EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 50,000 Max Cl/Cd: 14.52 at α=-0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e343-il-50000.txt Download as CSV file: xf-e343-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 343 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3135 0.11061 0.10461 -0.0238 1.0000 0.2227
-9.000 -0.2878 0.10576 0.09981 -0.0221 1.0000 0.2335
-8.750 -0.3250 0.10562 0.09989 -0.0244 1.0000 0.2415
-8.500 -0.3043 0.10137 0.09571 -0.0224 1.0000 0.2583
-8.250 -0.2906 0.09777 0.09221 -0.0208 1.0000 0.2743
-8.000 -0.2854 0.09486 0.08942 -0.0195 1.0000 0.2910
-7.750 -0.2831 0.09231 0.08702 -0.0181 1.0000 0.3086
-7.500 -0.2913 0.09041 0.08532 -0.0161 1.0000 0.3289
-7.250 -0.3068 0.08911 0.08429 -0.0133 1.0000 0.3483
-7.000 -0.2933 0.08673 0.08210 -0.0097 1.0000 0.3722
-6.750 -0.3871 0.09170 0.08747 -0.0029 0.9964 0.3481
-6.500 -0.3158 0.08674 0.08248 -0.0043 0.9852 0.4185
-6.250 -0.2230 0.08208 0.07775 -0.0029 0.9750 0.5431
-6.000 -0.1352 0.07740 0.07301 -0.0050 0.9624 0.6710
-5.750 -0.0393 0.06984 0.06534 -0.0161 0.9472 0.7464
-5.500 -0.0771 0.04834 0.04400 -0.0482 0.8683 0.4488
-5.250 -0.1300 0.04544 0.04115 -0.0472 0.8521 0.4254
-5.000 -0.1805 0.04157 0.03710 -0.0488 0.8383 0.3717
-4.500 -0.2065 0.04861 0.04136 -0.0527 0.8438 0.1662
-4.250 -0.1849 0.04620 0.03843 -0.0513 0.8293 0.1466
-4.000 -0.1617 0.04441 0.03598 -0.0496 0.8160 0.1318
-3.750 -0.1274 0.04155 0.03265 -0.0497 0.8058 0.1228
-3.500 -0.1043 0.04085 0.03125 -0.0475 0.7928 0.1168
-3.250 -0.0803 0.03937 0.02954 -0.0466 0.7807 0.1158
-3.000 0.2982 0.02710 0.01961 -0.0920 0.7673 1.0000
-2.750 0.3187 0.02739 0.01937 -0.0909 0.7553 1.0000
-2.500 0.3369 0.02785 0.01951 -0.0901 0.7434 1.0000
-2.250 0.3562 0.02821 0.01952 -0.0889 0.7335 1.0000
-2.000 0.3734 0.02876 0.01984 -0.0879 0.7227 1.0000
-1.750 0.3914 0.02929 0.02013 -0.0868 0.7136 1.0000
-1.500 0.4086 0.02994 0.02059 -0.0858 0.7044 1.0000
-1.250 0.4269 0.03054 0.02098 -0.0847 0.6969 1.0000
-1.000 0.4418 0.03144 0.02176 -0.0837 0.6878 1.0000
-0.750 0.4626 0.03185 0.02194 -0.0824 0.6814 1.0000
-0.500 0.4727 0.03326 0.02333 -0.0814 0.6729 1.0000
-0.250 0.4896 0.03406 0.02398 -0.0802 0.6664 1.0000
0.000 0.5039 0.03514 0.02496 -0.0789 0.6602 1.0000
0.250 0.5109 0.03674 0.02653 -0.0774 0.6528 1.0000
0.500 0.5283 0.03755 0.02722 -0.0761 0.6473 1.0000
0.750 0.5345 0.03929 0.02892 -0.0744 0.6420 1.0000
1.000 0.5281 0.04177 0.03143 -0.0719 0.6361 1.0000
1.250 0.5369 0.04320 0.03278 -0.0700 0.6309 1.0000
1.500 0.5594 0.04389 0.03333 -0.0690 0.6265 1.0000
1.750 0.5211 0.04810 0.03764 -0.0640 0.6229 1.0000
2.000 0.4874 0.05160 0.04116 -0.0589 0.6208 1.0000
2.250 0.4473 0.05473 0.04429 -0.0524 0.6205 1.0000
2.500 0.4183 0.05738 0.04692 -0.0472 0.6213 1.0000
2.750 0.4043 0.05974 0.04924 -0.0438 0.6233 1.0000
3.000 0.4023 0.06192 0.05136 -0.0417 0.6254 1.0000
3.250 0.1823 0.06820 0.05815 -0.0265 0.8100 1.0000
3.500 0.1886 0.06926 0.05910 -0.0246 0.7977 1.0000
3.750 0.2237 0.07257 0.06227 -0.0271 0.7893 1.0000
4.000 0.2249 0.07283 0.06244 -0.0243 0.7741 1.0000
4.250 0.2306 0.07390 0.06344 -0.0224 0.7609 1.0000
4.500 0.2658 0.07745 0.06686 -0.0247 0.7532 1.0000
4.750 0.2617 0.07743 0.06678 -0.0214 0.7390 1.0000
5.000 0.2673 0.07873 0.06801 -0.0196 0.7278 1.0000
5.250 0.2991 0.08182 0.07102 -0.0213 0.7181 1.0000
5.500 0.2943 0.08212 0.07127 -0.0182 0.7047 1.0000
5.750 0.3189 0.08522 0.07430 -0.0191 0.6983 1.0000
6.000 0.3216 0.08586 0.07490 -0.0170 0.6845 1.0000
6.250 0.3251 0.08724 0.07624 -0.0153 0.6742 1.0000
6.500 0.3515 0.09004 0.07900 -0.0161 0.6647 1.0000
6.750 0.3464 0.09073 0.07966 -0.0136 0.6536 1.0000
7.000 0.3781 0.09430 0.08320 -0.0151 0.6458 1.0000
7.250 0.3695 0.09451 0.08339 -0.0123 0.6333 1.0000
7.500 0.4073 0.09906 0.08792 -0.0145 0.6270 1.0000
7.750 0.3917 0.09848 0.08733 -0.0112 0.6142 1.0000
8.000 0.4235 0.10278 0.09163 -0.0128 0.6086 1.0000
8.250 0.4139 0.10260 0.09144 -0.0102 0.5954 1.0000
8.500 0.4267 0.10533 0.09417 -0.0102 0.5885 1.0000
8.750 0.4345 0.10685 0.09569 -0.0094 0.5772 1.0000
9.000 0.4456 0.10957 0.09843 -0.0093 0.5706 1.0000
9.250 0.4551 0.11124 0.10012 -0.0088 0.5590 1.0000
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Polar data table (+)
Polar graphs
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