EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 200,000 Max Cl/Cd: 65.82 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e344-il-200000-n5.txt Download as CSV file: xf-e344-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 344 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2780 0.11791 0.11441 -0.0322 1.0000 0.0235
-10.750 -0.2771 0.11443 0.11097 -0.0338 1.0000 0.0236
-10.500 -0.2808 0.11026 0.10685 -0.0365 1.0000 0.0237
-10.250 -0.2784 0.10695 0.10359 -0.0375 1.0000 0.0237
-10.000 -0.2681 0.10304 0.09973 -0.0387 0.9939 0.0239
-9.750 -0.2155 0.09754 0.09406 -0.0488 0.8921 0.0256
-9.500 -0.1790 0.09104 0.08726 -0.0605 0.8276 0.0266
-9.250 -0.1809 0.08534 0.08142 -0.0680 0.7901 0.0282
-9.000 -0.1888 0.07993 0.07590 -0.0740 0.7624 0.0284
-8.750 -0.1937 0.07594 0.07178 -0.0767 0.7394 0.0284
-8.500 -0.2071 0.07214 0.06783 -0.0778 0.7213 0.0285
-8.000 -0.2155 0.06637 0.06190 -0.0754 0.6900 0.0287
-7.750 -0.2148 0.06384 0.05928 -0.0743 0.6762 0.0289
-7.000 -0.2097 0.05606 0.05114 -0.0706 0.6403 0.0296
-6.500 -0.2102 0.04648 0.04094 -0.0659 0.6239 0.0194
-6.000 -0.1986 0.03883 0.03263 -0.0606 0.6067 0.0160
-5.750 -0.1861 0.03676 0.03035 -0.0588 0.5975 0.0158
-5.500 -0.1723 0.03462 0.02797 -0.0569 0.5890 0.0155
-5.250 -0.1578 0.03224 0.02528 -0.0548 0.5808 0.0152
-5.000 -0.1419 0.02971 0.02240 -0.0526 0.5731 0.0148
-4.750 -0.1242 0.02721 0.01948 -0.0505 0.5651 0.0145
-4.500 -0.1041 0.02498 0.01682 -0.0487 0.5574 0.0143
-4.250 -0.0815 0.02314 0.01460 -0.0473 0.5493 0.0142
-4.000 -0.0574 0.02167 0.01280 -0.0462 0.5420 0.0143
-3.750 -0.0318 0.02045 0.01132 -0.0455 0.5343 0.0145
-3.500 -0.0061 0.01944 0.01007 -0.0447 0.5276 0.0148
-3.250 0.0198 0.01858 0.00906 -0.0441 0.5207 0.0152
-3.000 0.0450 0.01781 0.00813 -0.0433 0.5140 0.0159
-2.750 0.0691 0.01724 0.00748 -0.0425 0.5078 0.0165
-2.500 0.0932 0.01683 0.00705 -0.0418 0.5011 0.0175
-2.250 0.1170 0.01650 0.00662 -0.0409 0.4952 0.0201
-2.000 0.1407 0.01617 0.00627 -0.0401 0.4896 0.0218
-1.750 0.1641 0.01581 0.00584 -0.0391 0.4841 0.0239
-1.500 0.1873 0.01553 0.00550 -0.0381 0.4791 0.0269
-1.250 0.2110 0.01530 0.00524 -0.0372 0.4745 0.0345
-1.000 0.2343 0.01501 0.00499 -0.0363 0.4692 0.0494
-0.750 0.2565 0.01469 0.00481 -0.0352 0.4644 0.0935
-0.500 0.2681 0.01286 0.00572 -0.0309 0.4608 0.8369
-0.250 0.2751 0.01328 0.00607 -0.0257 0.4567 0.8898
0.000 0.3226 0.01409 0.00673 -0.0281 0.4515 0.9193
0.250 0.4272 0.01487 0.00718 -0.0424 0.4452 0.9439
0.500 0.4526 0.01497 0.00717 -0.0419 0.4412 0.9502
0.750 0.4815 0.01497 0.00709 -0.0422 0.4368 0.9520
1.000 0.5120 0.01499 0.00700 -0.0430 0.4327 0.9536
1.250 0.5408 0.01504 0.00693 -0.0433 0.4294 0.9553
1.500 0.5683 0.01510 0.00690 -0.0435 0.4262 0.9573
1.750 0.5938 0.01514 0.00692 -0.0432 0.4228 0.9595
2.000 0.6164 0.01521 0.00694 -0.0422 0.4193 0.9620
2.250 0.6397 0.01529 0.00695 -0.0415 0.4160 0.9640
2.500 0.6685 0.01536 0.00694 -0.0420 0.4130 0.9651
2.750 0.6971 0.01545 0.00698 -0.0424 0.4099 0.9664
3.000 0.7240 0.01552 0.00706 -0.0424 0.4068 0.9677
3.250 0.7500 0.01561 0.00713 -0.0423 0.4035 0.9692
