EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 500,000 Max Cl/Cd: 88.27 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e342-il-500000.txt Download as CSV file: xf-e342-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3737 0.08738 0.08530 -0.0330 1.0000 0.0172
-9.500 -0.3752 0.08360 0.08155 -0.0345 1.0000 0.0173
-9.250 -0.3860 0.07744 0.07540 -0.0401 1.0000 0.0173
-9.000 -0.3923 0.07434 0.07231 -0.0405 1.0000 0.0174
-8.750 -0.3680 0.06710 0.06492 -0.0523 0.9161 0.0175
-8.500 -0.3605 0.06322 0.06055 -0.0556 0.8117 0.0177
-8.250 -0.3747 0.06083 0.05792 -0.0523 0.7711 0.0178
-8.000 -0.3820 0.05852 0.05542 -0.0496 0.7419 0.0180
-7.750 -0.3854 0.05587 0.05258 -0.0473 0.7199 0.0181
-7.500 -0.3859 0.05323 0.04976 -0.0450 0.7013 0.0184
-7.250 -0.3845 0.05048 0.04682 -0.0427 0.6848 0.0188
-7.000 -0.3823 0.04727 0.04337 -0.0399 0.6706 0.0196
-6.750 -0.3890 0.04152 0.03705 -0.0344 0.6610 0.0207
-6.500 -0.3777 0.03961 0.03504 -0.0329 0.6471 0.0210
-6.250 -0.3654 0.03797 0.03327 -0.0311 0.6339 0.0212
-6.000 -0.3521 0.03627 0.03142 -0.0293 0.6213 0.0217
-5.750 -0.3381 0.03442 0.02938 -0.0273 0.6097 0.0223
-5.500 -0.3303 0.03101 0.02532 -0.0226 0.6005 0.0248
-5.250 -0.3117 0.02938 0.02365 -0.0216 0.5888 0.0252
-5.000 -0.2930 0.02803 0.02215 -0.0202 0.5784 0.0258
-4.750 -0.2736 0.02666 0.02057 -0.0186 0.5682 0.0272
-4.500 -0.2500 0.01902 0.01169 -0.0138 0.5623 0.0138
-4.250 -0.2227 0.01739 0.00992 -0.0135 0.5524 0.0133
-4.000 -0.1943 0.01601 0.00832 -0.0132 0.5432 0.0128
-3.750 -0.1674 0.01508 0.00724 -0.0127 0.5338 0.0125
-3.500 -0.1419 0.01438 0.00643 -0.0120 0.5252 0.0125
-3.250 -0.1178 0.01380 0.00576 -0.0111 0.5163 0.0128
-3.000 -0.0942 0.01334 0.00524 -0.0101 0.5084 0.0132
-2.750 -0.0707 0.01297 0.00478 -0.0090 0.5007 0.0140
-2.500 -0.0484 0.01255 0.00435 -0.0078 0.4938 0.0159
-2.250 -0.0250 0.01222 0.00399 -0.0068 0.4867 0.0180
-2.000 -0.0016 0.01199 0.00370 -0.0058 0.4801 0.0216
-1.750 0.0214 0.01164 0.00341 -0.0047 0.4738 0.0369
-1.500 0.0423 0.01120 0.00324 -0.0033 0.4675 0.1001
-1.250 0.0530 0.01022 0.00303 -0.0004 0.4623 0.3260
-1.000 0.0414 0.00849 0.00336 0.0081 0.4588 0.8345
-0.750 0.0598 0.00915 0.00400 0.0113 0.4535 0.8879
-0.500 0.0928 0.01013 0.00487 0.0117 0.4479 0.9089
-0.250 0.2027 0.01157 0.00612 -0.0037 0.4390 0.9159
0.000 0.2589 0.01220 0.00660 -0.0088 0.4327 0.9261
0.250 0.3240 0.01267 0.00693 -0.0159 0.4266 0.9319
0.500 0.3406 0.01280 0.00703 -0.0135 0.4227 0.9393
0.750 0.3764 0.01274 0.00690 -0.0153 0.4182 0.9403
1.000 0.4106 0.01276 0.00680 -0.0167 0.4138 0.9416
1.250 0.4433 0.01274 0.00675 -0.0178 0.4097 0.9433
1.500 0.4740 0.01273 0.00671 -0.0185 0.4057 0.9453
1.750 0.5009 0.01275 0.00669 -0.0184 0.4022 0.9480
2.000 0.5146 0.01289 0.00678 -0.0156 0.3992 0.9527
2.250 0.5480 0.01288 0.00671 -0.0170 0.3952 0.9536
2.500 0.5812 0.01282 0.00665 -0.0182 0.3919 0.9548
2.750 0.6126 0.01279 0.00661 -0.0191 0.3883 0.9562
3.000 0.6418 0.01280 0.00659 -0.0196 0.3850 0.9577
3.250 0.6689 0.01287 0.00661 -0.0197 0.3818 0.9597
3.500 0.6921 0.01299 0.00669 -0.0189 0.3786 0.9619
3.750 0.7089 0.01307 0.00681 -0.0168 0.3761 0.9647
