MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 100,000 Max Cl/Cd: 28.32 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh80-il-100000.txt Download as CSV file: xf-mh80-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4500 0.09849 0.09464 0.0140 1.0000 0.1079
-8.250 -0.4717 0.09444 0.09071 0.0058 1.0000 0.1128
-8.000 -0.5184 0.09015 0.08640 -0.0055 1.0000 0.1138
-7.750 -0.4526 0.08609 0.08253 0.0050 1.0000 0.1181
-7.500 -0.4478 0.08251 0.07903 0.0028 1.0000 0.1224
-7.250 -0.4996 0.07795 0.07425 -0.0111 1.0000 0.1289
-7.000 -0.4574 0.07309 0.06976 -0.0071 1.0000 0.1322
-6.750 -0.4418 0.06971 0.06646 -0.0098 1.0000 0.1395
-6.500 -0.4223 0.06494 0.06162 -0.0153 0.9232 0.1505
-6.000 -0.4163 0.05924 0.05553 -0.0141 0.8462 0.1659
-5.750 -0.4223 0.04043 0.03452 -0.0187 0.8405 0.0651
-5.500 -0.4069 0.03778 0.03149 -0.0163 0.8177 0.0623
-5.250 -0.3907 0.03485 0.02814 -0.0142 0.7975 0.0603
-5.000 -0.3721 0.03136 0.02370 -0.0116 0.7793 0.0557
-4.750 -0.3492 0.02975 0.02153 -0.0096 0.7600 0.0545
-4.500 -0.3255 0.02782 0.01924 -0.0081 0.7420 0.0546
-4.250 -0.3007 0.02581 0.01700 -0.0068 0.7249 0.0554
-4.000 -0.2755 0.02434 0.01543 -0.0057 0.7081 0.0576
-3.750 -0.2498 0.02339 0.01427 -0.0045 0.6920 0.0629
-3.500 -0.2248 0.02214 0.01304 -0.0034 0.6769 0.0689
-3.250 -0.2003 0.02102 0.01184 -0.0019 0.6629 0.0774
-3.000 -0.1765 0.02005 0.01094 -0.0006 0.6484 0.0977
-2.750 -0.1567 0.01816 0.00983 0.0011 0.6349 0.2047
-2.500 -0.1419 0.01635 0.00938 0.0034 0.6226 0.4630
-2.250 -0.1098 0.01555 0.00991 0.0065 0.6092 0.8266
-2.000 -0.0384 0.01660 0.01055 0.0026 0.5908 0.9408
-1.750 0.0546 0.01686 0.01024 -0.0083 0.5703 0.9810
-1.500 0.1172 0.01666 0.00962 -0.0150 0.5542 1.0000
-1.250 0.1384 0.01664 0.00932 -0.0141 0.5444 1.0000
-1.000 0.1616 0.01668 0.00920 -0.0136 0.5323 1.0000
-0.750 0.1844 0.01676 0.00908 -0.0130 0.5225 1.0000
-0.500 0.2076 0.01683 0.00896 -0.0123 0.5127 1.0000
-0.250 0.2315 0.01699 0.00898 -0.0118 0.5026 1.0000
0.000 0.2544 0.01711 0.00888 -0.0109 0.4942 1.0000
0.250 0.2786 0.01733 0.00903 -0.0105 0.4842 1.0000
0.500 0.3017 0.01751 0.00899 -0.0096 0.4770 1.0000
0.750 0.3261 0.01780 0.00926 -0.0093 0.4677 1.0000
1.000 0.3494 0.01800 0.00927 -0.0084 0.4607 1.0000
1.250 0.3737 0.01835 0.00959 -0.0080 0.4522 1.0000
1.500 0.3972 0.01860 0.00970 -0.0072 0.4453 1.0000
1.750 0.4211 0.01900 0.01005 -0.0067 0.4385 1.0000
2.000 0.4449 0.01936 0.01037 -0.0061 0.4312 1.0000
2.250 0.4682 0.01965 0.01046 -0.0051 0.4260 1.0000
2.500 0.4921 0.02019 0.01110 -0.0048 0.4181 1.0000
2.750 0.5156 0.02053 0.01136 -0.0041 0.4125 1.0000
3.000 0.5389 0.02103 0.01179 -0.0034 0.4073 1.0000
3.250 0.5621 0.02163 0.01247 -0.0030 0.4004 1.0000
3.500 0.5855 0.02196 0.01270 -0.0021 0.3953 1.0000
3.750 0.6083 0.02260 0.01335 -0.0015 0.3900 1.0000
4.000 0.6308 0.02333 0.01418 -0.0010 0.3840 1.0000
4.250 0.6541 0.02375 0.01452 -0.0002 0.3794 1.0000
4.500 0.6769 0.02436 0.01510 0.0005 0.3750 1.0000
4.750 0.6977 0.02534 0.01626 0.0009 0.3685 1.0000
5.000 0.7207 0.02584 0.01673 0.0017 0.3640 1.0000
5.250 0.7447 0.02630 0.01706 0.0025 0.3606 1.0000
5.500 0.7624 0.02781 0.01886 0.0028 0.3545 1.0000
5.750 0.7839 0.02855 0.01966 0.0034 0.3495 1.0000
6.000 0.8082 0.02887 0.01988 0.0043 0.3458 1.0000
6.250 0.8262 0.03032 0.02148 0.0047 0.3412 1.0000
6.500 0.8416 0.03207 0.02348 0.0051 0.3357 1.0000
6.750 0.8651 0.03254 0.02393 0.0058 0.3317 1.0000
7.000 0.8916 0.03272 0.02398 0.0066 0.3286 1.0000
7.250 0.8945 0.03612 0.02783 0.0066 0.3221 1.0000
7.500 0.9084 0.03796 0.02981 0.0070 0.3177 1.0000
7.750 0.9361 0.03795 0.02973 0.0078 0.3146 1.0000
8.000 0.9642 0.03812 0.02980 0.0085 0.3118 1.0000
8.250 0.7579 0.06778 0.06025 -0.0031 0.2982 1.0000
8.500 0.9222 0.04970 0.04213 0.0073 0.2992 1.0000
8.750 0.9795 0.04635 0.03864 0.0092 0.2977 1.0000
9.000 0.6894 0.08968 0.08218 -0.0121 0.2974 1.0000
9.250 0.5915 0.10640 0.09899 -0.0230 0.3340 1.0000
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Polar data table (+)
Polar graphs
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