3.500 0.7755 0.01571 0.00721 -0.0421 0.4004 0.9709
3.750 0.7990 0.01584 0.00728 -0.0415 0.3978 0.9725
4.000 0.8213 0.01599 0.00739 -0.0406 0.3954 0.9740
4.250 0.8459 0.01611 0.00755 -0.0403 0.3925 0.9756
4.500 0.8731 0.01622 0.00770 -0.0405 0.3893 0.9766
4.750 0.8989 0.01635 0.00783 -0.0404 0.3862 0.9775
5.000 0.9243 0.01649 0.00796 -0.0402 0.3835 0.9785
5.250 0.9504 0.01666 0.00811 -0.0402 0.3810 0.9798
5.500 0.9755 0.01683 0.00831 -0.0400 0.3782 0.9813
5.750 0.9986 0.01700 0.00855 -0.0395 0.3752 0.9826
6.000 1.0210 0.01718 0.00877 -0.0387 0.3722 0.9839
6.250 1.0427 0.01736 0.00899 -0.0379 0.3694 0.9852
6.500 1.0681 0.01754 0.00917 -0.0378 0.3666 0.9861
6.750 1.0951 0.01775 0.00936 -0.0381 0.3640 0.9871
7.000 1.1203 0.01796 0.00970 -0.0381 0.3608 0.9885
7.250 1.1439 0.01817 0.01000 -0.0377 0.3574 0.9897
7.500 1.1671 0.01838 0.01026 -0.0373 0.3542 0.9909
7.750 1.1903 0.01860 0.01051 -0.0369 0.3513 0.9922
8.000 1.2135 0.01884 0.01075 -0.0364 0.3484 0.9934
8.250 1.2350 0.01911 0.01117 -0.0358 0.3449 0.9948
8.500 1.2581 0.01936 0.01153 -0.0355 0.3411 0.9962
8.750 1.2821 0.01960 0.01184 -0.0353 0.3376 0.9979
9.000 1.3065 0.01985 0.01209 -0.0352 0.3343 0.9994
9.250 1.3215 0.02015 0.01253 -0.0333 0.3307 1.0000
9.500 1.3313 0.02043 0.01293 -0.0304 0.3269 1.0000
9.750 1.3403 0.02067 0.01324 -0.0274 0.3232 1.0000
10.000 1.3493 0.02090 0.01349 -0.0243 0.3201 1.0000
10.250 1.3545 0.02116 0.01384 -0.0205 0.3166 1.0000
10.500 1.3551 0.02143 0.01425 -0.0160 0.3127 1.0000
10.750 1.3521 0.02163 0.01452 -0.0108 0.3092 1.0000
11.000 1.3543 0.02185 0.01475 -0.0067 0.3056 1.0000
11.250 1.3605 0.02223 0.01522 -0.0037 0.3013 1.0000
11.500 1.3679 0.02271 0.01584 -0.0012 0.2962 1.0000
11.750 1.3771 0.02319 0.01635 0.0010 0.2912 1.0000
12.000 1.3854 0.02384 0.01711 0.0029 0.2858 1.0000
12.250 1.3931 0.02458 0.01795 0.0048 0.2802 1.0000
12.500 1.4005 0.02538 0.01879 0.0064 0.2750 1.0000
12.750 1.4056 0.02647 0.02003 0.0080 0.2685 1.0000
13.000 1.4100 0.02763 0.02123 0.0094 0.2626 1.0000
13.250 1.4127 0.02908 0.02281 0.0106 0.2557 1.0000
13.500 1.4140 0.03071 0.02448 0.0117 0.2491 1.0000
13.750 1.4135 0.03264 0.02651 0.0126 0.2418 1.0000
14.000 1.4108 0.03483 0.02874 0.0133 0.2349 1.0000
14.250 1.4074 0.03728 0.03131 0.0138 0.2274 1.0000
14.500 1.3999 0.04015 0.03419 0.0141 0.2196 1.0000
14.750 1.3926 0.04322 0.03735 0.0142 0.2119 1.0000
15.000 1.3829 0.04657 0.04074 0.0142 0.2046 1.0000
15.250 1.3735 0.05008 0.04432 0.0139 0.1973 1.0000
15.500 1.3626 0.05384 0.04813 0.0135 0.1902 1.0000
15.750 1.3514 0.05779 0.05213 0.0129 0.1828 1.0000
16.000 1.3416 0.06172 0.05611 0.0122 0.1759 1.0000
16.250 1.3309 0.06583 0.06026 0.0113 0.1690 1.0000
16.500 1.3206 0.07006 0.06454 0.0103 0.1618 1.0000
16.750 1.3112 0.07421 0.06872 0.0092 0.1554 1.0000
17.000 1.3026 0.07839 0.07297 0.0081 0.1487 1.0000
17.250 1.2936 0.08267 0.07727 0.0068 0.1424 1.0000
17.500 1.2865 0.08682 0.08149 0.0055 0.1360 1.0000
17.750 1.2782 0.09112 0.08580 0.0040 0.1299 1.0000
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