EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.19 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e340-il-1000000.txt Download as CSV file: xf-e340-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 340 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5680 0.08503 0.08362 -0.0018 1.0000 0.0087
-9.750 -0.5828 0.07690 0.07544 -0.0086 1.0000 0.0087
-9.500 -0.6001 0.07074 0.06919 -0.0107 1.0000 0.0087
-9.250 -0.6246 0.06712 0.06510 -0.0074 0.8212 0.0087
-9.000 -0.6615 0.06058 0.05828 -0.0045 0.7883 0.0088
-8.750 -0.6760 0.05721 0.05468 -0.0015 0.7587 0.0089
-8.500 -0.6785 0.05424 0.05151 0.0006 0.7341 0.0090
-5.750 -0.5631 0.01850 0.01213 0.0275 0.5794 0.0089
-5.500 -0.5371 0.01775 0.01122 0.0281 0.5678 0.0088
-5.250 -0.5105 0.01673 0.01004 0.0284 0.5562 0.0088
-5.000 -0.4836 0.01602 0.00922 0.0288 0.5450 0.0088
-4.750 -0.4563 0.01494 0.00807 0.0290 0.5343 0.0086
-4.250 -0.4047 0.01326 0.00621 0.0300 0.5137 0.0084
-4.000 -0.3798 0.01270 0.00557 0.0307 0.5044 0.0084
-3.750 -0.3549 0.01222 0.00503 0.0314 0.4954 0.0084
-3.500 -0.3300 0.01182 0.00456 0.0321 0.4869 0.0085
-3.250 -0.3047 0.01148 0.00416 0.0327 0.4781 0.0086
-3.000 -0.2801 0.01109 0.00370 0.0334 0.4699 0.0089
-2.750 -0.2547 0.01077 0.00335 0.0340 0.4619 0.0095
-2.500 -0.2286 0.01058 0.00310 0.0344 0.4543 0.0107
-2.250 -0.2030 0.01032 0.00282 0.0350 0.4475 0.0145
-2.000 -0.1789 0.00998 0.00258 0.0358 0.4404 0.0420
-1.750 -0.1544 0.00968 0.00244 0.0364 0.4344 0.0835
-1.500 -0.1304 0.00938 0.00231 0.0371 0.4278 0.1396
-1.250 -0.1141 0.00859 0.00211 0.0391 0.4218 0.3145
-1.000 -0.1171 0.00707 0.00176 0.0449 0.4180 0.6221
-0.750 -0.1169 0.00632 0.00196 0.0513 0.4138 0.8610
-0.500 -0.0917 0.00689 0.00252 0.0527 0.4079 0.8933
-0.250 -0.0611 0.00744 0.00304 0.0528 0.4027 0.9038
0.000 -0.0312 0.00784 0.00340 0.0529 0.3972 0.9103
0.250 -0.0004 0.00828 0.00376 0.0527 0.3914 0.9156
0.500 0.0438 0.00893 0.00437 0.0501 0.3867 0.9181
0.750 0.0892 0.00942 0.00480 0.0469 0.3816 0.9198
1.000 0.1258 0.00965 0.00495 0.0452 0.3767 0.9214
1.250 0.1496 0.00967 0.00494 0.0460 0.3727 0.9239
1.500 0.1593 0.00950 0.00475 0.0496 0.3697 0.9290
1.750 0.1898 0.00952 0.00473 0.0491 0.3654 0.9295
2.000 0.2198 0.00956 0.00472 0.0485 0.3610 0.9300
2.250 0.2498 0.00962 0.00473 0.0480 0.3570 0.9305
2.500 0.2803 0.00963 0.00474 0.0474 0.3541 0.9311
2.750 0.3107 0.00966 0.00475 0.0468 0.3507 0.9316
3.000 0.3406 0.00971 0.00476 0.0462 0.3473 0.9322
3.250 0.3695 0.00979 0.00480 0.0459 0.3432 0.9329
3.500 0.3975 0.00980 0.00481 0.0457 0.3402 0.9337
3.750 0.4255 0.00981 0.00482 0.0456 0.3373 0.9346
4.000 0.4509 0.00982 0.00482 0.0460 0.3339 0.9359
4.250 0.4712 0.00982 0.00480 0.0474 0.3308 0.9376
4.500 0.4743 0.00967 0.00463 0.0523 0.3281 0.9420
4.750 0.5018 0.00969 0.00465 0.0522 0.3252 0.9424
5.000 0.5306 0.00969 0.00467 0.0518 0.3225 0.9429
