MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 200,000 Max Cl/Cd: 56.98 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh64-il-200000-n5.txt Download as CSV file: xf-mh64-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5733 0.10554 0.10219 0.0153 1.0000 0.0098
-9.500 -0.5737 0.10080 0.09744 0.0131 1.0000 0.0094
-9.250 -0.5735 0.09616 0.09283 0.0107 1.0000 0.0092
-9.000 -0.5739 0.09149 0.08820 0.0082 1.0000 0.0090
-8.750 -0.5755 0.08654 0.08330 0.0053 1.0000 0.0088
-8.500 -0.5784 0.08143 0.07823 0.0021 1.0000 0.0086
-8.250 -0.5835 0.07591 0.07277 -0.0017 1.0000 0.0085
-8.000 -0.5910 0.07002 0.06699 -0.0068 1.0000 0.0083
-7.750 -0.5960 0.06151 0.05843 -0.0151 1.0000 0.0082
-7.500 -0.5980 0.05393 0.05066 -0.0199 1.0000 0.0079
-7.250 -0.5966 0.04728 0.04372 -0.0227 1.0000 0.0077
-7.000 -0.5903 0.04126 0.03729 -0.0242 1.0000 0.0073
-6.750 -0.5794 0.03576 0.03129 -0.0247 1.0000 0.0070
-6.500 -0.5643 0.03097 0.02591 -0.0245 1.0000 0.0067
-6.250 -0.5450 0.02734 0.02169 -0.0240 1.0000 0.0066
-6.000 -0.5231 0.02451 0.01841 -0.0235 1.0000 0.0065
-5.750 -0.4996 0.02224 0.01576 -0.0230 1.0000 0.0064
-5.500 -0.4749 0.02036 0.01360 -0.0227 0.9961 0.0065
-5.000 -0.4116 0.01722 0.00999 -0.0245 0.9513 0.0069
-4.750 -0.3836 0.01611 0.00871 -0.0245 0.9352 0.0072
-4.500 -0.3578 0.01522 0.00767 -0.0239 0.9204 0.0077
-4.250 -0.3331 0.01447 0.00674 -0.0231 0.9068 0.0086
-4.000 -0.3083 0.01387 0.00590 -0.0222 0.8942 0.0097
-3.750 -0.2839 0.01325 0.00519 -0.0213 0.8824 0.0158
-3.500 -0.2604 0.01230 0.00441 -0.0203 0.8712 0.0585
-3.000 -0.2133 0.01089 0.00377 -0.0190 0.8493 0.2493
-2.750 -0.1885 0.01051 0.00357 -0.0184 0.8387 0.3154
-2.500 -0.1634 0.01021 0.00339 -0.0178 0.8284 0.3711
-2.250 -0.1382 0.00996 0.00318 -0.0171 0.8185 0.4206
-2.000 -0.1128 0.00972 0.00303 -0.0165 0.8079 0.4694
-1.750 -0.0873 0.00948 0.00290 -0.0158 0.7972 0.5195
-1.500 -0.0621 0.00925 0.00278 -0.0150 0.7868 0.5723
-1.250 -0.0373 0.00901 0.00268 -0.0141 0.7765 0.6299
-1.000 -0.0130 0.00877 0.00258 -0.0130 0.7660 0.6942
-0.750 0.0115 0.00851 0.00253 -0.0118 0.7549 0.7671
-0.500 0.0404 0.00831 0.00249 -0.0113 0.7438 0.8491
-0.250 0.0848 0.00822 0.00240 -0.0142 0.7319 0.9259
0.000 0.1291 0.00820 0.00230 -0.0175 0.7191 0.9739
0.250 0.1685 0.00822 0.00222 -0.0199 0.7055 1.0000
0.500 0.1941 0.00827 0.00217 -0.0193 0.6917 1.0000
0.750 0.2197 0.00833 0.00213 -0.0188 0.6772 1.0000
1.000 0.2456 0.00839 0.00211 -0.0183 0.6619 1.0000
1.250 0.2715 0.00847 0.00210 -0.0178 0.6456 1.0000
1.500 0.2974 0.00856 0.00210 -0.0173 0.6285 1.0000
1.750 0.3236 0.00865 0.00213 -0.0168 0.6091 1.0000
2.000 0.3497 0.00877 0.00215 -0.0164 0.5889 1.0000
