MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.09 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh80-il-1000000-n5.txt Download as CSV file: xf-mh80-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8074 0.04894 0.04653 -0.0104 0.7647 0.0042
-10.500 -0.8522 0.04261 0.03988 -0.0092 0.7452 0.0042
-10.250 -0.8761 0.03743 0.03430 -0.0070 0.7289 0.0042
-10.000 -0.8803 0.03364 0.03013 -0.0052 0.7113 0.0042
-9.750 -0.8757 0.03060 0.02674 -0.0036 0.6939 0.0042
-9.500 -0.8657 0.02805 0.02385 -0.0021 0.6777 0.0042
-9.250 -0.8513 0.02602 0.02153 -0.0008 0.6619 0.0042
-9.000 -0.8345 0.02421 0.01944 0.0004 0.6461 0.0042
-8.750 -0.8154 0.02270 0.01768 0.0014 0.6311 0.0042
-8.500 -0.7945 0.02142 0.01618 0.0023 0.6166 0.0042
-8.250 -0.7727 0.02025 0.01480 0.0032 0.6023 0.0042
-8.000 -0.7499 0.01920 0.01356 0.0039 0.5892 0.0042
-7.750 -0.7263 0.01829 0.01247 0.0047 0.5754 0.0042
-7.500 -0.7021 0.01746 0.01147 0.0053 0.5620 0.0042
-7.250 -0.6773 0.01672 0.01058 0.0059 0.5492 0.0042
-7.000 -0.6522 0.01602 0.00975 0.0065 0.5373 0.0042
-6.750 -0.6266 0.01541 0.00901 0.0070 0.5251 0.0043
-6.500 -0.6007 0.01484 0.00832 0.0076 0.5130 0.0043
-6.250 -0.5745 0.01432 0.00770 0.0080 0.5024 0.0043
-6.000 -0.5485 0.01375 0.00702 0.0085 0.4910 0.0043
-5.750 -0.5225 0.01317 0.00633 0.0090 0.4800 0.0044
-5.500 -0.4960 0.01268 0.00576 0.0095 0.4704 0.0045
-5.000 -0.4419 0.01192 0.00484 0.0102 0.4496 0.0047
-4.750 -0.4144 0.01165 0.00450 0.0105 0.4405 0.0048
-4.500 -0.3868 0.01138 0.00418 0.0108 0.4317 0.0050
-4.250 -0.3590 0.01116 0.00390 0.0110 0.4228 0.0052
-4.000 -0.3311 0.01095 0.00363 0.0113 0.4129 0.0054
-3.750 -0.3032 0.01075 0.00338 0.0115 0.4046 0.0058
-3.500 -0.2751 0.01058 0.00316 0.0117 0.3964 0.0061
-3.250 -0.2470 0.01040 0.00294 0.0119 0.3893 0.0065
-3.000 -0.2189 0.01023 0.00274 0.0121 0.3813 0.0073
-2.750 -0.1906 0.01011 0.00257 0.0123 0.3736 0.0081
-2.500 -0.1623 0.00998 0.00241 0.0124 0.3652 0.0094
-2.250 -0.1340 0.00986 0.00227 0.0126 0.3583 0.0118
-2.000 -0.1057 0.00973 0.00214 0.0127 0.3518 0.0169
-1.750 -0.0775 0.00960 0.00203 0.0129 0.3450 0.0269
-1.500 -0.0496 0.00941 0.00190 0.0130 0.3391 0.0483
-1.250 -0.0221 0.00914 0.00179 0.0132 0.3318 0.0955
-1.000 0.0055 0.00891 0.00171 0.0133 0.3256 0.1452
-0.750 0.0329 0.00864 0.00164 0.0135 0.3200 0.2071
-0.500 0.0607 0.00846 0.00159 0.0136 0.3141 0.2600
-0.250 0.0873 0.00809 0.00154 0.0138 0.3094 0.3631
0.250 0.1414 0.00760 0.00148 0.0142 0.2978 0.5212
0.500 0.1683 0.00735 0.00146 0.0145 0.2934 0.6031
0.750 0.1949 0.00712 0.00146 0.0148 0.2890 0.6811
1.000 0.2204 0.00687 0.00148 0.0155 0.2844 0.7698
1.250 0.2464 0.00678 0.00155 0.0162 0.2800 0.8310
1.500 0.2737 0.00677 0.00161 0.0166 0.2760 0.8626
1.750 0.3013 0.00682 0.00167 0.0170 0.2714 0.8830
2.000 0.3285 0.00690 0.00174 0.0174 0.2671 0.9021
2.250 0.3553 0.00696 0.00182 0.0179 0.2640 0.9201
2.500 0.3822 0.00703 0.00189 0.0185 0.2608 0.9339
2.750 0.4091 0.00712 0.00196 0.0189 0.2567 0.9452
3.000 0.4357 0.00723 0.00205 0.0195 0.2525 0.9554
3.250 0.4641 0.00732 0.00213 0.0196 0.2494 0.9635
