EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 331 AIRFOIL (e331-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.46 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e331-il-1000000-n5.txt Download as CSV file: xf-e331-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 331 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4590 0.08184 0.07947 -0.0165 0.7236 0.0046
-8.750 -0.4697 0.07691 0.07450 -0.0205 0.7055 0.0046
-8.500 -0.4813 0.07290 0.07041 -0.0221 0.6873 0.0046
-8.250 -0.4965 0.06921 0.06665 -0.0213 0.6741 0.0046
-6.750 -0.5072 0.03167 0.02840 -0.0086 0.5939 0.0028
-6.250 -0.5567 0.01953 0.01419 0.0065 0.6018 0.0028
-6.000 -0.5351 0.01796 0.01231 0.0078 0.5901 0.0028
-5.750 -0.5144 0.01589 0.00984 0.0092 0.5787 0.0032
-5.250 -0.4647 0.01467 0.00834 0.0105 0.5549 0.0034
-5.000 -0.4395 0.01413 0.00768 0.0110 0.5450 0.0036
-4.750 -0.4143 0.01353 0.00695 0.0117 0.5342 0.0037
-4.500 -0.3890 0.01301 0.00630 0.0123 0.5235 0.0038
-4.250 -0.3636 0.01255 0.00574 0.0129 0.5133 0.0040
-3.750 -0.3133 0.01169 0.00470 0.0141 0.4951 0.0042
-3.500 -0.2878 0.01139 0.00431 0.0147 0.4857 0.0043
-3.250 -0.2626 0.01106 0.00391 0.0153 0.4765 0.0044
-3.000 -0.2369 0.01081 0.00361 0.0159 0.4688 0.0046
-2.750 -0.2117 0.01050 0.00324 0.0165 0.4607 0.0049
-2.500 -0.1861 0.01027 0.00296 0.0170 0.4531 0.0052
-2.250 -0.1603 0.01008 0.00272 0.0175 0.4447 0.0054
-2.000 -0.1344 0.00988 0.00247 0.0180 0.4378 0.0056
-1.750 -0.1083 0.00971 0.00226 0.0185 0.4308 0.0059
-1.500 -0.0820 0.00958 0.00208 0.0189 0.4240 0.0064
-1.250 -0.0556 0.00945 0.00191 0.0193 0.4167 0.0071
-1.000 -0.0296 0.00932 0.00176 0.0197 0.4100 0.0126
-0.750 -0.0035 0.00915 0.00166 0.0201 0.4043 0.0310
-0.500 0.0220 0.00899 0.00157 0.0206 0.3977 0.0652
-0.250 0.0461 0.00868 0.00150 0.0213 0.3918 0.1462
0.000 0.0304 0.00609 0.00117 0.0297 0.3888 0.7873
0.250 0.0510 0.00606 0.00142 0.0318 0.3835 0.8929
0.500 0.0775 0.00618 0.00151 0.0324 0.3782 0.9061
0.750 0.1039 0.00632 0.00162 0.0330 0.3726 0.9174
1.000 0.1295 0.00647 0.00172 0.0337 0.3670 0.9257
1.250 0.1572 0.00658 0.00180 0.0339 0.3624 0.9305
1.500 0.1858 0.00669 0.00187 0.0339 0.3573 0.9335
1.750 0.2135 0.00675 0.00187 0.0339 0.3516 0.9346
2.000 0.2413 0.00679 0.00188 0.0339 0.3474 0.9355
2.250 0.2691 0.00684 0.00189 0.0339 0.3427 0.9367
2.500 0.2965 0.00690 0.00190 0.0340 0.3374 0.9378
2.750 0.3239 0.00696 0.00193 0.0340 0.3329 0.9388
3.000 0.3514 0.00700 0.00195 0.0340 0.3287 0.9397
3.250 0.3786 0.00706 0.00198 0.0341 0.3235 0.9407
3.500 0.4057 0.00714 0.00202 0.0342 0.3186 0.9416
3.750 0.4330 0.00719 0.00206 0.0342 0.3143 0.9425
4.000 0.4610 0.00726 0.00211 0.0341 0.3087 0.9434
4.250 0.4887 0.00735 0.00218 0.0340 0.3038 0.9442
4.500 0.5166 0.00742 0.00224 0.0339 0.2987 0.9449