4.000 0.7414 0.01301 0.00676 -0.0180 0.3728 0.9655
4.250 0.7716 0.01299 0.00674 -0.0187 0.3695 0.9664
4.500 0.7999 0.01303 0.00675 -0.0191 0.3664 0.9674
4.750 0.8282 0.01316 0.00684 -0.0195 0.3629 0.9685
5.000 0.8558 0.01317 0.00691 -0.0197 0.3603 0.9700
5.250 0.8806 0.01320 0.00698 -0.0193 0.3573 0.9711
5.500 0.9039 0.01326 0.00705 -0.0186 0.3542 0.9724
5.750 0.9248 0.01337 0.00716 -0.0175 0.3513 0.9742
6.000 0.9423 0.01358 0.00734 -0.0156 0.3481 0.9754
6.250 0.9700 0.01359 0.00740 -0.0159 0.3453 0.9760
6.500 0.9983 0.01359 0.00746 -0.0164 0.3419 0.9766
6.750 1.0270 0.01362 0.00753 -0.0169 0.3384 0.9775
7.000 1.0529 0.01370 0.00762 -0.0168 0.3350 0.9783
7.250 1.0768 0.01389 0.00779 -0.0164 0.3313 0.9789
7.500 1.1006 0.01392 0.00792 -0.0160 0.3282 0.9797
7.750 1.1245 0.01398 0.00804 -0.0155 0.3243 0.9806
8.000 1.1483 0.01407 0.00817 -0.0151 0.3207 0.9817
8.250 1.1690 0.01427 0.00834 -0.0140 0.3167 0.9825
8.500 1.1892 0.01435 0.00852 -0.0128 0.3130 0.9833
8.750 1.2083 0.01443 0.00868 -0.0115 0.3090 0.9841
9.000 1.2248 0.01457 0.00885 -0.0095 0.3048 0.9852
9.250 1.2498 0.01475 0.00903 -0.0095 0.3001 0.9860
9.500 1.2744 0.01479 0.00920 -0.0093 0.2952 0.9866
9.750 1.2972 0.01491 0.00936 -0.0089 0.2900 0.9872
10.000 1.3187 0.01511 0.00958 -0.0082 0.2845 0.9879
10.250 1.3409 0.01522 0.00980 -0.0076 0.2784 0.9887
10.500 1.3602 0.01546 0.01004 -0.0065 0.2723 0.9897
10.750 1.3805 0.01564 0.01032 -0.0056 0.2660 0.9906
11.000 1.3990 0.01591 0.01062 -0.0045 0.2588 0.9919
11.250 1.4172 0.01618 0.01096 -0.0033 0.2515 0.9932
11.500 1.4307 0.01656 0.01134 -0.0013 0.2431 0.9944
11.750 1.4512 0.01688 0.01173 -0.0008 0.2334 0.9953
12.000 1.4680 0.01733 0.01221 0.0003 0.2231 0.9965
12.250 1.4787 0.01787 0.01275 0.0023 0.2122 0.9982
12.500 1.4868 0.01851 0.01340 0.0045 0.2016 1.0000
12.750 1.4772 0.01903 0.01396 0.0103 0.1941 1.0000
13.000 1.4600 0.01983 0.01477 0.0169 0.1877 1.0000
13.250 1.4471 0.02062 0.01561 0.0223 0.1813 1.0000
13.500 1.4268 0.02166 0.01669 0.0284 0.1762 1.0000
13.750 1.4062 0.02287 0.01792 0.0341 0.1715 1.0000
14.000 1.3953 0.02450 0.01958 0.0373 0.1642 1.0000
14.250 1.3877 0.02666 0.02176 0.0389 0.1559 1.0000
14.750 1.3709 0.03211 0.02726 0.0405 0.1396 1.0000
15.000 1.3596 0.03538 0.03056 0.0408 0.1335 1.0000
15.250 1.3487 0.03873 0.03395 0.0409 0.1258 1.0000
15.500 1.3356 0.04240 0.03766 0.0408 0.1205 1.0000
15.750 1.3237 0.04603 0.04134 0.0406 0.1142 1.0000
16.000 1.3080 0.05022 0.04557 0.0401 0.1096 1.0000
16.250 1.2975 0.05400 0.04940 0.0395 0.1036 1.0000
16.500 1.2818 0.05850 0.05392 0.0386 0.0989 1.0000
16.750 1.2737 0.06221 0.05770 0.0378 0.0943 1.0000
17.000 1.2604 0.06667 0.06218 0.0366 0.0894 1.0000
17.250 1.2512 0.07071 0.06628 0.0355 0.0856 1.0000
17.500 1.2417 0.07486 0.07047 0.0343 0.0808 1.0000
17.750 1.2297 0.07944 0.07506 0.0329 0.0770 1.0000
18.000 1.2235 0.08335 0.07904 0.0316 0.0722 1.0000
18.250 1.2137 0.08778 0.08349 0.0300 0.0690 1.0000
18.500 1.2084 0.09166 0.08744 0.0286 0.0655 1.0000
18.750 1.2010 0.09594 0.09176 0.0270 0.0620 1.0000
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