EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.82 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh3012-il-1000000.txt Download as CSV file: xf-eh3012-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EH 3.0/12
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3646 0.08333 0.08137 -0.0134 0.7829 0.0152
-9.500 -0.3694 0.07792 0.07589 -0.0156 0.7636 0.0152
-9.250 -0.3790 0.07147 0.06940 -0.0185 0.7497 0.0152
-9.000 -0.3923 0.06460 0.06250 -0.0221 0.7379 0.0152
-8.750 -0.6757 0.02954 0.02631 -0.0272 0.8350 0.0107
-8.500 -0.6753 0.02561 0.02178 -0.0240 0.8009 0.0108
-8.250 -0.6650 0.02297 0.01868 -0.0216 0.7736 0.0108
-8.000 -0.6481 0.02131 0.01668 -0.0200 0.7515 0.0110
-7.750 -0.6291 0.01988 0.01496 -0.0186 0.7319 0.0111
-7.500 -0.6085 0.01861 0.01342 -0.0174 0.7145 0.0112
-7.250 -0.5861 0.01765 0.01225 -0.0165 0.6979 0.0114
-7.000 -0.5629 0.01678 0.01117 -0.0156 0.6818 0.0115
-6.750 -0.5388 0.01606 0.01027 -0.0148 0.6672 0.0117
-6.500 -0.5139 0.01551 0.00959 -0.0142 0.6541 0.0118
-6.250 -0.4923 0.01405 0.00791 -0.0131 0.6419 0.0123
-6.000 -0.4675 0.01353 0.00731 -0.0125 0.6288 0.0127
-5.750 -0.4417 0.01319 0.00691 -0.0121 0.6161 0.0133
-5.500 -0.4160 0.01278 0.00642 -0.0116 0.6050 0.0137
-5.250 -0.3902 0.01238 0.00593 -0.0110 0.5950 0.0143
-5.000 -0.3641 0.01206 0.00553 -0.0106 0.5850 0.0148
-4.750 -0.3376 0.01179 0.00518 -0.0101 0.5757 0.0152
-4.500 -0.3139 0.01110 0.00441 -0.0093 0.5666 0.0163
-4.250 -0.2876 0.01082 0.00410 -0.0089 0.5575 0.0173
-4.000 -0.2611 0.01060 0.00382 -0.0085 0.5490 0.0183
-3.750 -0.2342 0.01042 0.00358 -0.0081 0.5403 0.0191
-3.500 -0.2089 0.01003 0.00315 -0.0075 0.5323 0.0210
-3.250 -0.1822 0.00985 0.00294 -0.0071 0.5240 0.0227
-3.000 -0.1554 0.00968 0.00271 -0.0068 0.5165 0.0246
-2.750 -0.1290 0.00947 0.00249 -0.0064 0.5086 0.0278
-2.500 -0.1024 0.00928 0.00229 -0.0060 0.5015 0.0334
-2.250 -0.0761 0.00906 0.00215 -0.0056 0.4944 0.0520
-2.000 -0.0492 0.00895 0.00205 -0.0053 0.4877 0.0656
-1.750 -0.0220 0.00883 0.00196 -0.0051 0.4810 0.0772
-1.250 0.0323 0.00864 0.00180 -0.0046 0.4674 0.1055
-1.000 0.0593 0.00856 0.00173 -0.0044 0.4600 0.1260
-0.750 0.0862 0.00842 0.00167 -0.0042 0.4537 0.1554
-0.500 0.1114 0.00814 0.00161 -0.0037 0.4475 0.2281
-0.250 0.1207 0.00659 0.00141 -0.0006 0.4426 0.6502
0.000 0.1401 0.00617 0.00144 0.0014 0.4374 0.7866
0.250 0.1653 0.00612 0.00147 0.0022 0.4313 0.8291
0.500 0.1917 0.00612 0.00150 0.0028 0.4255 0.8528
0.750 0.2185 0.00613 0.00152 0.0032 0.4198 0.8725
1.000 0.2455 0.00618 0.00156 0.0036 0.4141 0.8876
1.250 0.2726 0.00621 0.00160 0.0040 0.4090 0.9026
1.500 0.2999 0.00626 0.00165 0.0043 0.4030 0.9166
1.750 0.3270 0.00635 0.00171 0.0046 0.3969 0.9291
2.000 0.3540 0.00640 0.00176 0.0051 0.3917 0.9408
2.250 0.3834 0.00650 0.00184 0.0049 0.3861 0.9499
2.500 0.4126 0.00661 0.00192 0.0047 0.3810 0.9576
2.750 0.4452 0.00670 0.00200 0.0038 0.3760 0.9627
