MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 50,000 Max Cl/Cd: 25.86 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh108-il-50000-n5.txt Download as CSV file: xf-mh108-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6814 0.09435 0.08769 -0.0002 1.0000 0.0475
-11.000 -0.7045 0.08447 0.07782 -0.0068 1.0000 0.0465
-10.750 -0.7346 0.07473 0.06800 -0.0141 1.0000 0.0450
-10.500 -0.7677 0.06680 0.05988 -0.0192 1.0000 0.0434
-10.250 -0.7920 0.06150 0.05436 -0.0205 1.0000 0.0430
-10.000 -0.8083 0.05769 0.05034 -0.0195 1.0000 0.0435
-9.750 -0.8173 0.05419 0.04659 -0.0182 1.0000 0.0447
-9.500 -0.8222 0.05061 0.04264 -0.0168 1.0000 0.0466
-9.250 -0.8236 0.04691 0.03840 -0.0151 1.0000 0.0490
-9.000 -0.8148 0.04428 0.03566 -0.0139 1.0000 0.0517
-8.750 -0.8037 0.04207 0.03331 -0.0125 1.0000 0.0558
-8.500 -0.7923 0.03930 0.03003 -0.0110 1.0000 0.0616
-8.250 -0.7774 0.03757 0.02837 -0.0098 1.0000 0.0677
-8.000 -0.7618 0.03553 0.02608 -0.0085 1.0000 0.0763
-7.750 -0.7448 0.03377 0.02403 -0.0072 1.0000 0.0871
-7.500 -0.7271 0.03230 0.02251 -0.0060 1.0000 0.0986
-7.250 -0.7087 0.03092 0.02107 -0.0048 1.0000 0.1123
-7.000 -0.6892 0.02961 0.01965 -0.0037 1.0000 0.1271
-6.750 -0.6691 0.02843 0.01846 -0.0026 1.0000 0.1429
-6.500 -0.6489 0.02738 0.01743 -0.0016 1.0000 0.1599
-6.250 -0.6277 0.02636 0.01636 -0.0005 1.0000 0.1781
-6.000 -0.6060 0.02542 0.01533 0.0004 1.0000 0.1993
-5.750 -0.5845 0.02454 0.01455 0.0014 1.0000 0.2197
-5.500 -0.5624 0.02373 0.01372 0.0024 1.0000 0.2438
-5.250 -0.5406 0.02297 0.01303 0.0033 1.0000 0.2688
-5.000 -0.5187 0.02226 0.01237 0.0043 1.0000 0.2957
-4.750 -0.4970 0.02160 0.01180 0.0053 1.0000 0.3257
-4.500 -0.4755 0.02099 0.01128 0.0064 1.0000 0.3574
-4.250 -0.4546 0.02043 0.01084 0.0076 1.0000 0.3914
-4.000 -0.4346 0.01990 0.01047 0.0090 1.0000 0.4268
-3.750 -0.4159 0.01944 0.01014 0.0105 1.0000 0.4650
-3.500 -0.3994 0.01903 0.00994 0.0125 1.0000 0.5031
-3.250 -0.3701 0.01867 0.00978 0.0119 0.9814 0.5523
-3.000 -0.3255 0.01836 0.00965 0.0091 0.9437 0.6123
-2.750 -0.2789 0.01818 0.00957 0.0065 0.9092 0.6726
-2.500 -0.2333 0.01815 0.00957 0.0046 0.8744 0.7270
-2.250 -0.1902 0.01826 0.00957 0.0033 0.8399 0.7746
-2.000 -0.1488 0.01846 0.00959 0.0024 0.8070 0.8143
-1.750 -0.1105 0.01870 0.00959 0.0018 0.7756 0.8492
-1.500 -0.0710 0.01895 0.00957 0.0009 0.7463 0.8792
-1.250 -0.0272 0.01919 0.00954 -0.0012 0.7181 0.9044
-1.000 0.0161 0.01937 0.00944 -0.0035 0.6913 0.9284
-0.750 0.0607 0.01948 0.00931 -0.0064 0.6663 0.9507
-0.500 0.1057 0.01953 0.00909 -0.0097 0.6435 0.9714
-0.250 0.1532 0.01949 0.00884 -0.0138 0.6206 0.9907
0.000 0.1873 0.01945 0.00861 -0.0155 0.6017 1.0000