3.500 0.4914 0.00741 0.00220 0.0200 0.2469 0.9714
3.750 0.5237 0.00751 0.00228 0.0192 0.2434 0.9746
4.000 0.5548 0.00763 0.00236 0.0186 0.2394 0.9771
4.250 0.5853 0.00776 0.00246 0.0181 0.2356 0.9795
4.500 0.6154 0.00785 0.00254 0.0177 0.2335 0.9820
4.750 0.6459 0.00795 0.00264 0.0171 0.2309 0.9840
5.000 0.6782 0.00807 0.00273 0.0162 0.2275 0.9850
5.250 0.7101 0.00821 0.00284 0.0153 0.2237 0.9862
5.500 0.7421 0.00835 0.00297 0.0145 0.2205 0.9873
5.750 0.7741 0.00846 0.00308 0.0136 0.2186 0.9886
6.000 0.8056 0.00858 0.00320 0.0128 0.2159 0.9900
6.250 0.8366 0.00872 0.00334 0.0120 0.2125 0.9915
6.500 0.8670 0.00889 0.00348 0.0114 0.2090 0.9931
6.750 0.8981 0.00905 0.00364 0.0106 0.2061 0.9945
7.000 0.9300 0.00918 0.00379 0.0097 0.2041 0.9957
7.250 0.9615 0.00932 0.00394 0.0088 0.2013 0.9970
7.500 0.9924 0.00950 0.00411 0.0080 0.1978 0.9984
7.750 1.0231 0.00970 0.00431 0.0072 0.1942 0.9997
8.000 1.0488 0.00987 0.00450 0.0075 0.1919 1.0000
8.250 1.0731 0.01003 0.00468 0.0081 0.1895 1.0000
8.500 1.0975 0.01022 0.00487 0.0087 0.1863 1.0000
8.750 1.1218 0.01043 0.00509 0.0092 0.1830 1.0000
9.000 1.1461 0.01068 0.00534 0.0096 0.1793 1.0000
9.250 1.1713 0.01086 0.00555 0.0100 0.1770 1.0000
9.500 1.1965 0.01107 0.00578 0.0103 0.1738 1.0000
9.750 1.2215 0.01133 0.00604 0.0106 0.1700 1.0000
10.000 1.2464 0.01163 0.00634 0.0108 0.1661 1.0000
10.250 1.2720 0.01185 0.00659 0.0110 0.1631 1.0000
10.500 1.2972 0.01212 0.00688 0.0111 0.1595 1.0000
10.750 1.3219 0.01244 0.00721 0.0113 0.1555 1.0000
11.000 1.3467 0.01275 0.00754 0.0115 0.1520 1.0000
11.250 1.3715 0.01305 0.00787 0.0117 0.1483 1.0000
11.500 1.3954 0.01343 0.00826 0.0119 0.1438 1.0000
11.750 1.4192 0.01381 0.00866 0.0121 0.1398 1.0000
12.000 1.4430 0.01416 0.00904 0.0123 0.1359 1.0000
12.250 1.4656 0.01462 0.00951 0.0126 0.1313 1.0000
12.500 1.4880 0.01506 0.00998 0.0129 0.1270 1.0000
12.750 1.5094 0.01556 0.01049 0.0133 0.1215 1.0000
13.000 1.5291 0.01617 0.01110 0.0139 0.1157 1.0000
13.250 1.5465 0.01690 0.01182 0.0146 0.1076 1.0000
13.500 1.5619 0.01771 0.01262 0.0154 0.0992 1.0000
13.750 1.5739 0.01866 0.01356 0.0166 0.0914 1.0000
14.000 1.5770 0.01983 0.01472 0.0187 0.0838 1.0000
14.250 1.5756 0.02117 0.01610 0.0209 0.0791 1.0000
14.500 1.5749 0.02294 0.01791 0.0219 0.0757 1.0000
14.750 1.5691 0.02553 0.02053 0.0221 0.0691 1.0000
15.000 1.5652 0.02829 0.02335 0.0218 0.0657 1.0000
15.250 1.5630 0.03109 0.02622 0.0212 0.0628 1.0000
15.500 1.5488 0.03527 0.03046 0.0201 0.0585 1.0000
15.750 1.5296 0.04019 0.03544 0.0186 0.0532 1.0000
16.000 1.5060 0.04574 0.04106 0.0167 0.0498 1.0000
16.250 1.4907 0.05045 0.04587 0.0151 0.0481 1.0000
16.500 1.4775 0.05500 0.05052 0.0135 0.0477 1.0000
16.750 1.4645 0.05961 0.05524 0.0119 0.0475 1.0000
17.000 1.4385 0.06619 0.06190 0.0092 0.0448 1.0000
17.250 1.4250 0.07127 0.06709 0.0070 0.0445 1.0000
17.500 1.4089 0.07679 0.07271 0.0047 0.0439 1.0000
17.750 1.3833 0.08389 0.07988 0.0015 0.0410 1.0000
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Polar data table (+)
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