MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 500,000 Max Cl/Cd: 77.96 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh64-il-500000.txt Download as CSV file: xf-mh64-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5715 0.08106 0.07907 0.0026 1.0000 0.0159
-8.000 -0.5759 0.07614 0.07420 -0.0009 1.0000 0.0160
-7.750 -0.5843 0.07043 0.06852 -0.0063 1.0000 0.0161
-7.500 -0.5857 0.06276 0.06079 -0.0140 1.0000 0.0160
-7.250 -0.5838 0.05546 0.05335 -0.0190 1.0000 0.0162
-7.000 -0.5766 0.04934 0.04699 -0.0218 1.0000 0.0169
-6.750 -0.5562 0.04686 0.04422 -0.0226 1.0000 0.0182
-6.500 -0.5424 0.04323 0.04028 -0.0234 1.0000 0.0183
-6.250 -0.5264 0.03961 0.03635 -0.0239 1.0000 0.0184
-5.000 -0.4208 0.01831 0.01296 -0.0227 0.9276 0.0106
-4.750 -0.3996 0.01605 0.01047 -0.0210 0.9137 0.0092
-4.500 -0.3771 0.01427 0.00845 -0.0195 0.9014 0.0086
-4.250 -0.3534 0.01292 0.00690 -0.0182 0.8897 0.0083
-4.000 -0.3290 0.01192 0.00571 -0.0172 0.8787 0.0081
-3.750 -0.3041 0.01113 0.00477 -0.0163 0.8685 0.0082
-3.500 -0.2785 0.01053 0.00401 -0.0155 0.8589 0.0087
-3.250 -0.2520 0.01008 0.00341 -0.0149 0.8489 0.0097
-3.000 -0.2271 0.00892 0.00257 -0.0142 0.8391 0.1031
-2.750 -0.2024 0.00823 0.00234 -0.0138 0.8297 0.2197
-2.500 -0.1771 0.00773 0.00219 -0.0135 0.8204 0.3214
-2.250 -0.1506 0.00742 0.00204 -0.0132 0.8106 0.3832
-2.000 -0.1245 0.00712 0.00194 -0.0128 0.8014 0.4553
-1.750 -0.0985 0.00686 0.00183 -0.0123 0.7925 0.5185
-1.500 -0.0722 0.00661 0.00175 -0.0119 0.7824 0.5801
-1.250 -0.0464 0.00636 0.00168 -0.0113 0.7728 0.6461
-1.000 -0.0215 0.00610 0.00161 -0.0105 0.7633 0.7185
-0.750 0.0025 0.00581 0.00157 -0.0093 0.7531 0.7999
-0.500 0.0280 0.00555 0.00155 -0.0082 0.7427 0.8900
-0.250 0.0762 0.00550 0.00151 -0.0122 0.7317 0.9594
0.000 0.1228 0.00552 0.00145 -0.0161 0.7199 0.9881
0.250 0.1612 0.00556 0.00140 -0.0183 0.7075 1.0000
0.500 0.1873 0.00559 0.00135 -0.0178 0.6947 1.0000
0.750 0.2135 0.00563 0.00132 -0.0174 0.6810 1.0000
1.000 0.2398 0.00568 0.00130 -0.0170 0.6663 1.0000
1.250 0.2663 0.00574 0.00129 -0.0166 0.6506 1.0000
1.500 0.2928 0.00581 0.00129 -0.0163 0.6336 1.0000
1.750 0.3193 0.00590 0.00130 -0.0159 0.6155 1.0000
2.000 0.3460 0.00599 0.00133 -0.0156 0.5952 1.0000
2.250 0.3726 0.00611 0.00136 -0.0153 0.5735 1.0000
2.500 0.3993 0.00625 0.00141 -0.0150 0.5493 1.0000
2.750 0.4260 0.00640 0.00149 -0.0147 0.5245 1.0000
3.000 0.4527 0.00657 0.00158 -0.0145 0.4989 1.0000
3.250 0.4794 0.00676 0.00168 -0.0143 0.4727 1.0000
