MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.79 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh64-il-1000000.txt Download as CSV file: xf-mh64-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 64 8.59%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5853 0.08115 0.07972 0.0045 1.0000 0.0073
-8.250 -0.5910 0.07605 0.07465 0.0013 1.0000 0.0073
-8.000 -0.6033 0.07053 0.06918 -0.0030 1.0000 0.0072
-7.750 -0.6109 0.06135 0.05997 -0.0125 1.0000 0.0071
-7.500 -0.6131 0.05275 0.05122 -0.0180 1.0000 0.0071
-7.250 -0.6093 0.04633 0.04459 -0.0205 1.0000 0.0072
-7.000 -0.6000 0.04109 0.03911 -0.0219 1.0000 0.0074
-6.750 -0.5850 0.03649 0.03425 -0.0229 0.9831 0.0077
-6.500 -0.5687 0.03287 0.03027 -0.0227 0.9381 0.0082
-6.250 -0.5535 0.03030 0.02740 -0.0211 0.9156 0.0088
-6.000 -0.5312 0.02919 0.02607 -0.0200 0.9000 0.0096
-5.750 -0.5067 0.02892 0.02559 -0.0191 0.8865 0.0101
-5.500 -0.4862 0.02664 0.02296 -0.0184 0.8742 0.0101
-5.250 -0.4739 0.01922 0.01483 -0.0173 0.8630 0.0117
-5.000 -0.4493 0.01782 0.01328 -0.0169 0.8526 0.0126
-4.750 -0.4239 0.01664 0.01194 -0.0164 0.8429 0.0137
-4.500 -0.3969 0.01276 0.00749 -0.0140 0.8342 0.0059
-4.250 -0.3709 0.01165 0.00627 -0.0134 0.8248 0.0052
-4.000 -0.3455 0.01047 0.00491 -0.0127 0.8159 0.0050
-3.750 -0.3193 0.00968 0.00395 -0.0121 0.8068 0.0048
-3.500 -0.2921 0.00910 0.00323 -0.0117 0.7977 0.0048
-3.250 -0.2647 0.00870 0.00270 -0.0114 0.7890 0.0048
-3.000 -0.2370 0.00839 0.00228 -0.0111 0.7802 0.0051
-2.750 -0.2090 0.00813 0.00191 -0.0109 0.7713 0.0064
-2.500 -0.1835 0.00724 0.00149 -0.0106 0.7629 0.1225
-2.250 -0.1567 0.00683 0.00132 -0.0105 0.7538 0.1969
-2.000 -0.1292 0.00661 0.00121 -0.0104 0.7448 0.2410
-1.750 -0.1026 0.00621 0.00111 -0.0103 0.7358 0.3317
-1.500 -0.0757 0.00589 0.00103 -0.0101 0.7261 0.4125
-1.250 -0.0484 0.00568 0.00097 -0.0100 0.7162 0.4710
-1.000 -0.0210 0.00551 0.00091 -0.0099 0.7062 0.5201
-0.750 0.0063 0.00536 0.00086 -0.0097 0.6958 0.5718
-0.500 0.0334 0.00519 0.00083 -0.0095 0.6845 0.6270
-0.250 0.0601 0.00500 0.00080 -0.0091 0.6727 0.6890
0.000 0.0860 0.00479 0.00078 -0.0086 0.6604 0.7599
0.250 0.1106 0.00456 0.00078 -0.0077 0.6473 0.8388
0.500 0.1372 0.00437 0.00080 -0.0070 0.6330 0.9275
0.750 0.1871 0.00440 0.00081 -0.0117 0.6148 0.9773
1.250 0.2631 0.00458 0.00081 -0.0161 0.5742 1.0000
1.500 0.2898 0.00467 0.00082 -0.0158 0.5529 1.0000
1.750 0.3166 0.00479 0.00085 -0.0156 0.5300 1.0000
2.000 0.3433 0.00493 0.00089 -0.0153 0.5060 1.0000
2.250 0.3702 0.00507 0.00093 -0.0151 0.4818 1.0000
2.500 0.3970 0.00522 0.00099 -0.0149 0.4576 1.0000
2.750 0.4238 0.00538 0.00108 -0.0147 0.4336 1.0000
3.000 0.4506 0.00556 0.00116 -0.0145 0.4096 1.0000
