EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.42 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e343-il-1000000-n5.txt Download as CSV file: xf-e343-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1823 0.09244 0.08931 -0.0438 0.5580 0.0073
-9.500 -0.2517 0.07864 0.07535 -0.0592 0.5621 0.0065
-9.000 -0.2053 0.06363 0.06047 -0.0548 0.5306 0.0060
-8.500 -0.2427 0.05204 0.04887 -0.0626 0.5251 0.0057
-7.500 -0.4626 0.02311 0.01793 -0.0388 0.5390 0.0041
-7.250 -0.4537 0.01948 0.01373 -0.0356 0.5324 0.0040
-7.000 -0.4339 0.01812 0.01211 -0.0342 0.5241 0.0041
-6.750 -0.4128 0.01681 0.01055 -0.0329 0.5169 0.0041
-6.500 -0.3898 0.01597 0.00952 -0.0320 0.5089 0.0041
-6.250 -0.3665 0.01516 0.00854 -0.0310 0.5016 0.0042
-6.000 -0.3424 0.01454 0.00780 -0.0303 0.4938 0.0042
-5.500 -0.2933 0.01362 0.00665 -0.0289 0.4787 0.0043
-5.250 -0.2687 0.01322 0.00616 -0.0282 0.4714 0.0044
-5.000 -0.2455 0.01257 0.00541 -0.0272 0.4656 0.0046
-4.750 -0.2207 0.01223 0.00501 -0.0265 0.4596 0.0047
-4.500 -0.1958 0.01198 0.00470 -0.0259 0.4533 0.0050
-4.250 -0.1706 0.01174 0.00443 -0.0253 0.4482 0.0052
-4.000 -0.1454 0.01152 0.00416 -0.0247 0.4424 0.0054
-3.750 -0.1203 0.01133 0.00392 -0.0240 0.4359 0.0057
-3.500 -0.0949 0.01114 0.00369 -0.0235 0.4308 0.0060
-3.250 -0.0695 0.01096 0.00347 -0.0229 0.4259 0.0061
-3.000 -0.0440 0.01081 0.00328 -0.0223 0.4209 0.0064
-2.750 -0.0188 0.01064 0.00307 -0.0217 0.4164 0.0066
-2.500 0.0067 0.01047 0.00288 -0.0212 0.4127 0.0072
-2.250 0.0325 0.01034 0.00274 -0.0207 0.4083 0.0077
-2.000 0.0582 0.01024 0.00261 -0.0202 0.4037 0.0083
-1.750 0.0839 0.01015 0.00249 -0.0197 0.3993 0.0095
-1.500 0.1101 0.01005 0.00238 -0.0193 0.3959 0.0113
-1.250 0.1360 0.00995 0.00229 -0.0188 0.3921 0.0150
-1.000 0.1618 0.00986 0.00221 -0.0184 0.3883 0.0217
-0.750 0.1873 0.00977 0.00215 -0.0179 0.3847 0.0348
-0.500 0.2127 0.00964 0.00210 -0.0174 0.3819 0.0595
-0.250 0.2380 0.00949 0.00205 -0.0169 0.3791 0.0946
0.000 0.2610 0.00919 0.00201 -0.0160 0.3758 0.1843
0.250 0.2442 0.00688 0.00186 -0.0074 0.3738 0.8217
0.500 0.2684 0.00709 0.00212 -0.0063 0.3702 0.8705
1.000 0.3212 0.00740 0.00235 -0.0053 0.3650 0.8908
1.250 0.3474 0.00751 0.00244 -0.0048 0.3625 0.8978
1.500 0.3733 0.00760 0.00250 -0.0043 0.3597 0.9046
1.750 0.4004 0.00764 0.00251 -0.0040 0.3564 0.9071
2.000 0.4282 0.00770 0.00252 -0.0041 0.3535 0.9077
2.250 0.4558 0.00777 0.00254 -0.0041 0.3505 0.9084
2.500 0.4840 0.00780 0.00255 -0.0042 0.3487 0.9092
2.750 0.5120 0.00785 0.00257 -0.0043 0.3461 0.9098
3.000 0.5400 0.00790 0.00260 -0.0044 0.3435 0.9104
3.250 0.5678 0.00796 0.00263 -0.0045 0.3410 0.9110
3.500 0.5954 0.00804 0.00268 -0.0046 0.3382 0.9116
3.750 0.6227 0.00813 0.00273 -0.0046 0.3351 0.9122
4.000 0.6506 0.00819 0.00279 -0.0048 0.3331 0.9127
4.250 0.6784 0.00825 0.00284 -0.0049 0.3311 0.9133
4.500 0.7061 0.00832 0.00290 -0.0050 0.3286 0.9140
4.750 0.7335 0.00839 0.00297 -0.0051 0.3257 0.9146
5.000 0.7606 0.00848 0.00304 -0.0051 0.3232 0.9151
