EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.7 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e340-il-1000000-n5.txt Download as CSV file: xf-e340-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6271 0.08265 0.08019 -0.0003 0.6564 0.0040
-10.000 -0.6564 0.07397 0.07142 -0.0057 0.6518 0.0040
-9.750 -0.6826 0.06796 0.06529 -0.0061 0.6440 0.0040
-9.500 -0.7084 0.06242 0.05960 -0.0040 0.6368 0.0040
-9.250 -0.7345 0.05622 0.05319 -0.0003 0.6298 0.0041
-9.000 -0.8424 0.02985 0.02541 0.0150 0.6486 0.0041
-8.750 -0.8338 0.02679 0.02193 0.0177 0.6353 0.0041
-8.500 -0.8197 0.02452 0.01930 0.0199 0.6213 0.0041
-8.250 -0.8013 0.02296 0.01746 0.0213 0.6067 0.0041
-8.000 -0.7816 0.02146 0.01571 0.0227 0.5931 0.0041
-7.750 -0.7597 0.02036 0.01439 0.0237 0.5799 0.0042
-7.500 -0.7366 0.01949 0.01334 0.0245 0.5685 0.0042
-7.250 -0.7129 0.01864 0.01233 0.0252 0.5574 0.0043
-7.000 -0.6885 0.01792 0.01147 0.0258 0.5472 0.0043
-6.750 -0.6636 0.01733 0.01075 0.0264 0.5367 0.0044
-6.500 -0.6385 0.01673 0.01002 0.0269 0.5251 0.0044
-6.250 -0.6133 0.01610 0.00927 0.0274 0.5152 0.0044
-6.000 -0.5886 0.01533 0.00836 0.0280 0.5056 0.0044
-5.750 -0.5637 0.01467 0.00761 0.0286 0.4972 0.0045
-5.500 -0.5391 0.01404 0.00687 0.0293 0.4887 0.0045
-5.250 -0.5141 0.01354 0.00630 0.0299 0.4809 0.0045
-4.750 -0.4639 0.01269 0.00530 0.0310 0.4649 0.0046
-4.250 -0.4130 0.01202 0.00452 0.0321 0.4493 0.0048
-4.000 -0.3872 0.01175 0.00421 0.0325 0.4420 0.0050
-3.750 -0.3612 0.01152 0.00393 0.0329 0.4360 0.0051
-3.500 -0.3352 0.01130 0.00368 0.0333 0.4296 0.0053
-3.000 -0.2828 0.01093 0.00322 0.0341 0.4170 0.0061
-2.750 -0.2566 0.01077 0.00302 0.0345 0.4104 0.0066
-2.500 -0.2305 0.01061 0.00285 0.0349 0.4050 0.0079
-2.250 -0.2041 0.01046 0.00269 0.0352 0.4001 0.0101
-2.000 -0.1777 0.01033 0.00255 0.0355 0.3948 0.0144
-1.750 -0.1517 0.01018 0.00242 0.0359 0.3898 0.0244
-1.500 -0.1257 0.01002 0.00231 0.0363 0.3853 0.0401
-1.250 -0.1004 0.00982 0.00221 0.0368 0.3799 0.0713
-1.000 -0.0763 0.00955 0.00211 0.0374 0.3750 0.1271
-0.750 -0.0645 0.00846 0.00188 0.0402 0.3720 0.3761
-0.500 -0.0866 0.00639 0.00149 0.0503 0.3703 0.7915
-0.250 -0.0630 0.00654 0.00186 0.0517 0.3661 0.8709
0.000 -0.0372 0.00668 0.00192 0.0523 0.3614 0.8832
0.250 -0.0083 0.00693 0.00215 0.0524 0.3572 0.8912
0.500 0.0178 0.00708 0.00225 0.0530 0.3540 0.8984
0.750 0.0479 0.00732 0.00248 0.0528 0.3505 0.9030
1.000 0.0766 0.00751 0.00263 0.0528 0.3469 0.9065
1.250 0.1042 0.00759 0.00266 0.0529 0.3433 0.9084
1.500 0.1319 0.00761 0.00264 0.0529 0.3403 0.9095
1.750 0.1597 0.00763 0.00262 0.0528 0.3370 0.9106
2.000 0.1874 0.00765 0.00260 0.0528 0.3332 0.9114
2.250 0.2151 0.00770 0.00260 0.0527 0.3293 0.9123
2.500 0.2429 0.00774 0.00260 0.0526 0.3260 0.9130
2.750 0.2712 0.00776 0.00260 0.0525 0.3238 0.9135
3.000 0.2995 0.00778 0.00261 0.0523 0.3212 0.9141
3.250 0.3277 0.00782 0.00263 0.0521 0.3183 0.9145
3.500 0.3559 0.00788 0.00266 0.0519 0.3148 0.9151
