EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 500,000 Max Cl/Cd: 69.65 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e325-il-500000.txt Download as CSV file: xf-e325-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 325 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5910 0.08024 0.07807 -0.0155 1.0000 0.0141
-9.750 -0.6107 0.07473 0.07250 -0.0175 1.0000 0.0141
-9.500 -0.6296 0.07040 0.06809 -0.0172 1.0000 0.0141
-9.250 -0.6483 0.06655 0.06415 -0.0155 1.0000 0.0141
-9.000 -0.6634 0.06362 0.06114 -0.0125 1.0000 0.0141
-8.750 -0.6769 0.06108 0.05853 -0.0087 1.0000 0.0144
-8.500 -0.6843 0.05813 0.05546 -0.0057 1.0000 0.0145
-8.250 -0.6887 0.05505 0.05225 -0.0026 1.0000 0.0148
-8.000 -0.6911 0.05175 0.04879 0.0006 1.0000 0.0154
-7.750 -0.7134 0.04483 0.04109 0.0090 1.0000 0.0168
-7.500 -0.7036 0.04211 0.03841 0.0106 1.0000 0.0170
-7.250 -0.6941 0.04035 0.03662 0.0125 1.0000 0.0174
-7.000 -0.6845 0.03853 0.03471 0.0149 1.0000 0.0178
-6.750 -0.6750 0.03650 0.03252 0.0177 1.0000 0.0185
-6.500 -0.6755 0.03287 0.02829 0.0238 1.0000 0.0210
-6.250 -0.6400 0.03032 0.02568 0.0209 0.9649 0.0216
-6.000 -0.5950 0.02132 0.01548 0.0204 0.9177 0.0128
-5.750 -0.5619 0.01919 0.01294 0.0199 0.8560 0.0121
-5.500 -0.5369 0.01812 0.01153 0.0209 0.8141 0.0124
-5.250 -0.5126 0.01751 0.01063 0.0220 0.7811 0.0131
-5.000 -0.4845 0.01630 0.00924 0.0222 0.7543 0.0129
-4.750 -0.4585 0.01536 0.00815 0.0228 0.7310 0.0129
-4.500 -0.4350 0.01462 0.00729 0.0237 0.7095 0.0128
-4.250 -0.4130 0.01399 0.00653 0.0251 0.6897 0.0132
-4.000 -0.3933 0.01330 0.00574 0.0267 0.6721 0.0137
-3.750 -0.3723 0.01284 0.00521 0.0281 0.6555 0.0140
-3.500 -0.3509 0.01245 0.00474 0.0295 0.6397 0.0155
-3.000 -0.3094 0.01153 0.00377 0.0326 0.6102 0.0348
-2.750 -0.2936 0.01079 0.00342 0.0347 0.5972 0.1244
-2.500 -0.2841 0.00977 0.00305 0.0379 0.5859 0.2936
-2.250 -0.2966 0.00803 0.00250 0.0455 0.5767 0.5875
-2.000 -0.2940 0.00748 0.00285 0.0516 0.5663 0.8069
-1.750 -0.2718 0.00802 0.00336 0.0538 0.5547 0.8458
-1.500 -0.2447 0.00855 0.00381 0.0548 0.5433 0.8622
-1.250 -0.2102 0.00923 0.00442 0.0545 0.5311 0.8732
-1.000 -0.1788 0.00978 0.00489 0.0547 0.5198 0.8829
-0.750 -0.1350 0.01048 0.00549 0.0523 0.5082 0.8875
-0.500 -0.1077 0.01092 0.00583 0.0530 0.4980 0.8967
-0.250 -0.0604 0.01139 0.00619 0.0495 0.4864 0.8984
0.000 -0.0287 0.01144 0.00615 0.0487 0.4771 0.8994
0.250 0.0028 0.01147 0.00610 0.0480 0.4676 0.9004
0.500 0.0329 0.01149 0.00605 0.0474 0.4587 0.9016
0.750 0.0613 0.01152 0.00599 0.0472 0.4502 0.9031
1.000 0.0862 0.01147 0.00591 0.0477 0.4427 0.9052
1.250 0.0833 0.01113 0.00553 0.0537 0.4372 0.9120
1.500 0.1127 0.01112 0.00546 0.0533 0.4296 0.9128
1.750 0.1420 0.01111 0.00541 0.0529 0.4218 0.9136
2.000 0.1713 0.01115 0.00539 0.0525 0.4151 0.9145
2.250 0.2000 0.01115 0.00537 0.0522 0.4079 0.9154
2.500 0.2273 0.01120 0.00534 0.0521 0.4012 0.9164
2.750 0.2557 0.01119 0.00535 0.0519 0.3948 0.9176
3.000 0.2818 0.01121 0.00533 0.0521 0.3885 0.9190
