MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.57 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh114-il-1000000-n5.txt Download as CSV file: xf-mh114-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 114 13.02%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1602 0.02747 0.02449 -0.1785 0.8287 0.0040
-9.500 -0.1576 0.02267 0.01928 -0.1832 0.8196 0.0040
-9.250 -0.1411 0.02055 0.01689 -0.1845 0.8124 0.0040
-9.000 -0.1218 0.01862 0.01468 -0.1856 0.8066 0.0040
-8.750 -0.0998 0.01710 0.01292 -0.1863 0.8004 0.0041
-8.500 -0.0760 0.01601 0.01162 -0.1868 0.7947 0.0041
-8.250 -0.0508 0.01505 0.01049 -0.1872 0.7896 0.0041
-8.000 -0.0250 0.01422 0.00950 -0.1876 0.7839 0.0041
-7.750 0.0011 0.01355 0.00867 -0.1878 0.7787 0.0042
-7.500 0.0281 0.01292 0.00792 -0.1881 0.7737 0.0042
-7.250 0.0553 0.01238 0.00726 -0.1883 0.7684 0.0042
-7.000 0.0823 0.01169 0.00642 -0.1886 0.7630 0.0044
-6.750 0.1101 0.01111 0.00573 -0.1890 0.7581 0.0045
-6.500 0.1380 0.01072 0.00526 -0.1892 0.7529 0.0047
-6.250 0.1658 0.01041 0.00487 -0.1893 0.7474 0.0049
-6.000 0.1939 0.01013 0.00453 -0.1895 0.7426 0.0051
-5.750 0.2222 0.00987 0.00421 -0.1897 0.7371 0.0054
-5.500 0.2501 0.00965 0.00392 -0.1898 0.7316 0.0057
-5.250 0.2785 0.00944 0.00365 -0.1899 0.7266 0.0060
-5.000 0.3069 0.00923 0.00339 -0.1901 0.7210 0.0064
-4.750 0.3349 0.00904 0.00315 -0.1902 0.7153 0.0070
-4.500 0.3633 0.00888 0.00295 -0.1903 0.7101 0.0077
-4.250 0.3917 0.00875 0.00277 -0.1905 0.7041 0.0084
-4.000 0.4195 0.00862 0.00259 -0.1905 0.6981 0.0098
-3.750 0.4481 0.00849 0.00245 -0.1906 0.6924 0.0114
-3.500 0.4762 0.00839 0.00232 -0.1907 0.6860 0.0139
-3.250 0.5042 0.00829 0.00220 -0.1908 0.6799 0.0187
-3.000 0.5326 0.00818 0.00210 -0.1909 0.6733 0.0255
-2.750 0.5602 0.00811 0.00202 -0.1909 0.6664 0.0351
-2.500 0.5887 0.00800 0.00194 -0.1911 0.6600 0.0475
-2.250 0.6165 0.00793 0.00188 -0.1911 0.6528 0.0624
-2.000 0.6445 0.00786 0.00183 -0.1912 0.6460 0.0824
-1.750 0.6725 0.00778 0.00180 -0.1913 0.6384 0.1079
-1.500 0.7003 0.00772 0.00178 -0.1914 0.6312 0.1383
-1.250 0.7281 0.00767 0.00177 -0.1915 0.6233 0.1663
-1.000 0.7555 0.00766 0.00178 -0.1914 0.6154 0.1944
-0.750 0.7832 0.00763 0.00180 -0.1915 0.6073 0.2267
-0.500 0.8105 0.00761 0.00183 -0.1914 0.5987 0.2662
-0.250 0.8378 0.00761 0.00187 -0.1914 0.5898 0.3013
0.000 0.8649 0.00762 0.00192 -0.1913 0.5812 0.3358
0.250 0.8916 0.00766 0.00198 -0.1912 0.5719 0.3694
0.500 0.9187 0.00769 0.00205 -0.1911 0.5628 0.4031
0.750 0.9450 0.00775 0.00213 -0.1909 0.5534 0.4375
1.000 0.9718 0.00780 0.00221 -0.1907 0.5440 0.4702
1.250 0.9980 0.00788 0.00231 -0.1905 0.5345 0.5034
1.500 1.0239 0.00797 0.00242 -0.1902 0.5242 0.5350
1.750 1.0501 0.00805 0.00253 -0.1899 0.5147 0.5656
2.000 1.0755 0.00816 0.00265 -0.1895 0.5048 0.5955
2.250 1.1010 0.00827 0.00278 -0.1892 0.4942 0.6263
2.500 1.1264 0.00838 0.00292 -0.1888 0.4846 0.6577
2.750 1.1509 0.00852 0.00307 -0.1882 0.4739 0.6894
3.000 1.1759 0.00864 0.00322 -0.1877 0.4636 0.7235
3.250 1.2001 0.00876 0.00339 -0.1871 0.4535 0.7605
3.500 1.2230 0.00890 0.00358 -0.1862 0.4428 0.8052
3.750 1.2449 0.00897 0.00375 -0.1850 0.4330 0.8632
4.000 1.2609 0.00897 0.00386 -0.1825 0.4235 1.0000
4.250 1.2830 0.00921 0.00404 -0.1815 0.4127 1.0000
