EPPLER 335 AIRFOIL (e335-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 335 AIRFOIL (e335-il) Reynolds number: 200,000 Max Cl/Cd: 58.74 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e335-il-200000-n5.txt Download as CSV file: xf-e335-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 335 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4367 0.08154 0.07849 -0.0111 1.0000 0.0121
-9.250 -0.5451 0.07467 0.07130 -0.0184 1.0000 0.0121
-9.000 -0.5557 0.07138 0.06798 -0.0181 1.0000 0.0120
-8.750 -0.5669 0.06835 0.06492 -0.0167 1.0000 0.0119
-8.500 -0.5773 0.06566 0.06216 -0.0145 1.0000 0.0117
-8.250 -0.5873 0.06279 0.05923 -0.0117 1.0000 0.0115
-8.000 -0.5935 0.05953 0.05586 -0.0092 1.0000 0.0113
-7.500 -0.6176 0.04639 0.04200 -0.0001 1.0000 0.0094
-7.250 -0.6056 0.04342 0.03882 0.0008 0.9319 0.0093
-7.000 -0.5859 0.03886 0.03370 0.0007 0.8567 0.0092
-6.750 -0.5761 0.03585 0.03022 0.0036 0.8133 0.0091
-6.500 -0.5657 0.03287 0.02674 0.0068 0.7827 0.0090
-6.250 -0.5521 0.03010 0.02345 0.0096 0.7577 0.0090
-6.000 -0.5350 0.02766 0.02051 0.0119 0.7354 0.0090
-5.750 -0.5137 0.02513 0.01741 0.0138 0.7156 0.0092
-5.500 -0.4892 0.02322 0.01503 0.0149 0.6966 0.0095
-5.250 -0.4642 0.02196 0.01353 0.0156 0.6789 0.0096
-5.000 -0.4391 0.02096 0.01235 0.0162 0.6622 0.0101
-4.750 -0.4137 0.02027 0.01144 0.0168 0.6463 0.0117
-4.500 -0.3880 0.01945 0.01046 0.0173 0.6314 0.0128
-4.250 -0.3623 0.01866 0.00955 0.0178 0.6174 0.0136
-4.000 -0.3372 0.01785 0.00861 0.0186 0.6046 0.0142
-3.750 -0.3134 0.01718 0.00779 0.0195 0.5924 0.0150
-3.500 -0.2906 0.01653 0.00707 0.0206 0.5801 0.0160
-3.250 -0.2676 0.01603 0.00649 0.0217 0.5685 0.0175
-3.000 -0.2445 0.01561 0.00597 0.0227 0.5576 0.0202
-2.750 -0.2215 0.01521 0.00551 0.0237 0.5474 0.0259
-2.500 -0.1992 0.01474 0.00504 0.0249 0.5375 0.0382
-2.250 -0.1787 0.01420 0.00468 0.0264 0.5285 0.0872
-2.000 -0.1626 0.01335 0.00436 0.0283 0.5191 0.2146
-1.750 -0.0941 0.01301 0.00651 0.0228 0.5070 0.8700
-1.250 -0.0046 0.01471 0.00779 0.0183 0.4867 0.9057
-1.000 0.0389 0.01521 0.00810 0.0158 0.4775 0.9174
-0.750 0.0729 0.01529 0.00802 0.0146 0.4691 0.9215
-0.500 0.0968 0.01531 0.00792 0.0154 0.4623 0.9261
-0.250 0.1216 0.01531 0.00781 0.0159 0.4550 0.9298
0.000 0.1543 0.01529 0.00766 0.0148 0.4479 0.9314
0.250 0.1857 0.01527 0.00754 0.0140 0.4408 0.9334
0.500 0.2151 0.01528 0.00743 0.0136 0.4347 0.9357
0.750 0.2423 0.01527 0.00737 0.0136 0.4282 0.9385
1.000 0.2647 0.01531 0.00734 0.0146 0.4222 0.9421
1.250 0.2892 0.01534 0.00728 0.0151 0.4172 0.9446
1.500 0.3207 0.01531 0.00722 0.0142 0.4110 0.9459
1.750 0.3509 0.01531 0.00715 0.0136 0.4054 0.9474
2.000 0.3802 0.01532 0.00711 0.0131 0.4000 0.9490
2.250 0.4086 0.01533 0.00711 0.0128 0.3946 0.9509
2.500 0.4351 0.01537 0.00710 0.0129 0.3898 0.9529
2.750 0.4600 0.01544 0.00713 0.0133 0.3851 0.9552
3.000 0.4817 0.01551 0.00722 0.0144 0.3800 0.9576