3.250 0.3051 0.01119 0.00529 0.0528 0.3826 0.9207
3.500 0.3256 0.01113 0.00523 0.0541 0.3769 0.9231
3.750 0.3357 0.01100 0.00506 0.0575 0.3722 0.9267
4.000 0.3610 0.01097 0.00504 0.0578 0.3666 0.9278
4.250 0.3888 0.01097 0.00505 0.0576 0.3604 0.9286
4.500 0.4166 0.01108 0.00511 0.0574 0.3545 0.9295
4.750 0.4452 0.01109 0.00517 0.0571 0.3483 0.9305
5.000 0.4721 0.01116 0.00522 0.0570 0.3421 0.9315
5.250 0.4984 0.01122 0.00529 0.0571 0.3363 0.9326
5.500 0.5243 0.01125 0.00535 0.0573 0.3303 0.9339
5.750 0.5484 0.01136 0.00542 0.0578 0.3243 0.9354
6.000 0.5729 0.01134 0.00548 0.0582 0.3186 0.9370
6.250 0.5952 0.01138 0.00553 0.0591 0.3126 0.9391
6.500 0.6144 0.01143 0.00559 0.0605 0.3070 0.9418
6.750 0.6396 0.01145 0.00566 0.0608 0.3004 0.9431
7.000 0.6663 0.01159 0.00578 0.0607 0.2937 0.9441
7.250 0.6941 0.01164 0.00592 0.0604 0.2864 0.9451
7.500 0.7202 0.01181 0.00607 0.0604 0.2787 0.9463
7.750 0.7473 0.01188 0.00622 0.0603 0.2704 0.9476
8.000 0.7725 0.01205 0.00640 0.0604 0.2628 0.9492
8.250 0.7977 0.01216 0.00657 0.0606 0.2543 0.9509
8.500 0.8205 0.01230 0.00674 0.0612 0.2458 0.9532
8.750 0.8389 0.01244 0.00691 0.0627 0.2371 0.9565
9.000 0.8645 0.01262 0.00713 0.0627 0.2268 0.9581
9.250 0.8918 0.01288 0.00742 0.0622 0.2149 0.9594
9.500 0.9183 0.01319 0.00774 0.0618 0.2013 0.9608
9.750 0.9437 0.01355 0.00810 0.0616 0.1867 0.9625
10.000 0.9672 0.01398 0.00851 0.0617 0.1701 0.9647
10.250 0.9864 0.01448 0.00897 0.0625 0.1523 0.9679
10.500 1.0033 0.01502 0.00947 0.0637 0.1358 0.9715
10.750 1.0293 0.01573 0.01015 0.0628 0.1176 0.9730
11.000 1.0537 0.01656 0.01094 0.0620 0.1007 0.9747
11.250 1.0768 0.01748 0.01183 0.0612 0.0854 0.9769
11.500 1.0972 0.01839 0.01273 0.0610 0.0726 0.9802
11.750 1.1151 0.01938 0.01373 0.0610 0.0622 0.9841
12.000 1.1357 0.02055 0.01491 0.0600 0.0528 0.9866
12.250 1.1515 0.02189 0.01627 0.0593 0.0447 0.9907
12.500 1.1656 0.02350 0.01793 0.0580 0.0380 0.9951
12.750 1.1824 0.02544 0.01994 0.0554 0.0325 0.9990
13.000 1.1575 0.02687 0.02141 0.0605 0.0317 1.0000
13.250 1.1392 0.02923 0.02383 0.0632 0.0308 1.0000
13.500 1.1392 0.03114 0.02579 0.0638 0.0276 1.0000
13.750 1.1291 0.03435 0.02909 0.0638 0.0266 1.0000
14.000 1.1169 0.03803 0.03284 0.0634 0.0254 1.0000
14.250 1.1166 0.04055 0.03544 0.0631 0.0233 1.0000
14.500 1.1052 0.04441 0.03939 0.0623 0.0226 1.0000
14.750 1.0943 0.04827 0.04328 0.0613 0.0209 1.0000
15.000 1.0812 0.05250 0.04762 0.0602 0.0209 1.0000
15.250 1.0823 0.05509 0.05027 0.0595 0.0187 1.0000
15.500 1.0730 0.05902 0.05427 0.0583 0.0178 1.0000
15.750 1.0619 0.06337 0.05869 0.0569 0.0174 1.0000
16.000 1.0475 0.06832 0.06373 0.0551 0.0171 1.0000
16.250 1.0335 0.07331 0.06879 0.0532 0.0167 1.0000
16.500 1.0228 0.07795 0.07353 0.0515 0.0168 1.0000
16.750 1.0216 0.08138 0.07706 0.0502 0.0159 1.0000
17.000 1.0186 0.08514 0.08088 0.0486 0.0146 1.0000
17.250 1.0097 0.08978 0.08560 0.0467 0.0144 1.0000
17.500 1.0014 0.09444 0.09032 0.0447 0.0139 1.0000
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