MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 500,000 Max Cl/Cd: 82.73 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh108-il-500000.txt Download as CSV file: xf-mh108-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8581 0.10440 0.10168 0.0109 1.0000 0.0071
-14.500 -0.8759 0.09557 0.09272 0.0054 1.0000 0.0070
-14.250 -0.8956 0.08686 0.08387 -0.0002 1.0000 0.0069
-14.000 -0.9072 0.08006 0.07697 -0.0047 1.0000 0.0069
-13.750 -0.9127 0.07460 0.07142 -0.0084 1.0000 0.0068
-13.500 -0.9356 0.06620 0.06283 -0.0143 1.0000 0.0069
-13.250 -0.9652 0.05734 0.05373 -0.0204 1.0000 0.0069
-13.000 -0.9604 0.05458 0.05091 -0.0222 1.0000 0.0068
-12.750 -0.9752 0.04929 0.04545 -0.0251 1.0000 0.0068
-12.250 -0.9987 0.04146 0.03726 -0.0270 1.0000 0.0068
-12.000 -1.0076 0.03858 0.03419 -0.0262 1.0000 0.0068
-11.750 -1.0202 0.03561 0.03099 -0.0240 1.0000 0.0069
-11.500 -1.0188 0.03408 0.02934 -0.0218 1.0000 0.0068
-11.250 -1.0299 0.03124 0.02627 -0.0179 1.0000 0.0069
-11.000 -1.0334 0.02889 0.02373 -0.0145 1.0000 0.0071
-10.750 -1.0250 0.02732 0.02200 -0.0123 1.0000 0.0071
-10.500 -1.0160 0.02569 0.02027 -0.0102 1.0000 0.0074
-10.250 -1.0027 0.02444 0.01892 -0.0084 1.0000 0.0076
-10.000 -0.9871 0.02337 0.01777 -0.0069 1.0000 0.0079
-9.750 -0.9709 0.02226 0.01655 -0.0053 1.0000 0.0081
-9.500 -0.9533 0.02126 0.01546 -0.0039 1.0000 0.0085
-9.250 -0.9349 0.02030 0.01439 -0.0025 1.0000 0.0089
-9.000 -0.9156 0.01943 0.01342 -0.0012 1.0000 0.0092
-8.750 -0.8952 0.01865 0.01254 0.0000 1.0000 0.0095
-8.500 -0.8798 0.01727 0.01107 0.0019 1.0000 0.0102
-8.250 -0.8594 0.01647 0.01022 0.0031 1.0000 0.0109
-8.000 -0.8369 0.01590 0.00960 0.0040 1.0000 0.0122
-7.750 -0.8162 0.01508 0.00870 0.0053 1.0000 0.0138
-7.500 -0.7938 0.01446 0.00808 0.0063 1.0000 0.0165
-7.250 -0.7726 0.01367 0.00727 0.0076 1.0000 0.0216
-7.000 -0.7513 0.01294 0.00657 0.0088 1.0000 0.0324
-6.750 -0.7288 0.01238 0.00612 0.0098 1.0000 0.0452
-6.500 -0.7056 0.01196 0.00575 0.0107 1.0000 0.0571
-6.250 -0.6822 0.01158 0.00542 0.0116 1.0000 0.0690
-6.000 -0.6590 0.01122 0.00512 0.0125 1.0000 0.0816
-5.750 -0.6361 0.01088 0.00483 0.0135 1.0000 0.0948
-5.500 -0.6127 0.01055 0.00458 0.0144 0.9995 0.1100
-5.250 -0.5704 0.01016 0.00428 0.0112 0.9775 0.1328
-5.000 -0.5253 0.00980 0.00398 0.0075 0.9326 0.1573
-4.750 -0.4951 0.00959 0.00371 0.0074 0.8764 0.1786
-4.500 -0.4718 0.00948 0.00350 0.0086 0.8321 0.1987
-4.250 -0.4481 0.00933 0.00330 0.0096 0.7956 0.2212
-4.000 -0.4236 0.00919 0.00311 0.0105 0.7640 0.2454
-3.750 -0.3986 0.00904 0.00292 0.0112 0.7359 0.2705
-3.500 -0.3734 0.00887 0.00275 0.0119 0.7106 0.2989
-3.250 -0.3481 0.00872 0.00260 0.0125 0.6868 0.3285
