EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 100,000 Max Cl/Cd: 42.41 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e341-il-100000-n5.txt Download as CSV file: xf-e341-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3590 0.08545 0.08131 -0.0221 1.0000 0.0275
-9.250 -0.4897 0.08306 0.07856 -0.0228 1.0000 0.0275
-9.000 -0.4871 0.08034 0.07589 -0.0225 1.0000 0.0271
-8.750 -0.4925 0.07674 0.07230 -0.0228 1.0000 0.0265
-8.500 -0.5013 0.07304 0.06858 -0.0226 1.0000 0.0259
-8.000 -0.5349 0.06206 0.05714 -0.0191 1.0000 0.0225
-7.750 -0.5334 0.05920 0.05422 -0.0174 1.0000 0.0222
-7.500 -0.5250 0.05571 0.05057 -0.0171 0.9333 0.0219
-7.250 -0.5098 0.05176 0.04625 -0.0175 0.8712 0.0215
-6.750 -0.4933 0.04537 0.03903 -0.0129 0.8013 0.0209
-6.500 -0.4834 0.04234 0.03554 -0.0102 0.7770 0.0206
-6.250 -0.4712 0.03941 0.03213 -0.0077 0.7558 0.0203
-6.000 -0.4564 0.03664 0.02886 -0.0053 0.7369 0.0202
-5.750 -0.4387 0.03414 0.02588 -0.0032 0.7196 0.0202
-5.500 -0.4183 0.03192 0.02319 -0.0015 0.7034 0.0203
-5.250 -0.3955 0.03003 0.02084 -0.0002 0.6878 0.0213
-5.000 -0.3700 0.02822 0.01847 0.0010 0.6731 0.0225
-4.750 -0.3456 0.02706 0.01722 0.0015 0.6589 0.0239
-4.500 -0.3187 0.02577 0.01569 0.0021 0.6457 0.0249
-4.250 -0.2904 0.02445 0.01413 0.0025 0.6332 0.0259
-4.000 -0.2620 0.02326 0.01273 0.0028 0.6205 0.0271
-3.750 -0.2361 0.02225 0.01164 0.0034 0.6092 0.0287
-3.500 -0.2117 0.02156 0.01084 0.0042 0.5989 0.0317
-3.000 -0.1646 0.02023 0.00932 0.0062 0.5781 0.0413
-2.750 -0.1416 0.01961 0.00869 0.0072 0.5688 0.0519
-2.500 -0.1180 0.01896 0.00812 0.0082 0.5600 0.0772
-2.250 -0.0458 0.01764 0.00999 0.0034 0.5491 0.8343
-2.000 -0.0250 0.01877 0.01090 0.0067 0.5400 0.8885
-1.750 0.0430 0.02005 0.01176 0.0014 0.5295 0.9317
-1.500 0.1046 0.02025 0.01164 -0.0045 0.5194 0.9564
-1.250 0.1375 0.02017 0.01133 -0.0056 0.5120 0.9635
-1.000 0.1714 0.02000 0.01096 -0.0071 0.5040 0.9670
-0.750 0.2010 0.01993 0.01068 -0.0077 0.4976 0.9715
-0.500 0.2341 0.01979 0.01041 -0.0091 0.4903 0.9745
-0.250 0.2658 0.01970 0.01013 -0.0102 0.4845 0.9778
0.000 0.2956 0.01966 0.00998 -0.0110 0.4783 0.9813
0.250 0.3281 0.01956 0.00975 -0.0123 0.4719 0.9837
0.500 0.3587 0.01951 0.00954 -0.0131 0.4669 0.9866
0.750 0.3894 0.01949 0.00948 -0.0141 0.4607 0.9892
1.000 0.4211 0.01944 0.00933 -0.0153 0.4554 0.9915
1.250 0.4514 0.01943 0.00919 -0.0161 0.4510 0.9938
1.500 0.4825 0.01943 0.00919 -0.0172 0.4453 0.9960
1.750 0.5137 0.01942 0.00913 -0.0183 0.4401 0.9979
2.000 0.5440 0.01945 0.00906 -0.0192 0.4359 0.9998
2.250 0.5691 0.01958 0.00918 -0.0190 0.4317 1.0000
2.500 0.5937 0.01973 0.00934 -0.0188 0.4269 1.0000
2.750 0.6181 0.01987 0.00945 -0.0184 0.4226 1.0000
3.000 0.6424 0.02001 0.00953 -0.0181 0.4191 1.0000
3.250 0.6667 0.02022 0.00979 -0.0178 0.4148 1.0000
3.500 0.6909 0.02043 0.01003 -0.0175 0.4103 1.0000