3.750 0.3838 0.00795 0.00272 0.0518 0.3111 0.9157
4.000 0.4121 0.00800 0.00276 0.0516 0.3086 0.9162
4.250 0.4403 0.00805 0.00281 0.0514 0.3056 0.9167
4.500 0.4684 0.00811 0.00286 0.0512 0.3026 0.9171
4.750 0.4964 0.00819 0.00293 0.0510 0.2996 0.9176
5.000 0.5242 0.00828 0.00300 0.0508 0.2960 0.9181
5.250 0.5523 0.00834 0.00307 0.0506 0.2934 0.9186
5.500 0.5804 0.00841 0.00314 0.0504 0.2904 0.9191
5.750 0.6083 0.00848 0.00322 0.0501 0.2866 0.9197
6.000 0.6359 0.00859 0.00332 0.0500 0.2823 0.9202
6.250 0.6637 0.00869 0.00341 0.0497 0.2789 0.9208
6.500 0.6916 0.00877 0.00352 0.0495 0.2754 0.9214
6.750 0.7193 0.00887 0.00362 0.0493 0.2709 0.9221
7.000 0.7466 0.00901 0.00375 0.0491 0.2657 0.9228
7.250 0.7744 0.00910 0.00386 0.0488 0.2611 0.9233
7.500 0.8020 0.00922 0.00399 0.0486 0.2563 0.9239
7.750 0.8291 0.00938 0.00414 0.0484 0.2508 0.9244
8.000 0.8567 0.00951 0.00428 0.0481 0.2456 0.9250
8.250 0.8836 0.00969 0.00445 0.0479 0.2377 0.9255
8.500 0.9108 0.00986 0.00463 0.0476 0.2312 0.9261
8.750 0.9374 0.01008 0.00483 0.0474 0.2235 0.9266
9.000 0.9642 0.01029 0.00504 0.0472 0.2151 0.9271
9.250 0.9901 0.01057 0.00530 0.0470 0.2049 0.9276
9.500 1.0158 0.01086 0.00557 0.0468 0.1949 0.9281
9.750 1.0408 0.01115 0.00585 0.0469 0.1848 0.9287
10.000 1.0646 0.01153 0.00620 0.0470 0.1723 0.9294
10.250 1.0883 0.01190 0.00656 0.0472 0.1621 0.9301
10.500 1.1109 0.01236 0.00698 0.0474 0.1493 0.9308
10.750 1.1322 0.01290 0.00748 0.0478 0.1346 0.9317
11.000 1.1527 0.01349 0.00802 0.0482 0.1203 0.9328
11.250 1.1727 0.01410 0.00859 0.0487 0.1074 0.9338
11.500 1.1918 0.01477 0.00921 0.0492 0.0952 0.9347
11.750 1.2099 0.01548 0.00989 0.0497 0.0836 0.9358
12.000 1.2264 0.01627 0.01065 0.0504 0.0726 0.9370
12.250 1.2399 0.01710 0.01145 0.0514 0.0631 0.9384
12.500 1.2531 0.01801 0.01236 0.0522 0.0558 0.9398
12.750 1.2640 0.01922 0.01356 0.0527 0.0478 0.9413
13.000 1.2721 0.02055 0.01492 0.0532 0.0424 0.9430
13.250 1.2791 0.02214 0.01657 0.0533 0.0381 0.9449
13.500 1.2835 0.02428 0.01875 0.0527 0.0337 0.9470
13.750 1.2867 0.02681 0.02133 0.0517 0.0296 0.9492
14.000 1.2897 0.02951 0.02409 0.0504 0.0265 0.9512
14.250 1.2890 0.03272 0.02736 0.0488 0.0237 0.9532
14.500 1.2845 0.03575 0.03047 0.0484 0.0217 0.9556
14.750 1.2760 0.03924 0.03404 0.0479 0.0200 0.9581
15.000 1.2695 0.04264 0.03753 0.0472 0.0188 0.9605
15.250 1.2616 0.04636 0.04133 0.0462 0.0175 0.9627
15.500 1.2490 0.04993 0.04498 0.0463 0.0168 0.9655
15.750 1.2273 0.05314 0.04828 0.0488 0.0163 0.9707
16.000 1.2097 0.05639 0.05161 0.0506 0.0158 0.9767
16.500 1.1930 0.06421 0.05958 0.0485 0.0139 0.9883
16.750 1.1847 0.06834 0.06376 0.0470 0.0131 0.9919
17.000 1.1783 0.07212 0.06762 0.0460 0.0125 0.9947
17.500 1.1660 0.08043 0.07606 0.0423 0.0108 0.9969
17.750 1.1602 0.08464 0.08034 0.0403 0.0102 0.9978
18.000 1.1547 0.08853 0.08430 0.0387 0.0096 0.9995
18.250 1.1485 0.09272 0.08855 0.0369 0.0091 1.0000
18.500 1.1425 0.09688 0.09278 0.0352 0.0087 1.0000
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