3.250 0.5080 0.01555 0.00725 0.0145 0.3753 0.9591
3.500 0.5379 0.01560 0.00725 0.0138 0.3710 0.9602
3.750 0.5669 0.01562 0.00731 0.0133 0.3656 0.9613
4.000 0.5947 0.01567 0.00738 0.0131 0.3608 0.9624
4.500 0.6494 0.01582 0.00756 0.0128 0.3514 0.9653
4.750 0.6748 0.01590 0.00767 0.0130 0.3466 0.9666
5.000 0.6995 0.01602 0.00778 0.0134 0.3422 0.9681
5.250 0.7236 0.01614 0.00796 0.0139 0.3375 0.9698
5.500 0.7458 0.01626 0.00815 0.0148 0.3327 0.9713
5.750 0.7703 0.01638 0.00828 0.0152 0.3278 0.9723
6.000 0.7983 0.01648 0.00845 0.0148 0.3227 0.9731
6.250 0.8264 0.01658 0.00863 0.0144 0.3171 0.9742
6.500 0.8529 0.01671 0.00879 0.0143 0.3120 0.9752
6.750 0.8785 0.01684 0.00903 0.0144 0.3062 0.9761
7.000 0.9034 0.01698 0.00924 0.0147 0.3001 0.9770
7.250 0.9279 0.01716 0.00946 0.0149 0.2946 0.9781
7.500 0.9529 0.01732 0.00975 0.0151 0.2875 0.9795
7.750 0.9759 0.01752 0.00998 0.0157 0.2815 0.9807
8.000 0.9984 0.01771 0.01031 0.0163 0.2739 0.9818
8.250 1.0193 0.01794 0.01057 0.0173 0.2667 0.9829
8.500 1.0409 0.01816 0.01093 0.0181 0.2583 0.9839
8.750 1.0665 0.01840 0.01125 0.0179 0.2496 0.9848
9.000 1.0916 0.01867 0.01161 0.0178 0.2395 0.9859
9.250 1.1149 0.01898 0.01202 0.0181 0.2291 0.9869
9.500 1.1365 0.01936 0.01248 0.0186 0.2185 0.9879
9.750 1.1568 0.01980 0.01298 0.0192 0.2065 0.9890
10.000 1.1759 0.02032 0.01355 0.0200 0.1938 0.9902
10.250 1.1934 0.02093 0.01420 0.0210 0.1801 0.9916
10.500 1.2098 0.02165 0.01496 0.0220 0.1656 0.9932
10.750 1.2263 0.02249 0.01584 0.0227 0.1503 0.9947
11.000 1.2405 0.02344 0.01681 0.0236 0.1359 0.9962
11.250 1.2518 0.02454 0.01793 0.0248 0.1222 0.9980
11.500 1.2604 0.02577 0.01919 0.0261 0.1101 0.9999
11.750 1.2492 0.02689 0.02034 0.0311 0.1032 1.0000
12.000 1.2323 0.02792 0.02145 0.0368 0.0993 1.0000
12.250 1.2150 0.02942 0.02302 0.0413 0.0951 1.0000
12.500 1.1965 0.03147 0.02513 0.0448 0.0912 1.0000
12.750 1.1828 0.03358 0.02732 0.0474 0.0874 1.0000
13.000 1.1685 0.03597 0.02979 0.0495 0.0835 1.0000
13.250 1.1516 0.03882 0.03268 0.0513 0.0798 1.0000
13.500 1.1380 0.04162 0.03554 0.0526 0.0761 1.0000
13.750 1.1253 0.04458 0.03857 0.0536 0.0727 1.0000
14.000 1.1111 0.04794 0.04197 0.0540 0.0694 1.0000
14.250 1.0981 0.05139 0.04548 0.0541 0.0664 1.0000
14.500 1.0880 0.05471 0.04888 0.0541 0.0631 1.0000
14.750 1.0763 0.05837 0.05259 0.0537 0.0602 1.0000
15.000 1.0624 0.06246 0.05672 0.0530 0.0575 1.0000
15.250 1.0555 0.06591 0.06027 0.0524 0.0546 1.0000
15.500 1.0459 0.06983 0.06425 0.0515 0.0515 1.0000
15.750 1.0349 0.07410 0.06855 0.0503 0.0492 1.0000
16.000 1.0270 0.07805 0.07257 0.0492 0.0467 1.0000
16.250 1.0199 0.08198 0.07660 0.0480 0.0442 1.0000
16.500 1.0114 0.08624 0.08091 0.0466 0.0420 1.0000
17.000 0.9957 0.09478 0.08958 0.0437 0.0379 1.0000
17.250 0.9894 0.09897 0.09385 0.0422 0.0361 1.0000
17.500 0.9810 0.10359 0.09851 0.0404 0.0343 1.0000
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