3.750 0.7151 0.02061 0.01020 -0.0171 0.4063 1.0000
4.000 0.7392 0.02079 0.01035 -0.0167 0.4030 1.0000
4.250 0.7630 0.02107 0.01072 -0.0164 0.3989 1.0000
4.500 0.7867 0.02135 0.01107 -0.0160 0.3946 1.0000
4.750 0.8103 0.02157 0.01133 -0.0156 0.3907 1.0000
5.000 0.8342 0.02178 0.01151 -0.0151 0.3875 1.0000
5.250 0.8572 0.02212 0.01195 -0.0146 0.3833 1.0000
5.500 0.8798 0.02246 0.01243 -0.0142 0.3789 1.0000
5.750 0.9028 0.02273 0.01275 -0.0136 0.3750 1.0000
6.000 0.9261 0.02297 0.01297 -0.0130 0.3718 1.0000
6.250 0.9479 0.02338 0.01353 -0.0124 0.3678 1.0000
6.500 0.9690 0.02380 0.01410 -0.0117 0.3631 1.0000
6.750 0.9908 0.02410 0.01446 -0.0110 0.3591 1.0000
7.000 1.0135 0.02434 0.01470 -0.0103 0.3558 1.0000
7.250 1.0328 0.02487 0.01544 -0.0094 0.3512 1.0000
7.500 1.0522 0.02534 0.01605 -0.0084 0.3464 1.0000
7.750 1.0731 0.02562 0.01640 -0.0075 0.3425 1.0000
8.000 1.0945 0.02589 0.01671 -0.0066 0.3388 1.0000
8.250 1.1098 0.02657 0.01765 -0.0052 0.3332 1.0000
8.500 1.1284 0.02694 0.01812 -0.0040 0.3284 1.0000
8.750 1.1496 0.02711 0.01830 -0.0030 0.3247 1.0000
9.000 1.1624 0.02786 0.01931 -0.0012 0.3190 1.0000
9.250 1.1780 0.02830 0.01990 0.0004 0.3137 1.0000
9.500 1.1980 0.02842 0.02002 0.0016 0.3095 1.0000
9.750 1.2066 0.02924 0.02110 0.0039 0.3034 1.0000
10.000 1.2199 0.02965 0.02165 0.0059 0.2979 1.0000
10.250 1.2359 0.02986 0.02190 0.0076 0.2930 1.0000
10.500 1.2384 0.03077 0.02308 0.0107 0.2865 1.0000
10.750 1.2502 0.03102 0.02339 0.0130 0.2810 1.0000
11.000 1.2516 0.03180 0.02434 0.0163 0.2752 1.0000
11.250 1.2512 0.03251 0.02520 0.0200 0.2692 1.0000
11.500 1.2566 0.03283 0.02555 0.0231 0.2641 1.0000
11.750 1.2349 0.03411 0.02701 0.0292 0.2591 1.0000
12.000 1.2169 0.03509 0.02806 0.0348 0.2546 1.0000
12.250 1.2113 0.03579 0.02877 0.0385 0.2499 1.0000
12.500 1.1803 0.03852 0.03165 0.0424 0.2449 1.0000
12.750 1.1710 0.04051 0.03371 0.0440 0.2390 1.0000
13.000 1.1556 0.04367 0.03698 0.0445 0.2327 1.0000
13.250 1.1400 0.04740 0.04080 0.0441 0.2258 1.0000
13.500 1.1272 0.05115 0.04462 0.0435 0.2190 1.0000
13.750 1.1110 0.05556 0.04910 0.0423 0.2117 1.0000
14.000 1.0949 0.06015 0.05377 0.0411 0.2045 1.0000
14.250 1.0892 0.06345 0.05711 0.0403 0.1971 1.0000
14.500 1.0679 0.06905 0.06279 0.0385 0.1896 1.0000
14.750 1.0775 0.07030 0.06403 0.0384 0.1824 1.0000
15.000 1.0512 0.07699 0.07083 0.0361 0.1749 1.0000
15.250 1.0706 0.07685 0.07066 0.0365 0.1678 1.0000
15.500 1.0410 0.08441 0.07835 0.0336 0.1605 1.0000
15.750 1.0552 0.08510 0.07901 0.0336 0.1537 1.0000
16.000 1.0337 0.09165 0.08568 0.0311 0.1467 1.0000
16.250 1.0436 0.09307 0.08708 0.0308 0.1401 1.0000
16.500 1.0269 0.09902 0.09315 0.0284 0.1336 1.0000
16.750 1.0356 0.10069 0.09478 0.0279 0.1272 1.0000
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Polar data table (+)
Polar graphs
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