EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 500,000 Max Cl/Cd: 87.93 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e343-il-500000-n5.txt Download as CSV file: xf-e343-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1961 0.07406 0.07059 -0.0515 0.6124 0.0114
-8.500 -0.2936 0.06337 0.05967 -0.0654 0.6111 0.0086
-8.250 -0.3038 0.06094 0.05718 -0.0636 0.6020 0.0085
-8.000 -0.3136 0.05845 0.05459 -0.0612 0.5936 0.0084
-7.750 -0.3165 0.05572 0.05176 -0.0595 0.5848 0.0083
-7.250 -0.3463 0.04275 0.03823 -0.0517 0.5751 0.0064
-7.000 -0.3414 0.03997 0.03525 -0.0492 0.5669 0.0064
-6.750 -0.3388 0.03612 0.03112 -0.0459 0.5595 0.0063
-6.500 -0.3335 0.03228 0.02696 -0.0426 0.5525 0.0062
-6.250 -0.3345 0.02579 0.01984 -0.0375 0.5476 0.0060
-6.000 -0.3236 0.02157 0.01496 -0.0341 0.5406 0.0060
-5.750 -0.3034 0.01943 0.01241 -0.0325 0.5333 0.0060
-5.500 -0.2803 0.01791 0.01054 -0.0313 0.5252 0.0062
-5.250 -0.2561 0.01698 0.00938 -0.0305 0.5177 0.0064
-5.000 -0.2316 0.01609 0.00832 -0.0297 0.5097 0.0066
-4.750 -0.2075 0.01546 0.00756 -0.0290 0.5018 0.0067
-4.500 -0.1828 0.01503 0.00707 -0.0283 0.4940 0.0071
-4.250 -0.1583 0.01462 0.00657 -0.0276 0.4867 0.0073
-4.000 -0.1337 0.01421 0.00609 -0.0269 0.4805 0.0076
-3.750 -0.1093 0.01382 0.00562 -0.0261 0.4739 0.0081
-3.250 -0.0606 0.01320 0.00486 -0.0246 0.4625 0.0086
-3.000 -0.0366 0.01288 0.00449 -0.0237 0.4563 0.0091
-2.750 -0.0124 0.01267 0.00422 -0.0230 0.4505 0.0097
-2.500 0.0128 0.01250 0.00403 -0.0224 0.4451 0.0109
-2.250 0.0373 0.01229 0.00378 -0.0217 0.4397 0.0120
-2.000 0.0618 0.01213 0.00357 -0.0209 0.4349 0.0133
-1.750 0.0867 0.01194 0.00336 -0.0202 0.4307 0.0150
-1.500 0.1117 0.01178 0.00319 -0.0196 0.4262 0.0183
-1.250 0.1364 0.01164 0.00304 -0.0189 0.4216 0.0256
-0.750 0.1848 0.01129 0.00286 -0.0175 0.4133 0.0786
-0.500 0.2078 0.01102 0.00278 -0.0166 0.4091 0.1436
-0.250 0.1997 0.00900 0.00249 -0.0102 0.4065 0.6394
0.000 0.2087 0.00885 0.00311 -0.0051 0.4034 0.8689
0.250 0.2303 0.00912 0.00330 -0.0034 0.3999 0.8900
0.500 0.2532 0.00926 0.00340 -0.0020 0.3970 0.9030
0.750 0.2777 0.00939 0.00350 -0.0009 0.3937 0.9130
1.000 0.3051 0.00961 0.00369 -0.0002 0.3900 0.9214
1.250 0.3345 0.00986 0.00388 -0.0002 0.3862 0.9263
1.500 0.3616 0.00995 0.00389 0.0000 0.3830 0.9277
1.750 0.3883 0.00998 0.00388 0.0001 0.3804 0.9288
2.000 0.4142 0.01000 0.00386 0.0005 0.3776 0.9300
2.250 0.4389 0.01002 0.00384 0.0010 0.3744 0.9317
2.500 0.4650 0.01007 0.00384 0.0013 0.3712 0.9326
2.750 0.4918 0.01016 0.00388 0.0014 0.3682 0.9332
3.000 0.5188 0.01023 0.00392 0.0015 0.3658 0.9338
3.250 0.5460 0.01030 0.00398 0.0015 0.3632 0.9346
3.500 0.5728 0.01037 0.00404 0.0016 0.3604 0.9354
3.750 0.5991 0.01044 0.00409 0.0018 0.3573 0.9362
4.000 0.6249 0.01053 0.00415 0.0020 0.3547 0.9370
4.250 0.6503 0.01062 0.00422 0.0023 0.3520 0.9380