5.250 0.7874 0.00858 0.00313 -0.0051 0.3204 0.9156
5.500 0.8145 0.00866 0.00321 -0.0051 0.3178 0.9161
5.750 0.8418 0.00873 0.00330 -0.0052 0.3158 0.9166
6.000 0.8689 0.00882 0.00340 -0.0053 0.3130 0.9172
6.250 0.8956 0.00891 0.00350 -0.0053 0.3097 0.9177
6.500 0.9219 0.00903 0.00361 -0.0052 0.3064 0.9183
6.750 0.9480 0.00916 0.00374 -0.0051 0.3030 0.9189
7.000 0.9748 0.00925 0.00385 -0.0052 0.3004 0.9195
7.250 1.0013 0.00935 0.00397 -0.0051 0.2968 0.9201
7.500 1.0272 0.00948 0.00411 -0.0051 0.2932 0.9207
7.750 1.0523 0.00965 0.00426 -0.0048 0.2888 0.9214
8.000 1.0783 0.00976 0.00440 -0.0048 0.2856 0.9220
8.250 1.1040 0.00989 0.00456 -0.0047 0.2813 0.9226
8.500 1.1286 0.01007 0.00473 -0.0044 0.2762 0.9234
8.750 1.1529 0.01023 0.00491 -0.0040 0.2716 0.9243
9.000 1.1773 0.01038 0.00509 -0.0037 0.2665 0.9252
9.250 1.1998 0.01061 0.00531 -0.0031 0.2597 0.9260
9.500 1.2232 0.01080 0.00552 -0.0027 0.2537 0.9268
9.750 1.2447 0.01106 0.00578 -0.0019 0.2459 0.9277
10.000 1.2667 0.01128 0.00602 -0.0012 0.2399 0.9287
10.250 1.2855 0.01162 0.00634 0.0000 0.2299 0.9298
10.500 1.3054 0.01190 0.00663 0.0010 0.2220 0.9310
11.000 1.3334 0.01262 0.00735 0.0053 0.2039 0.9346
11.250 1.3461 0.01299 0.00775 0.0076 0.1961 0.9370
11.500 1.3541 0.01351 0.00826 0.0107 0.1858 0.9401
11.750 1.3613 0.01403 0.00878 0.0139 0.1763 0.9462
12.000 1.3714 0.01462 0.00936 0.0161 0.1664 0.9569
12.250 1.3786 0.01531 0.01003 0.0187 0.1569 0.9633
12.500 1.3814 0.01614 0.01084 0.0218 0.1469 0.9687
12.750 1.3881 0.01697 0.01168 0.0239 0.1382 0.9725
13.000 1.3931 0.01808 0.01279 0.0258 0.1286 0.9765
13.250 1.4018 0.01946 0.01418 0.0262 0.1194 0.9801
13.500 1.4127 0.02102 0.01575 0.0258 0.1112 0.9833
14.000 1.4282 0.02506 0.01983 0.0244 0.0949 1.0000
14.250 1.4252 0.02737 0.02216 0.0252 0.0890 1.0000
14.500 1.4177 0.03022 0.02503 0.0258 0.0816 1.0000
14.750 1.4145 0.03280 0.02767 0.0262 0.0783 1.0000
15.000 1.4020 0.03634 0.03124 0.0265 0.0712 1.0000
15.250 1.3980 0.03916 0.03412 0.0266 0.0692 1.0000
15.500 1.3875 0.04267 0.03768 0.0266 0.0659 1.0000
15.750 1.3826 0.04569 0.04077 0.0264 0.0639 1.0000
16.000 1.3558 0.05113 0.04621 0.0260 0.0547 1.0000
16.250 1.3596 0.05341 0.04860 0.0257 0.0575 1.0000
16.500 1.3324 0.05921 0.05438 0.0248 0.0478 1.0000
16.750 1.3259 0.06279 0.05802 0.0242 0.0459 1.0000
17.000 1.3170 0.06672 0.06201 0.0234 0.0436 1.0000
17.250 1.3173 0.06958 0.06497 0.0227 0.0440 1.0000
17.500 1.3033 0.07424 0.06964 0.0216 0.0394 1.0000
17.750 1.2907 0.07886 0.07429 0.0203 0.0358 1.0000
18.000 1.2865 0.08247 0.07797 0.0193 0.0348 1.0000
18.250 1.2751 0.08704 0.08256 0.0179 0.0303 1.0000
18.500 1.2677 0.09121 0.08677 0.0165 0.0281 1.0000
18.750 1.2679 0.09437 0.09000 0.0154 0.0281 1.0000
19.000 1.2642 0.09813 0.09383 0.0141 0.0274 1.0000
19.250 1.2554 0.10260 0.09832 0.0124 0.0240 1.0000
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Polar data table (+)
Polar graphs
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