4.750 0.5441 0.00752 0.00233 0.0339 0.2928 0.9457
5.000 0.5716 0.00762 0.00242 0.0338 0.2877 0.9465
5.250 0.5991 0.00771 0.00250 0.0337 0.2822 0.9474
5.500 0.6261 0.00783 0.00261 0.0338 0.2756 0.9483
5.750 0.6534 0.00793 0.00272 0.0337 0.2700 0.9493
6.000 0.6802 0.00806 0.00283 0.0338 0.2631 0.9503
6.250 0.7069 0.00818 0.00295 0.0338 0.2563 0.9514
6.500 0.7331 0.00834 0.00309 0.0339 0.2482 0.9527
6.750 0.7594 0.00847 0.00323 0.0340 0.2415 0.9541
7.000 0.7848 0.00866 0.00339 0.0343 0.2314 0.9553
7.250 0.8106 0.00882 0.00355 0.0344 0.2229 0.9565
7.500 0.8362 0.00902 0.00373 0.0346 0.2140 0.9576
7.750 0.8621 0.00925 0.00395 0.0347 0.2031 0.9587
8.000 0.8878 0.00950 0.00417 0.0347 0.1913 0.9598
8.250 0.9131 0.00977 0.00442 0.0349 0.1791 0.9610
8.500 0.9377 0.01008 0.00470 0.0351 0.1665 0.9624
8.750 0.9611 0.01046 0.00503 0.0355 0.1509 0.9641
9.000 0.9843 0.01084 0.00537 0.0359 0.1373 0.9659
9.250 1.0065 0.01124 0.00573 0.0365 0.1236 0.9680
9.500 1.0273 0.01168 0.00613 0.0374 0.1100 0.9704
9.750 1.0500 0.01220 0.00658 0.0376 0.0948 0.9723
10.000 1.0740 0.01272 0.00707 0.0376 0.0822 0.9739
10.250 1.0968 0.01331 0.00761 0.0378 0.0688 0.9758
10.500 1.1184 0.01394 0.00820 0.0380 0.0565 0.9780
10.750 1.1403 0.01448 0.00873 0.0383 0.0495 0.9804
11.000 1.1569 0.01538 0.00953 0.0392 0.0348 0.9837
11.250 1.1804 0.01617 0.01030 0.0386 0.0264 0.9850
11.500 1.2030 0.01703 0.01114 0.0381 0.0197 0.9863
11.750 1.2262 0.01772 0.01187 0.0377 0.0169 0.9879
12.000 1.2455 0.01860 0.01276 0.0376 0.0130 0.9905
12.250 1.2619 0.01943 0.01364 0.0381 0.0110 0.9939
12.500 1.2813 0.02029 0.01456 0.0377 0.0101 0.9972
13.000 1.2932 0.02259 0.01697 0.0404 0.0077 1.0000
13.250 1.2907 0.02412 0.01856 0.0424 0.0065 1.0000
13.500 1.2937 0.02568 0.02020 0.0434 0.0068 1.0000
13.750 1.2928 0.02787 0.02245 0.0438 0.0057 1.0000
14.000 1.2925 0.03022 0.02488 0.0439 0.0049 1.0000
14.250 1.2910 0.03286 0.02759 0.0436 0.0041 1.0000
14.500 1.2881 0.03576 0.03057 0.0432 0.0036 1.0000
14.750 1.2866 0.03856 0.03347 0.0427 0.0037 1.0000
15.000 1.2825 0.04172 0.03671 0.0421 0.0034 1.0000
15.250 1.2768 0.04508 0.04016 0.0414 0.0031 1.0000
15.500 1.2714 0.04846 0.04363 0.0406 0.0031 1.0000
15.750 1.2630 0.05223 0.04748 0.0396 0.0029 1.0000
16.000 1.2503 0.05658 0.05191 0.0384 0.0021 1.0000
16.250 1.2423 0.06051 0.05592 0.0373 0.0021 1.0000
16.500 1.2332 0.06469 0.06018 0.0359 0.0018 1.0000
16.750 1.2228 0.06914 0.06472 0.0344 0.0016 1.0000
17.000 1.2109 0.07390 0.06956 0.0327 0.0011 1.0000
17.250 1.2102 0.07714 0.07290 0.0317 0.0020 1.0000
17.500 1.1978 0.08207 0.07790 0.0299 0.0014 1.0000
17.750 1.1891 0.08659 0.08251 0.0282 0.0014 1.0000
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Polar data table (+)
Polar graphs
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