3.250 0.4775 0.00573 0.00126 -0.0143 0.3863 1.0000
3.500 0.5043 0.00592 0.00136 -0.0141 0.3627 1.0000
3.750 0.5311 0.00612 0.00149 -0.0140 0.3395 1.0000
4.000 0.5579 0.00633 0.00162 -0.0138 0.3161 1.0000
4.250 0.5847 0.00654 0.00176 -0.0137 0.2940 1.0000
4.500 0.6114 0.00678 0.00192 -0.0135 0.2696 1.0000
4.750 0.6380 0.00704 0.00209 -0.0134 0.2457 1.0000
5.000 0.6646 0.00732 0.00230 -0.0132 0.2211 1.0000
5.250 0.6910 0.00762 0.00250 -0.0131 0.1958 1.0000
5.500 0.7174 0.00791 0.00273 -0.0129 0.1734 1.0000
5.750 0.7435 0.00829 0.00299 -0.0128 0.1464 1.0000
6.000 0.7696 0.00865 0.00326 -0.0126 0.1242 1.0000
6.250 0.7954 0.00904 0.00355 -0.0125 0.1029 1.0000
6.500 0.8210 0.00947 0.00388 -0.0123 0.0799 1.0000
6.750 0.8464 0.00993 0.00426 -0.0121 0.0600 1.0000
7.000 0.8716 0.01041 0.00465 -0.0119 0.0430 1.0000
7.250 0.8966 0.01093 0.00509 -0.0116 0.0280 1.0000
7.500 0.9215 0.01143 0.00555 -0.0113 0.0179 1.0000
7.750 0.9447 0.01230 0.00634 -0.0108 0.0053 1.0000
8.000 0.9682 0.01310 0.00722 -0.0103 0.0034 1.0000
8.250 0.9902 0.01417 0.00848 -0.0095 0.0030 1.0000
8.500 1.0131 0.01496 0.00938 -0.0089 0.0029 1.0000
8.750 1.0347 0.01590 0.01046 -0.0082 0.0028 1.0000
9.000 1.0549 0.01701 0.01174 -0.0073 0.0028 1.0000
9.250 1.0748 0.01807 0.01293 -0.0065 0.0027 1.0000
9.500 1.0950 0.01900 0.01397 -0.0057 0.0025 1.0000
9.750 1.1127 0.02022 0.01532 -0.0046 0.0025 1.0000
10.000 1.1320 0.02111 0.01630 -0.0039 0.0023 1.0000
10.250 1.1471 0.02249 0.01783 -0.0026 0.0022 1.0000
10.500 1.1606 0.02395 0.01944 -0.0013 0.0022 1.0000
10.750 1.1720 0.02548 0.02113 0.0002 0.0021 1.0000
11.000 1.1775 0.02748 0.02332 0.0022 0.0021 1.0000
11.250 1.1790 0.02922 0.02522 0.0047 0.0021 1.0000
11.500 1.1652 0.03213 0.02837 0.0080 0.0022 1.0000
11.750 1.1682 0.03371 0.03004 0.0090 0.0021 1.0000
12.000 1.1520 0.03776 0.03435 0.0100 0.0022 1.0000
12.250 1.1482 0.04068 0.03741 0.0098 0.0021 1.0000
12.500 1.1428 0.04410 0.04099 0.0089 0.0021 1.0000
12.750 1.1268 0.04937 0.04647 0.0069 0.0021 1.0000
13.000 1.1143 0.05463 0.05189 0.0042 0.0021 1.0000
13.250 1.1044 0.05994 0.05733 0.0011 0.0021 1.0000
13.500 1.0799 0.06831 0.06587 -0.0039 0.0022 1.0000
13.750 1.0629 0.07577 0.07348 -0.0085 0.0022 1.0000
14.000 1.0460 0.08366 0.08149 -0.0134 0.0022 1.0000
14.250 1.0336 0.09087 0.08879 -0.0177 0.0021 1.0000
14.500 1.0019 0.10283 0.10091 -0.0246 0.0023 1.0000
14.750 0.9781 0.11353 0.11171 -0.0305 0.0023 1.0000
15.000 0.9585 0.12365 0.12193 -0.0359 0.0024 1.0000
15.250 0.9397 0.13406 0.13240 -0.0413 0.0024 1.0000
15.500 0.9181 0.14580 0.14421 -0.0471 0.0024 1.0000
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Polar data table (+)
Polar graphs
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