EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 500,000 Max Cl/Cd: 83.67 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e342-il-500000-n5.txt Download as CSV file: xf-e342-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 342 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3168 0.08635 0.08302 -0.0426 0.6748 0.0122
-9.250 -0.2976 0.06274 0.05947 -0.0460 0.6267 0.0087
-8.750 -0.3970 0.06084 0.05726 -0.0526 0.6410 0.0087
-8.500 -0.4077 0.05873 0.05506 -0.0499 0.6299 0.0086
-8.250 -0.4162 0.05636 0.05258 -0.0471 0.6195 0.0085
-8.000 -0.4213 0.05342 0.04951 -0.0447 0.6095 0.0083
-7.750 -0.4227 0.05050 0.04641 -0.0422 0.5996 0.0082
-7.250 -0.4545 0.03492 0.02997 -0.0309 0.5904 0.0064
-6.750 -0.4475 0.02651 0.02065 -0.0232 0.5740 0.0062
-6.500 -0.4348 0.02345 0.01710 -0.0204 0.5648 0.0061
-6.250 -0.4162 0.02118 0.01442 -0.0186 0.5560 0.0060
-6.000 -0.3943 0.01963 0.01253 -0.0173 0.5472 0.0060
-5.750 -0.3704 0.01845 0.01112 -0.0165 0.5382 0.0060
-5.500 -0.3460 0.01740 0.00984 -0.0157 0.5294 0.0061
-5.250 -0.3210 0.01657 0.00884 -0.0150 0.5202 0.0061
-5.000 -0.2964 0.01589 0.00801 -0.0143 0.5116 0.0061
-4.750 -0.2717 0.01532 0.00733 -0.0136 0.5031 0.0062
-4.500 -0.2475 0.01477 0.00666 -0.0128 0.4954 0.0063
-4.250 -0.2231 0.01431 0.00613 -0.0120 0.4882 0.0064
-4.000 -0.1998 0.01381 0.00554 -0.0110 0.4810 0.0067
-3.750 -0.1757 0.01347 0.00514 -0.0102 0.4746 0.0068
-3.500 -0.1516 0.01317 0.00479 -0.0094 0.4675 0.0070
-3.250 -0.1275 0.01291 0.00447 -0.0086 0.4608 0.0076
-3.000 -0.1029 0.01267 0.00419 -0.0079 0.4541 0.0080
-2.750 -0.0786 0.01246 0.00391 -0.0071 0.4481 0.0089
-2.500 -0.0543 0.01226 0.00367 -0.0063 0.4429 0.0104
-2.250 -0.0296 0.01207 0.00346 -0.0056 0.4375 0.0120
-2.000 -0.0050 0.01192 0.00328 -0.0049 0.4321 0.0146
-1.750 0.0195 0.01178 0.00313 -0.0042 0.4272 0.0213
-1.500 0.0435 0.01156 0.00301 -0.0034 0.4222 0.0417
-1.250 0.0671 0.01136 0.00291 -0.0026 0.4169 0.0725
-0.750 0.0959 0.00984 0.00260 0.0021 0.4094 0.4253
-0.500 0.0895 0.00862 0.00305 0.0099 0.4066 0.8506
-0.250 0.1087 0.00880 0.00316 0.0121 0.4026 0.8767
0.000 0.1337 0.00911 0.00340 0.0131 0.3986 0.8901
0.250 0.1648 0.00960 0.00383 0.0132 0.3947 0.9012
0.500 0.1910 0.00989 0.00407 0.0140 0.3907 0.9102
0.750 0.2320 0.01035 0.00447 0.0119 0.3862 0.9153
1.000 0.2585 0.01049 0.00453 0.0123 0.3827 0.9192
1.250 0.2721 0.01044 0.00442 0.0151 0.3798 0.9233
1.500 0.2992 0.01044 0.00439 0.0153 0.3768 0.9242
1.750 0.3274 0.01047 0.00437 0.0151 0.3735 0.9249
2.000 0.3548 0.01051 0.00436 0.0152 0.3698 0.9257
2.250 0.3819 0.01056 0.00437 0.0153 0.3666 0.9265
2.500 0.4086 0.01064 0.00439 0.0154 0.3637 0.9274
2.750 0.4351 0.01067 0.00440 0.0156 0.3611 0.9283
3.000 0.4613 0.01070 0.00442 0.0158 0.3581 0.9293
3.250 0.4871 0.01075 0.00444 0.0162 0.3548 0.9305
3.500 0.5118 0.01079 0.00446 0.0167 0.3521 0.9317
3.750 0.5356 0.01085 0.00448 0.0174 0.3493 0.9329
4.000 0.5590 0.01089 0.00451 0.0181 0.3466 0.9342