0.250 0.2074 0.01949 0.00851 -0.0145 0.5860 1.0000
0.500 0.2280 0.01958 0.00847 -0.0136 0.5713 1.0000
0.750 0.2489 0.01971 0.00849 -0.0126 0.5571 1.0000
1.000 0.2702 0.01986 0.00855 -0.0117 0.5436 1.0000
1.250 0.2919 0.02005 0.00866 -0.0108 0.5311 1.0000
1.500 0.3137 0.02027 0.00879 -0.0099 0.5195 1.0000
1.750 0.3354 0.02049 0.00891 -0.0089 0.5089 1.0000
2.000 0.3574 0.02077 0.00918 -0.0081 0.4975 1.0000
2.250 0.3802 0.02108 0.00946 -0.0073 0.4871 1.0000
2.500 0.4028 0.02139 0.00970 -0.0065 0.4778 1.0000
2.750 0.4253 0.02174 0.01004 -0.0057 0.4679 1.0000
3.000 0.4480 0.02214 0.01047 -0.0049 0.4587 1.0000
3.250 0.4706 0.02249 0.01075 -0.0040 0.4508 1.0000
3.500 0.4930 0.02296 0.01130 -0.0033 0.4411 1.0000
3.750 0.5156 0.02338 0.01171 -0.0024 0.4334 1.0000
4.000 0.5380 0.02387 0.01226 -0.0016 0.4246 1.0000
4.250 0.5604 0.02437 0.01281 -0.0007 0.4164 1.0000
4.500 0.5828 0.02484 0.01333 0.0002 0.4084 1.0000
4.750 0.6047 0.02543 0.01402 0.0010 0.3997 1.0000
5.000 0.6273 0.02588 0.01446 0.0019 0.3924 1.0000
5.250 0.6485 0.02657 0.01531 0.0027 0.3832 1.0000
5.500 0.6713 0.02698 0.01572 0.0038 0.3762 1.0000
5.750 0.6917 0.02775 0.01669 0.0046 0.3667 1.0000
6.000 0.7133 0.02833 0.01734 0.0056 0.3586 1.0000
6.250 0.7344 0.02895 0.01806 0.0065 0.3500 1.0000
6.500 0.7544 0.02971 0.01901 0.0075 0.3409 1.0000
6.750 0.7771 0.03012 0.01943 0.0086 0.3333 1.0000
7.000 0.7952 0.03107 0.02062 0.0095 0.3231 1.0000
7.250 0.8156 0.03173 0.02139 0.0106 0.3144 1.0000
7.500 0.8360 0.03233 0.02210 0.0117 0.3054 1.0000
7.750 0.8530 0.03332 0.02334 0.0128 0.2952 1.0000
8.000 0.8736 0.03389 0.02399 0.0139 0.2866 1.0000
8.250 0.8916 0.03466 0.02492 0.0150 0.2767 1.0000
8.500 0.9063 0.03581 0.02630 0.0162 0.2664 1.0000
8.750 0.9251 0.03644 0.02703 0.0174 0.2573 1.0000
9.000 0.9419 0.03719 0.02793 0.0187 0.2474 1.0000
9.250 0.9522 0.03866 0.02970 0.0199 0.2372 1.0000
9.500 0.9672 0.03951 0.03067 0.0212 0.2278 1.0000
9.750 0.9836 0.04008 0.03132 0.0226 0.2183 1.0000
10.000 0.9864 0.04209 0.03360 0.0240 0.2087 1.0000
10.250 0.9967 0.04316 0.03477 0.0254 0.1998 1.0000
10.500 1.0073 0.04407 0.03576 0.0268 0.1909 1.0000
10.750 0.9996 0.04682 0.03872 0.0282 0.1834 1.0000
11.000 1.0132 0.04719 0.03906 0.0298 0.1749 1.0000
11.250 0.9850 0.05165 0.04374 0.0305 0.1704 1.0000
11.500 1.0027 0.05162 0.04367 0.0320 0.1617 1.0000
11.750 0.9633 0.05885 0.05108 0.0292 0.1589 1.0000
12.000 0.8897 0.07340 0.06569 0.0207 0.1574 1.0000
12.250 0.8533 0.08325 0.07551 0.0155 0.1518 1.0000
12.500 0.8480 0.08766 0.07994 0.0140 0.1463 1.0000
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Polar data table (+)
Polar graphs
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