3.500 0.5060 0.00697 0.00180 -0.0141 0.4462 1.0000
3.750 0.5327 0.00719 0.00195 -0.0139 0.4204 1.0000
4.000 0.5593 0.00743 0.00211 -0.0137 0.3937 1.0000
4.250 0.5859 0.00769 0.00228 -0.0135 0.3675 1.0000
4.500 0.6125 0.00795 0.00247 -0.0134 0.3413 1.0000
4.750 0.6389 0.00824 0.00268 -0.0132 0.3152 1.0000
5.000 0.6653 0.00854 0.00293 -0.0131 0.2880 1.0000
5.250 0.6915 0.00887 0.00318 -0.0129 0.2604 1.0000
5.500 0.7176 0.00923 0.00345 -0.0127 0.2329 1.0000
5.750 0.7435 0.00961 0.00375 -0.0126 0.2046 1.0000
6.000 0.7692 0.01002 0.00407 -0.0124 0.1789 1.0000
6.250 0.7946 0.01048 0.00443 -0.0122 0.1506 1.0000
6.500 0.8198 0.01097 0.00482 -0.0120 0.1257 1.0000
6.750 0.8452 0.01142 0.00526 -0.0118 0.1056 1.0000
7.000 0.8701 0.01194 0.00571 -0.0115 0.0855 1.0000
7.250 0.8941 0.01257 0.00621 -0.0112 0.0599 1.0000
7.500 0.9176 0.01331 0.00681 -0.0109 0.0376 1.0000
7.750 0.9410 0.01404 0.00750 -0.0105 0.0237 1.0000
8.000 0.9614 0.01540 0.00886 -0.0096 0.0109 1.0000
8.250 0.9829 0.01646 0.01002 -0.0088 0.0070 1.0000
8.500 0.9972 0.01866 0.01248 -0.0073 0.0059 1.0000
8.750 1.0165 0.01985 0.01382 -0.0063 0.0056 1.0000
9.000 1.0337 0.02133 0.01547 -0.0051 0.0054 1.0000
9.250 1.0488 0.02308 0.01745 -0.0037 0.0053 1.0000
9.500 1.0626 0.02501 0.01958 -0.0022 0.0053 1.0000
9.750 1.0743 0.02721 0.02202 -0.0006 0.0053 1.0000
10.000 1.0831 0.02971 0.02476 0.0011 0.0053 1.0000
10.250 1.0874 0.03260 0.02794 0.0030 0.0053 1.0000
10.500 1.0865 0.03555 0.03115 0.0052 0.0054 1.0000
10.750 1.0777 0.03834 0.03418 0.0079 0.0055 1.0000
11.000 1.0648 0.04177 0.03785 0.0095 0.0056 1.0000
11.250 1.0522 0.04546 0.04174 0.0099 0.0056 1.0000
11.500 1.0354 0.05010 0.04661 0.0092 0.0057 1.0000
11.750 1.0180 0.05533 0.05204 0.0072 0.0057 1.0000
12.000 0.9232 0.05407 0.05108 0.0045 0.0057 1.0000
12.250 0.9036 0.06167 0.05883 0.0011 0.0058 1.0000
12.500 0.8823 0.07009 0.06739 -0.0029 0.0058 1.0000
12.750 0.9666 0.07880 0.07606 -0.0067 0.0061 1.0000
13.000 0.9543 0.08579 0.08316 -0.0115 0.0061 1.0000
13.250 0.9396 0.09376 0.09124 -0.0169 0.0061 1.0000
13.500 0.9273 0.10170 0.09929 -0.0219 0.0062 1.0000
13.750 0.9132 0.11050 0.10817 -0.0274 0.0062 1.0000
14.000 0.8992 0.11981 0.11757 -0.0327 0.0062 1.0000
14.250 0.8854 0.12956 0.12737 -0.0380 0.0063 1.0000
14.500 0.8692 0.14081 0.13868 -0.0435 0.0065 1.0000
14.750 0.7411 0.14056 0.13866 -0.0416 0.0064 1.0000
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Polar data table (+)
Polar graphs
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