5.250 0.5588 0.00972 0.00471 0.0516 0.3194 0.9434
5.500 0.5859 0.00976 0.00475 0.0515 0.3161 0.9439
5.750 0.6121 0.00984 0.00481 0.0516 0.3118 0.9444
6.000 0.6388 0.00987 0.00485 0.0517 0.3088 0.9450
6.250 0.6656 0.00989 0.00490 0.0517 0.3059 0.9455
6.500 0.6918 0.00992 0.00495 0.0518 0.3024 0.9462
6.750 0.7176 0.01001 0.00502 0.0519 0.2985 0.9470
7.000 0.7421 0.01009 0.00511 0.0523 0.2944 0.9480
7.250 0.7669 0.01008 0.00514 0.0527 0.2910 0.9489
7.500 0.7904 0.01010 0.00518 0.0533 0.2873 0.9500
7.750 0.8130 0.01015 0.00522 0.0541 0.2833 0.9513
8.000 0.8360 0.01021 0.00530 0.0547 0.2790 0.9524
8.250 0.8615 0.01023 0.00536 0.0548 0.2747 0.9532
8.500 0.8869 0.01030 0.00544 0.0549 0.2693 0.9539
8.750 0.9120 0.01042 0.00556 0.0551 0.2643 0.9545
9.000 0.9383 0.01049 0.00568 0.0551 0.2593 0.9551
9.250 0.9633 0.01065 0.00583 0.0553 0.2524 0.9558
9.500 0.9889 0.01076 0.00598 0.0553 0.2463 0.9564
9.750 1.0137 0.01093 0.00615 0.0555 0.2393 0.9571
10.000 1.0383 0.01110 0.00634 0.0556 0.2316 0.9578
10.250 1.0618 0.01133 0.00656 0.0559 0.2229 0.9587
10.500 1.0860 0.01153 0.00677 0.0561 0.2145 0.9596
10.750 1.1088 0.01181 0.00705 0.0564 0.2042 0.9607
11.000 1.1308 0.01217 0.00737 0.0567 0.1916 0.9618
11.250 1.1526 0.01258 0.00774 0.0570 0.1781 0.9630
11.500 1.1739 0.01304 0.00817 0.0573 0.1644 0.9640
11.750 1.1914 0.01355 0.00863 0.0583 0.1498 0.9651
12.000 1.2071 0.01414 0.00919 0.0596 0.1355 0.9665
12.250 1.2208 0.01481 0.00981 0.0610 0.1215 0.9683
12.500 1.2336 0.01548 0.01045 0.0625 0.1100 0.9703
12.750 1.2434 0.01631 0.01124 0.0641 0.0968 0.9727
13.000 1.2486 0.01718 0.01211 0.0665 0.0883 0.9751
13.250 1.2559 0.01826 0.01319 0.0679 0.0796 0.9777
13.500 1.2631 0.01962 0.01457 0.0684 0.0714 0.9808
13.750 1.2703 0.02143 0.01638 0.0679 0.0634 0.9840
14.000 1.2741 0.02365 0.01862 0.0672 0.0571 0.9883
14.250 1.2816 0.02610 0.02112 0.0652 0.0513 0.9914
14.500 1.2865 0.02886 0.02393 0.0633 0.0466 0.9947
14.750 1.2890 0.03234 0.02745 0.0604 0.0419 0.9964
15.000 1.2928 0.03559 0.03078 0.0577 0.0386 0.9975
15.250 1.2892 0.03959 0.03484 0.0551 0.0355 0.9987
15.500 1.2865 0.04328 0.03862 0.0529 0.0332 0.9999
15.750 1.2710 0.04672 0.04212 0.0533 0.0317 1.0000
16.000 1.2583 0.05074 0.04620 0.0523 0.0300 1.0000
16.250 1.2472 0.05486 0.05039 0.0510 0.0284 1.0000
16.500 1.2385 0.05887 0.05447 0.0495 0.0268 1.0000
16.750 1.2282 0.06318 0.05884 0.0480 0.0253 1.0000
17.000 1.2178 0.06755 0.06326 0.0464 0.0240 1.0000
17.250 1.2114 0.07149 0.06728 0.0449 0.0227 1.0000
17.500 1.2033 0.07569 0.07153 0.0433 0.0213 1.0000
17.750 1.1932 0.08019 0.07609 0.0416 0.0201 1.0000
18.000 1.1859 0.08441 0.08038 0.0400 0.0191 1.0000
18.250 1.1796 0.08850 0.08453 0.0384 0.0180 1.0000
18.500 1.1704 0.09302 0.08911 0.0366 0.0171 1.0000
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