4.500 1.3053 0.00942 0.00421 -0.1805 0.4023 1.0000
4.750 1.3266 0.00967 0.00441 -0.1794 0.3923 1.0000
5.000 1.3477 0.00993 0.00461 -0.1782 0.3819 1.0000
5.250 1.3689 0.01017 0.00483 -0.1770 0.3720 1.0000
5.500 1.3893 0.01046 0.00507 -0.1758 0.3621 1.0000
5.750 1.4098 0.01074 0.00531 -0.1745 0.3518 1.0000
6.000 1.4300 0.01103 0.00556 -0.1733 0.3425 1.0000
6.250 1.4493 0.01137 0.00585 -0.1718 0.3326 1.0000
6.500 1.4694 0.01166 0.00613 -0.1706 0.3229 1.0000
6.750 1.4882 0.01202 0.00645 -0.1691 0.3134 1.0000
7.000 1.5066 0.01239 0.00678 -0.1676 0.3036 1.0000
7.250 1.5252 0.01276 0.00712 -0.1662 0.2936 1.0000
7.500 1.5425 0.01319 0.00751 -0.1645 0.2841 1.0000
7.750 1.5596 0.01363 0.00793 -0.1629 0.2738 1.0000
8.000 1.5771 0.01406 0.00834 -0.1613 0.2650 1.0000
8.250 1.5928 0.01459 0.00883 -0.1595 0.2552 1.0000
8.500 1.6086 0.01512 0.00933 -0.1578 0.2447 1.0000
8.750 1.6241 0.01567 0.00987 -0.1560 0.2353 1.0000
9.000 1.6381 0.01631 0.01047 -0.1541 0.2251 1.0000
9.250 1.6523 0.01696 0.01110 -0.1523 0.2150 1.0000
9.500 1.6666 0.01762 0.01175 -0.1505 0.2061 1.0000
9.750 1.6790 0.01841 0.01250 -0.1485 0.1963 1.0000
10.000 1.6898 0.01931 0.01336 -0.1464 0.1844 1.0000
10.250 1.7030 0.02010 0.01414 -0.1446 0.1757 1.0000
10.500 1.7137 0.02105 0.01507 -0.1426 0.1661 1.0000
10.750 1.7241 0.02207 0.01606 -0.1407 0.1571 1.0000
11.000 1.7355 0.02304 0.01703 -0.1389 0.1488 1.0000
11.250 1.7443 0.02422 0.01819 -0.1369 0.1395 1.0000
11.500 1.7527 0.02546 0.01940 -0.1349 0.1306 1.0000
11.750 1.7630 0.02659 0.02055 -0.1332 0.1236 1.0000
12.000 1.7702 0.02800 0.02194 -0.1313 0.1157 1.0000
12.250 1.7783 0.02938 0.02332 -0.1296 0.1081 1.0000
12.500 1.7849 0.03092 0.02486 -0.1279 0.1000 1.0000
12.750 1.7897 0.03265 0.02657 -0.1260 0.0922 1.0000
13.000 1.7966 0.03427 0.02821 -0.1245 0.0858 1.0000
13.250 1.8024 0.03604 0.02998 -0.1230 0.0800 1.0000
13.500 1.8077 0.03790 0.03185 -0.1215 0.0740 1.0000
13.750 1.8126 0.03984 0.03382 -0.1201 0.0690 1.0000
14.000 1.8153 0.04205 0.03603 -0.1187 0.0629 1.0000
14.250 1.8183 0.04431 0.03830 -0.1175 0.0569 1.0000
14.500 1.8195 0.04683 0.04083 -0.1162 0.0513 1.0000
14.750 1.8199 0.04949 0.04351 -0.1151 0.0458 1.0000
15.000 1.8202 0.05225 0.04628 -0.1141 0.0407 1.0000
15.250 1.8198 0.05517 0.04924 -0.1133 0.0367 1.0000
15.500 1.8190 0.05822 0.05232 -0.1125 0.0323 1.0000
15.750 1.8184 0.06132 0.05545 -0.1120 0.0288 1.0000
16.000 1.8161 0.06472 0.05889 -0.1115 0.0256 1.0000
16.250 1.8149 0.06806 0.06228 -0.1112 0.0227 1.0000
16.500 1.8122 0.07168 0.06597 -0.1110 0.0203 1.0000
16.750 1.8098 0.07535 0.06969 -0.1110 0.0182 1.0000
17.000 1.8070 0.07913 0.07354 -0.1111 0.0165 1.0000
17.250 1.8041 0.08298 0.07746 -0.1113 0.0148 1.0000
17.500 1.8003 0.08705 0.08160 -0.1117 0.0135 1.0000
17.750 1.7970 0.09109 0.08572 -0.1122 0.0122 1.0000
18.000 1.7919 0.09548 0.09018 -0.1129 0.0111 1.0000
18.250 1.7878 0.09975 0.09455 -0.1137 0.0101 1.0000
18.500 1.7823 0.10429 0.09917 -0.1147 0.0092 1.0000
18.750 1.7767 0.10890 0.10386 -0.1158 0.0084 1.0000
19.000 1.7716 0.11347 0.10852 -0.1171 0.0077 1.0000
19.250 1.7662 0.11810 0.11324 -0.1185 0.0071 1.0000
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Polar data table (+)
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