2.250 0.3760 0.00889 0.00220 -0.0160 0.5670 1.0000
2.500 0.4022 0.00905 0.00226 -0.0156 0.5438 1.0000
2.750 0.4284 0.00922 0.00237 -0.0152 0.5193 1.0000
3.000 0.4546 0.00942 0.00248 -0.0149 0.4935 1.0000
3.250 0.4808 0.00964 0.00261 -0.0146 0.4670 1.0000
3.500 0.5070 0.00988 0.00276 -0.0143 0.4408 1.0000
3.750 0.5332 0.01014 0.00297 -0.0140 0.4146 1.0000
4.000 0.5593 0.01042 0.00318 -0.0137 0.3890 1.0000
4.250 0.5854 0.01071 0.00342 -0.0135 0.3636 1.0000
4.500 0.6113 0.01103 0.00367 -0.0132 0.3381 1.0000
4.750 0.6372 0.01137 0.00396 -0.0130 0.3128 1.0000
5.000 0.6630 0.01173 0.00431 -0.0128 0.2869 1.0000
5.500 0.7140 0.01253 0.00502 -0.0123 0.2353 1.0000
5.750 0.7393 0.01298 0.00542 -0.0120 0.2096 1.0000
6.000 0.7643 0.01346 0.00586 -0.0118 0.1846 1.0000
6.250 0.7890 0.01398 0.00634 -0.0115 0.1606 1.0000
6.500 0.8134 0.01454 0.00686 -0.0112 0.1380 1.0000
6.750 0.8376 0.01514 0.00748 -0.0109 0.1162 1.0000
7.000 0.8615 0.01577 0.00809 -0.0106 0.0951 1.0000
7.250 0.8846 0.01650 0.00877 -0.0102 0.0744 1.0000
7.500 0.9075 0.01727 0.00951 -0.0098 0.0550 1.0000
7.750 0.9295 0.01817 0.01039 -0.0092 0.0406 1.0000
8.000 0.9503 0.01926 0.01145 -0.0086 0.0282 1.0000
8.250 0.9709 0.02031 0.01257 -0.0079 0.0201 1.0000
8.500 0.9911 0.02138 0.01377 -0.0072 0.0145 1.0000
8.750 1.0080 0.02288 0.01535 -0.0062 0.0105 1.0000
9.000 1.0275 0.02388 0.01649 -0.0055 0.0078 1.0000
9.250 1.0427 0.02542 0.01826 -0.0044 0.0066 1.0000
9.500 1.0515 0.02766 0.02072 -0.0028 0.0059 1.0000
9.750 1.0637 0.02933 0.02259 -0.0015 0.0056 1.0000
10.000 1.0733 0.03121 0.02468 0.0000 0.0053 1.0000
10.250 1.0797 0.03332 0.02702 0.0017 0.0050 1.0000
10.500 1.0819 0.03542 0.02933 0.0037 0.0049 1.0000
10.750 1.0808 0.03772 0.03184 0.0055 0.0048 1.0000
11.000 1.0777 0.04042 0.03476 0.0067 0.0047 1.0000
11.250 1.0736 0.04339 0.03796 0.0073 0.0046 1.0000
11.500 1.0672 0.04683 0.04162 0.0072 0.0045 1.0000
11.750 1.0586 0.05082 0.04584 0.0064 0.0045 1.0000
12.000 1.0481 0.05538 0.05062 0.0047 0.0044 1.0000
12.250 1.0362 0.06054 0.05599 0.0022 0.0045 1.0000
12.500 1.0241 0.06615 0.06179 -0.0010 0.0045 1.0000
12.750 1.0097 0.07268 0.06851 -0.0050 0.0045 1.0000
13.000 0.9936 0.08003 0.07604 -0.0097 0.0045 1.0000
13.250 0.9769 0.08798 0.08414 -0.0148 0.0046 1.0000
13.500 0.9577 0.09703 0.09334 -0.0204 0.0046 1.0000
13.750 0.9403 0.10612 0.10255 -0.0259 0.0048 1.0000
14.000 0.9200 0.11652 0.11305 -0.0319 0.0049 1.0000
14.250 0.8987 0.12774 0.12434 -0.0379 0.0050 1.0000
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Polar data table (+)
Polar graphs
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