4.500 0.6757 0.01071 0.00429 0.0026 0.3495 0.9390
4.750 0.7015 0.01076 0.00436 0.0029 0.3471 0.9400
5.000 0.7277 0.01085 0.00446 0.0030 0.3444 0.9408
5.250 0.7540 0.01096 0.00457 0.0031 0.3417 0.9416
5.500 0.7797 0.01108 0.00468 0.0033 0.3388 0.9425
5.750 0.8049 0.01121 0.00480 0.0036 0.3360 0.9433
6.000 0.8302 0.01134 0.00494 0.0039 0.3337 0.9442
6.250 0.8560 0.01142 0.00506 0.0041 0.3312 0.9452
6.500 0.8811 0.01152 0.00519 0.0043 0.3283 0.9463
6.750 0.9056 0.01164 0.00533 0.0047 0.3252 0.9476
7.000 0.9300 0.01177 0.00547 0.0051 0.3222 0.9486
7.250 0.9540 0.01194 0.00563 0.0055 0.3191 0.9498
7.500 0.9790 0.01205 0.00579 0.0058 0.3162 0.9510
7.750 1.0033 0.01217 0.00596 0.0062 0.3129 0.9525
8.000 1.0264 0.01230 0.00612 0.0068 0.3093 0.9544
8.250 1.0490 0.01247 0.00630 0.0074 0.3060 0.9563
8.500 1.0714 0.01264 0.00650 0.0081 0.3025 0.9584
8.750 1.0944 0.01276 0.00669 0.0087 0.2989 0.9607
9.000 1.1164 0.01291 0.00688 0.0094 0.2948 0.9628
9.250 1.1384 0.01311 0.00710 0.0100 0.2904 0.9646
9.500 1.1599 0.01329 0.00732 0.0108 0.2865 0.9669
9.750 1.1804 0.01345 0.00754 0.0118 0.2812 0.9695
10.000 1.2019 0.01367 0.00780 0.0124 0.2761 0.9714
10.250 1.2231 0.01391 0.00808 0.0131 0.2708 0.9738
10.500 1.2436 0.01416 0.00838 0.0139 0.2643 0.9768
10.750 1.2665 0.01453 0.00877 0.0139 0.2580 0.9787
11.000 1.2907 0.01488 0.00917 0.0138 0.2500 0.9805
11.250 1.3127 0.01533 0.00964 0.0138 0.2423 0.9829
11.500 1.3339 0.01582 0.01016 0.0139 0.2330 0.9856
11.750 1.3564 0.01641 0.01077 0.0135 0.2230 0.9878
12.000 1.3765 0.01711 0.01150 0.0133 0.2135 0.9911
12.250 1.3937 0.01796 0.01235 0.0134 0.2028 0.9964
12.500 1.4031 0.01882 0.01324 0.0148 0.1929 1.0000
12.750 1.4009 0.01986 0.01428 0.0181 0.1846 1.0000
13.000 1.3998 0.02117 0.01559 0.0205 0.1755 1.0000
13.250 1.4010 0.02260 0.01705 0.0223 0.1672 1.0000
13.500 1.3987 0.02447 0.01894 0.0238 0.1591 1.0000
13.750 1.3969 0.02651 0.02101 0.0249 0.1509 1.0000
14.000 1.3920 0.02896 0.02349 0.0257 0.1427 1.0000
14.250 1.3836 0.03188 0.02643 0.0264 0.1350 1.0000
14.500 1.3793 0.03454 0.02916 0.0267 0.1288 1.0000
14.750 1.3686 0.03792 0.03256 0.0270 0.1225 1.0000
15.000 1.3619 0.04099 0.03570 0.0271 0.1174 1.0000
15.250 1.3498 0.04466 0.03941 0.0270 0.1116 1.0000
15.500 1.3399 0.04823 0.04304 0.0268 0.1073 1.0000
15.750 1.3289 0.05203 0.04689 0.0264 0.1019 1.0000
16.000 1.3162 0.05615 0.05105 0.0258 0.0978 1.0000
16.250 1.3095 0.05968 0.05465 0.0253 0.0935 1.0000
16.500 1.2969 0.06398 0.05899 0.0244 0.0885 1.0000
16.750 1.2878 0.06798 0.06304 0.0235 0.0844 1.0000
17.000 1.2784 0.07207 0.06717 0.0225 0.0794 1.0000
17.250 1.2684 0.07633 0.07147 0.0214 0.0759 1.0000
17.500 1.2632 0.08005 0.07525 0.0203 0.0720 1.0000
17.750 1.2560 0.08407 0.07933 0.0191 0.0685 1.0000
18.000 1.2487 0.08817 0.08346 0.0178 0.0651 1.0000
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