0199 0.4241 0.1173
-1.000 -0.0109 0.00873 0.00209 0.0213 0.4184 0.2761
-0.750 -0.0152 0.00682 0.00170 0.0272 0.4154 0.6856
-0.500 -0.0027 0.00654 0.00208 0.0312 0.4108 0.8755
-0.250 0.0226 0.00706 0.00259 0.0325 0.4055 0.8964
0.000 0.0488 0.00746 0.00295 0.0333 0.4009 0.9065
0.250 0.0770 0.00777 0.00323 0.0338 0.3967 0.9114
0.500 0.1064 0.00830 0.00372 0.0343 0.3921 0.9185
0.750 0.1326 0.00857 0.00392 0.0349 0.3871 0.9241
1.000 0.1692 0.00895 0.00428 0.0337 0.3834 0.9269
1.250 0.2042 0.00917 0.00445 0.0325 0.3793 0.9288
1.500 0.2326 0.00921 0.00444 0.0323 0.3753 0.9300
1.750 0.2592 0.00927 0.00443 0.0325 0.3707 0.9314
2.000 0.2849 0.00925 0.00440 0.0329 0.3681 0.9332
2.250 0.3070 0.00921 0.00434 0.0340 0.3652 0.9356
2.500 0.3281 0.00919 0.00429 0.0351 0.3621 0.9377
2.750 0.3555 0.00917 0.00423 0.0352 0.3588 0.9385
3.000 0.3827 0.00921 0.00423 0.0352 0.3548 0.9391
3.250 0.4108 0.00919 0.00421 0.0350 0.3524 0.9397
3.500 0.4390 0.00920 0.00421 0.0349 0.3494 0.9403
3.750 0.4667 0.00923 0.00422 0.0348 0.3462 0.9410
4.000 0.4936 0.00928 0.00424 0.0348 0.3429 0.9417
4.250 0.5201 0.00936 0.00429 0.0349 0.3394 0.9424
4.500 0.5478 0.00937 0.00432 0.0348 0.3373 0.9432
4.750 0.5748 0.00938 0.00433 0.0348 0.3346 0.9440
5.000 0.6012 0.00940 0.00435 0.0349 0.3315 0.9448
5.250 0.6271 0.00944 0.00438 0.0351 0.3284 0.9456
5.500 0.6522 0.00953 0.00444 0.0354 0.3245 0.9465
5.750 0.6787 0.00955 0.00449 0.0354 0.3224 0.9476
6.000 0.7053 0.00956 0.00452 0.0354 0.3197 0.9485
6.250 0.7321 0.00959 0.00456 0.0354 0.3164 0.9493
6.500 0.7588 0.00965 0.00462 0.0353 0.3128 0.9500
6.750 0.7852 0.00978 0.00472 0.0352 0.3087 0.9506
7.000 0.8134 0.00981 0.00479 0.0348 0.3063 0.9511
7.250 0.8405 0.00982 0.00484 0.0347 0.3031 0.9516
7.500 0.8671 0.00988 0.00490 0.0347 0.2990 0.9521
7.750 0.8927 0.01001 0.00501 0.0348 0.2945 0.9527
8.000 0.9196 0.01006 0.00512 0.0347 0.2915 0.9534
8.250 0.9465 0.01012 0.00521 0.0346 0.2873 0.9541
8.500 0.9729 0.01024 0.00533 0.0345 0.2825 0.9547
8.750 0.9992 0.01036 0.00547 0.0344 0.2778 0.9553
9.000 1.0262 0.01044 0.00559 0.0342 0.2733 0.9560
9.250 1.0522 0.01059 0.00574 0.0341 0.2673 0.9567
9.500 1.0786 0.01073 0.00591 0.0340 0.2620 0.9574
9.750 1.1049 0.01087 0.00607 0.0338 0.2560 0.9581
10.000 1.1305 0.01108 0.00628 0.0337 0.2489 0.9590
10.250 1.1565 0.01126 0.00648 0.0335 0.2411 0.9597
10.500 1.1820 0.01150 0.00672 0.0334 0.2335 0.9605
11.000 1.2316 0.01211 0.00731 0.0331 0.2126 0.9621
11.250 1.2546 0.01246 0.00765 0.0333 0.2011 0.9629
11.500 1.2743 0.01286 0.00803 0.0341 0.1892 0.9642
11.750 1.2933 0.01333 0.00847 0.0349 0.1768 0.9655
12.000 1.3118 0.01387 0.00898 0.0357 0.1639 0.9668
12.250 1.3289 0.01449 0.00957 0.0366 0.1502 0.9683
12.500 1.3448 0.01517 0.01021 0.0376 0.1373 0.9700
12.750 1.3582 0.01588 0.01090 0.0388 0.1260 0.9720
13.000 1.3651 0.01671 0.01171 0.0411 0.1151 0.9746
13.250 1.3695 0.01773 0.01271 0.0434 0.1041 0.9779
13.500 1.3741 0.01897 0.01394 0.0449 0.0941 0.9816
13.750 1.3791 0.02041 0.01540 0.0458 0.0858 0.9864
14.000 1.3847 0.02233 0.01734 0.0454 0.0778 0.9913
14.250 1.3897 0.02487 0.01989 0.0439 0.0697 0.9959
14.500 1.3975 0.02754 0.02260 0.0416 0.0634 0.9980
14.750 1.3970 0.03056 0.02568 0.0401 0.0582 1.0000
15.000 1.3942 0.03394 0.02911 0.0386 0.0537 1.0000
15.250 1.3891 0.03760 0.03282 0.0371 0.0499 1.0000
15.500 1.3833 0.04135 0.03663 0.0356 0.0466 1.0000
15.750 1.3726 0.04561 0.04095 0.0342 0.0438 1.0000
16.000 1.3642 0.04958 0.04501 0.0328 0.0415 1.0000
16.250 1.3542 0.05374 0.04924 0.0315 0.0393 1.0000
16.500 1.3425 0.05824 0.05380 0.0300 0.0372 1.0000
16.750 1.3308 0.06278 0.05840 0.0284 0.0351 1.0000
17.000 1.3231 0.06692 0.06262 0.0270 0.0334 1.0000
17.250 1.3128 0.07140 0.06716 0.0254 0.0316 1.0000
17.500 1.3008 0.07615 0.07196 0.0238 0.0298 1.0000
17.750 1.2928 0.08045 0.07633 0.0223 0.0283 1.0000
18.000 1.2860 0.08460 0.08054 0.0208 0.0267 1.0000
18.250 1.2757 0.08927 0.08526 0.0191 0.0252 1.0000
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