4.250 0.5827 0.01091 0.00454 0.0188 0.3441 0.9357
4.500 0.6058 0.01094 0.00457 0.0196 0.3414 0.9372
4.750 0.6289 0.01098 0.00460 0.0204 0.3386 0.9384
5.000 0.6542 0.01104 0.00466 0.0207 0.3357 0.9391
5.250 0.6799 0.01114 0.00474 0.0209 0.3327 0.9397
5.500 0.7060 0.01122 0.00483 0.0210 0.3302 0.9403
5.750 0.7322 0.01129 0.00492 0.0211 0.3272 0.9410
6.000 0.7580 0.01137 0.00503 0.0213 0.3244 0.9417
6.250 0.7834 0.01147 0.00514 0.0216 0.3214 0.9427
6.500 0.8081 0.01159 0.00526 0.0220 0.3184 0.9437
6.750 0.8324 0.01171 0.00539 0.0224 0.3153 0.9446
7.000 0.8576 0.01179 0.00552 0.0226 0.3124 0.9456
7.250 0.8822 0.01188 0.00565 0.0230 0.3092 0.9466
7.500 0.9061 0.01199 0.00578 0.0234 0.3055 0.9477
7.750 0.9291 0.01213 0.00592 0.0240 0.3021 0.9488
8.000 0.9529 0.01225 0.00608 0.0245 0.2987 0.9500
8.250 0.9768 0.01235 0.00623 0.0249 0.2947 0.9511
8.500 0.9997 0.01248 0.00640 0.0255 0.2907 0.9522
8.750 1.0224 0.01266 0.00658 0.0260 0.2865 0.9531
9.000 1.0467 0.01280 0.00679 0.0264 0.2824 0.9540
9.250 1.0700 0.01296 0.00700 0.0268 0.2773 0.9552
9.500 1.0912 0.01318 0.00723 0.0276 0.2720 0.9568
9.750 1.1139 0.01335 0.00747 0.0281 0.2671 0.9581
10.000 1.1346 0.01356 0.00771 0.0290 0.2606 0.9597
10.250 1.1539 0.01381 0.00798 0.0300 0.2547 0.9615
10.500 1.1717 0.01402 0.00825 0.0314 0.2474 0.9635
10.750 1.1887 0.01433 0.00858 0.0328 0.2405 0.9654
11.000 1.2071 0.01469 0.00897 0.0338 0.2317 0.9672
11.250 1.2247 0.01511 0.00942 0.0348 0.2229 0.9693
11.500 1.2403 0.01564 0.00996 0.0360 0.2138 0.9719
11.750 1.2565 0.01617 0.01052 0.0370 0.2045 0.9746
12.000 1.2738 0.01685 0.01122 0.0374 0.1944 0.9769
12.250 1.2899 0.01772 0.01210 0.0377 0.1835 0.9794
12.500 1.3036 0.01878 0.01317 0.0379 0.1719 0.9830
12.750 1.3159 0.02004 0.01444 0.0378 0.1609 0.9871
13.000 1.3264 0.02153 0.01595 0.0375 0.1497 0.9921
13.250 1.3365 0.02331 0.01776 0.0367 0.1396 0.9964
13.500 1.3401 0.02551 0.01998 0.0361 0.1293 1.0000
13.750 1.3293 0.02768 0.02217 0.0383 0.1232 1.0000
14.000 1.3229 0.03006 0.02460 0.0394 0.1167 1.0000
14.250 1.3153 0.03284 0.02741 0.0400 0.1113 1.0000
14.500 1.3074 0.03580 0.03042 0.0403 0.1052 1.0000
14.750 1.2972 0.03911 0.03377 0.0404 0.1001 1.0000
15.000 1.2884 0.04238 0.03710 0.0404 0.0955 1.0000
15.250 1.2748 0.04621 0.04096 0.0401 0.0897 1.0000
15.500 1.2647 0.04981 0.04462 0.0398 0.0865 1.0000
15.750 1.2537 0.05361 0.04848 0.0392 0.0811 1.0000
16.000 1.2435 0.05748 0.05240 0.0385 0.0780 1.0000
16.250 1.2338 0.06138 0.05635 0.0377 0.0732 1.0000
16.500 1.2244 0.06534 0.06036 0.0367 0.0695 1.0000
16.750 1.2158 0.06932 0.06438 0.0357 0.0667 1.0000
17.000 1.2099 0.07301 0.06814 0.0346 0.0632 1.0000
17.250 1.2015 0.07708 0.07224 0.0334 0.0598 1.0000
17.500 1.1946 0.08107 0.07629 0.0322 0.0565 1.0000
17.750 1.1897 0.08484 0.08011 0.0309 0.0539 1.0000
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Polar data table (+)
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