MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 50,000 Max Cl/Cd: 29.72 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh64-il-50000.txt Download as CSV file: xf-mh64-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5243 0.10282 0.09665 0.0169 1.0000 0.2455
-8.000 -0.5357 0.10063 0.09459 0.0144 1.0000 0.2546
-7.750 -0.5304 0.09714 0.09115 0.0141 1.0000 0.2668
-7.500 -0.5198 0.09311 0.08716 0.0144 1.0000 0.2795
-7.250 -0.5146 0.08951 0.08363 0.0142 1.0000 0.2928
-7.000 -0.5054 0.08555 0.07973 0.0143 1.0000 0.3038
-6.750 -0.5433 0.06981 0.06385 -0.0170 1.0000 0.1434
-6.500 -0.5357 0.06096 0.05476 -0.0229 1.0000 0.1121
-6.250 -0.5269 0.05397 0.04735 -0.0266 1.0000 0.0990
-6.000 -0.5148 0.04759 0.04024 -0.0288 1.0000 0.0897
-5.750 -0.4972 0.04308 0.03537 -0.0291 1.0000 0.0866
-5.500 -0.4781 0.03901 0.03077 -0.0290 1.0000 0.0861
-5.250 -0.4569 0.03557 0.02675 -0.0286 1.0000 0.0887
-5.000 -0.4336 0.03255 0.02299 -0.0277 1.0000 0.0918
-4.750 -0.4098 0.02944 0.01980 -0.0269 1.0000 0.0964
-4.500 -0.3841 0.02702 0.01692 -0.0257 1.0000 0.1046
-4.250 -0.3617 0.02490 0.01495 -0.0246 1.0000 0.1286
-4.000 -0.3398 0.02278 0.01296 -0.0230 1.0000 0.1733
-3.750 -0.3237 0.02017 0.01139 -0.0204 1.0000 0.3157
-3.500 -0.3159 0.01909 0.01105 -0.0160 1.0000 0.4609
-3.250 -0.3059 0.01844 0.01080 -0.0116 1.0000 0.5587
-3.000 -0.2949 0.01774 0.01042 -0.0071 1.0000 0.6472
-2.750 -0.2839 0.01704 0.01005 -0.0020 1.0000 0.7405
-2.500 -0.1489 0.01666 0.00914 -0.0154 1.0000 0.9606
-2.250 -0.0923 0.01580 0.00772 -0.0249 1.0000 1.0000
-2.000 -0.1016 0.01568 0.00740 -0.0209 1.0000 1.0000
-1.750 -0.0990 0.01574 0.00719 -0.0181 1.0000 1.0000
-1.500 -0.0905 0.01587 0.00705 -0.0159 1.0000 1.0000
-1.250 -0.0788 0.01605 0.00698 -0.0142 1.0000 1.0000
-1.000 -0.0651 0.01626 0.00697 -0.0128 1.0000 1.0000
-0.750 -0.0504 0.01652 0.00699 -0.0117 1.0000 1.0000
-0.500 -0.0348 0.01682 0.00711 -0.0107 1.0000 1.0000
-0.250 -0.0189 0.01716 0.00729 -0.0099 1.0000 1.0000
0.000 -0.0027 0.01755 0.00754 -0.0092 1.0000 1.0000
0.250 0.0137 0.01799 0.00785 -0.0086 1.0000 1.0000
0.500 0.0301 0.01848 0.00821 -0.0082 1.0000 1.0000
0.750 0.0581 0.01918 0.00882 -0.0101 0.9950 1.0000
1.000 0.1196 0.02026 0.00985 -0.0181 0.9744 1.0000
1.250 0.1823 0.02127 0.01086 -0.0259 0.9532 1.0000
1.500 0.2409 0.02210 0.01173 -0.0325 0.9306 1.0000
1.750 0.2972 0.02279 0.01251 -0.0384 0.9072 1.0000
2.000 0.3558 0.02332 0.01319 -0.0440 0.8837 1.0000
2.250 0.4092 0.02368 0.01368 -0.0479 0.8603 1.0000
2.500 0.4447 0.02409 0.01419 -0.0485 0.8350 1.0000
2.750 0.4758 0.02445 0.01471 -0.0481 0.8096 1.0000
3.000 0.5037 0.02475 0.01511 -0.0468 0.7842 1.0000
3.250 0.5296 0.02497 0.01543 -0.0449 0.7591 1.0000
3.500 0.5542 0.02509 0.01564 -0.0425 0.7343 1.0000
3.750 0.5784 0.02506 0.01573 -0.0397 0.7100 1.0000
4.000 0.6005 0.02509 0.01585 -0.0368 0.6837 1.0000
4.250 0.6225 0.02507 0.01591 -0.0338 0.6567 1.0000
4.500 0.6447 0.02497 0.01587 -0.0308 0.6291 1.0000
4.750 0.6665 0.02501 0.01598 -0.0280 0.5989 1.0000
5.000 0.6886 0.02505 0.01608 -0.0253 0.5674 1.0000
5.250 0.7115 0.02502 0.01612 -0.0225 0.5358 1.0000
5.500 0.7338 0.02528 0.01639 -0.0201 0.5010 1.0000
5.750 0.7567 0.02555 0.01658 -0.0176 0.4663 1.0000
6.000 0.7786 0.02620 0.01722 -0.0156 0.4284 1.0000
6.250 0.8006 0.02700 0.01798 -0.0138 0.3910 1.0000
6.500 0.8228 0.02788 0.01874 -0.0119 0.3548 1.0000
6.750 0.8440 0.02903 0.01987 -0.0104 0.3180 1.0000
7.000 0.8645 0.03035 0.02132 -0.0089 0.2818 1.0000
7.250 0.8854 0.03166 0.02243 -0.0073 0.2470 1.0000
7.500 0.9041 0.03363 0.02457 -0.0059 0.2140 1.0000
7.750 0.9229 0.03529 0.02603 -0.0044 0.1813 1.0000
8.000 0.9404 0.03803 0.02897 -0.0030 0.1564 1.0000
8.250 0.9552 0.04081 0.03197 -0.0017 0.1348 1.0000
8.500 0.9696 0.04470 0.03621 -0.0005 0.1225 1.0000
8.750 0.9802 0.04794 0.03972 0.0007 0.1093 1.0000
9.000 0.9940 0.05167 0.04349 0.0017 0.1002 1.0000
9.250 0.9911 0.05686 0.04937 0.0026 0.0986 1.0000
9.500 0.9839 0.06214 0.05511 0.0032 0.0981 1.0000
9.750 0.9717 0.06743 0.06074 0.0032 0.0983 1.0000
10.000 0.9563 0.07268 0.06619 0.0028 0.0990 1.0000
10.250 0.9381 0.07777 0.07140 0.0022 0.0998 1.0000
10.500 0.9227 0.08323 0.07690 0.0007 0.1005 1.0000
10.750 0.8415 0.10109 0.09472 -0.0166 0.1256 1.0000
11.000 0.7997 0.11629 0.10967 -0.0290 0.1502 1.0000
11.250 0.8185 0.11909 0.11256 -0.0262 0.1401 1.0000
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Polar data table (+)
Polar graphs
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