3.000 0.4740 0.00682 0.00208 0.0037 0.3707 0.9693
3.250 0.5084 0.00693 0.00216 0.0023 0.3643 0.9716
3.500 0.5428 0.00705 0.00222 0.0008 0.3548 0.9731
3.750 0.5777 0.00715 0.00229 -0.0007 0.3469 0.9745
4.000 0.6120 0.00728 0.00237 -0.0022 0.3403 0.9761
4.250 0.6455 0.00739 0.00246 -0.0035 0.3342 0.9781
4.500 0.6771 0.00752 0.00255 -0.0044 0.3264 0.9809
4.750 0.7080 0.00764 0.00264 -0.0051 0.3192 0.9835
5.000 0.7427 0.00776 0.00273 -0.0068 0.3113 0.9844
5.250 0.7772 0.00790 0.00283 -0.0084 0.3023 0.9857
5.500 0.8110 0.00807 0.00295 -0.0099 0.2924 0.9872
5.750 0.8443 0.00822 0.00307 -0.0112 0.2820 0.9889
6.000 0.8768 0.00839 0.00320 -0.0125 0.2713 0.9910
6.250 0.9084 0.00859 0.00336 -0.0135 0.2622 0.9932
6.500 0.9408 0.00882 0.00353 -0.0148 0.2476 0.9947
6.750 0.9741 0.00907 0.00371 -0.0163 0.2324 0.9961
7.000 1.0070 0.00934 0.00391 -0.0178 0.2178 0.9977
7.250 1.0390 0.00970 0.00418 -0.0191 0.1978 0.9992
7.500 1.0656 0.01014 0.00450 -0.0194 0.1765 1.0000
7.750 1.0804 0.01078 0.00496 -0.0175 0.1446 1.0000
8.000 1.0929 0.01158 0.00555 -0.0152 0.1101 1.0000
8.250 1.0919 0.01331 0.00685 -0.0110 0.0387 1.0000
8.500 1.1043 0.01406 0.00751 -0.0087 0.0192 1.0000
8.750 1.1218 0.01447 0.00793 -0.0071 0.0166 1.0000
9.000 1.1403 0.01483 0.00831 -0.0056 0.0159 1.0000
9.250 1.1587 0.01520 0.00871 -0.0043 0.0156 1.0000
9.500 1.1759 0.01565 0.00919 -0.0027 0.0149 1.0000
9.750 1.1926 0.01612 0.00968 -0.0012 0.0143 1.0000
10.000 1.2101 0.01653 0.01014 0.0002 0.0145 1.0000
10.250 1.2244 0.01711 0.01074 0.0020 0.0138 1.0000
10.500 1.2382 0.01767 0.01135 0.0039 0.0135 1.0000
10.750 1.2498 0.01830 0.01203 0.0060 0.0133 1.0000
11.000 1.2544 0.01899 0.01278 0.0093 0.0130 1.0000
11.250 1.2593 0.01981 0.01366 0.0121 0.0129 1.0000
11.500 1.2628 0.02094 0.01488 0.0143 0.0127 1.0000
11.750 1.2717 0.02197 0.01597 0.0155 0.0126 1.0000
12.000 1.2779 0.02341 0.01748 0.0164 0.0125 1.0000
12.250 1.2816 0.02529 0.01946 0.0168 0.0125 1.0000
12.500 1.2885 0.02706 0.02129 0.0169 0.0124 1.0000
12.750 1.2917 0.02935 0.02366 0.0167 0.0123 1.0000
13.000 1.2951 0.03169 0.02609 0.0164 0.0122 1.0000
13.250 1.2976 0.03420 0.02868 0.0160 0.0122 1.0000
13.500 1.2949 0.03732 0.03190 0.0154 0.0121 1.0000
13.750 1.2929 0.04040 0.03507 0.0148 0.0120 1.0000
14.000 1.2891 0.04370 0.03846 0.0142 0.0121 1.0000
14.250 1.2805 0.04760 0.04246 0.0134 0.0122 1.0000
14.500 1.2747 0.05117 0.04612 0.0126 0.0120 1.0000
14.750 1.2692 0.05475 0.04978 0.0118 0.0119 1.0000
15.000 1.2622 0.05861 0.05373 0.0108 0.0119 1.0000
15.250 1.2535 0.06284 0.05804 0.0097 0.0118 1.0000
15.500 1.2462 0.06696 0.06225 0.0085 0.0118 1.0000
15.750 1.2398 0.07099 0.06635 0.0074 0.0117 1.0000
16.000 1.2339 0.07503 0.07046 0.0062 0.0115 1.0000
16.250 1.2232 0.07975 0.07529 0.0048 0.0118 1.0000
16.500 1.2180 0.08377 0.07937 0.0036 0.0116 1.0000
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