-2.750 -0.2971 0.00841 0.00233 0.0137 0.6425 0.3936
-2.500 -0.2714 0.00826 0.00222 0.0142 0.6226 0.4279
-2.000 -0.2205 0.00796 0.00202 0.0154 0.5852 0.5036
-1.750 -0.1951 0.00782 0.00195 0.0161 0.5675 0.5429
-1.500 -0.1701 0.00767 0.00188 0.0168 0.5505 0.5866
-1.250 -0.1453 0.00751 0.00183 0.0176 0.5347 0.6333
-1.000 -0.1206 0.00737 0.00180 0.0185 0.5196 0.6798
-0.750 -0.0958 0.00725 0.00178 0.0194 0.5047 0.7261
-0.500 -0.0709 0.00715 0.00178 0.0203 0.4901 0.7709
-0.250 -0.0453 0.00709 0.00180 0.0211 0.4763 0.8127
0.000 -0.0185 0.00708 0.00183 0.0217 0.4633 0.8513
0.250 0.0110 0.00712 0.00190 0.0218 0.4505 0.8837
0.500 0.0433 0.00721 0.00198 0.0212 0.4376 0.9094
0.750 0.0788 0.00735 0.00207 0.0199 0.4249 0.9275
1.000 0.1140 0.00751 0.00217 0.0186 0.4133 0.9413
1.250 0.1502 0.00770 0.00229 0.0171 0.4027 0.9517
1.500 0.1886 0.00789 0.00240 0.0151 0.3920 0.9584
1.750 0.2264 0.00805 0.00252 0.0133 0.3821 0.9651
2.000 0.2641 0.00823 0.00262 0.0113 0.3732 0.9708
2.250 0.3044 0.00838 0.00272 0.0088 0.3641 0.9752
2.500 0.3393 0.00854 0.00284 0.0075 0.3562 0.9818
2.750 0.3809 0.00867 0.00290 0.0046 0.3481 0.9847
3.000 0.4211 0.00875 0.00297 0.0020 0.3404 0.9886
3.250 0.4587 0.00892 0.00307 0.0000 0.3332 0.9929
3.500 0.4990 0.00894 0.00311 -0.0026 0.3260 0.9961
3.750 0.5385 0.00905 0.00316 -0.0052 0.3191 0.9994
4.000 0.5656 0.00910 0.00323 -0.0051 0.3136 1.0000
4.250 0.5893 0.00917 0.00330 -0.0043 0.3077 1.0000
4.500 0.6130 0.00930 0.00340 -0.0035 0.3024 1.0000
4.750 0.6371 0.00936 0.00350 -0.0028 0.2967 1.0000
5.000 0.6609 0.00949 0.00361 -0.0020 0.2911 1.0000
5.250 0.6849 0.00961 0.00375 -0.0013 0.2857 1.0000
5.500 0.7090 0.00971 0.00387 -0.0005 0.2796 1.0000
5.750 0.7326 0.00991 0.00404 0.0003 0.2739 1.0000
6.000 0.7571 0.00998 0.00418 0.0010 0.2675 1.0000
6.250 0.7808 0.01017 0.00435 0.0017 0.2610 1.0000
6.500 0.8052 0.01028 0.00452 0.0024 0.2545 1.0000
6.750 0.8290 0.01047 0.00469 0.0032 0.2470 1.0000
7.000 0.8533 0.01060 0.00488 0.0039 0.2394 1.0000
7.250 0.8769 0.01082 0.00509 0.0047 0.2309 1.0000
7.500 0.9011 0.01098 0.00529 0.0054 0.2212 1.0000
7.750 0.9248 0.01120 0.00552 0.0061 0.2108 1.0000
8.000 0.9481 0.01146 0.00578 0.0069 0.1994 1.0000
8.250 0.9710 0.01176 0.00607 0.0077 0.1865 1.0000
8.500 0.9934 0.01212 0.00641 0.0086 0.1726 1.0000
8.750 1.0154 0.01253 0.00679 0.0095 0.1595 1.0000
9.000 1.0368 0.01298 0.00721 0.0104 0.1473 1.0000
9.500 1.0787 0.01396 0.00814 0.0124 0.1229 1.0000
9.750 1.0993 0.01446 0.00864 0.0134 0.1113 1.0000
10.000 1.1195 0.01499 0.00918 0.0145 0.1007 1.0000
10.250 1.1390 0.01557 0.00975 0.0156 0.0899 1.0000
10.500 1.1577 0.01620 0.01036 0.0167 0.0798 1.0000
10.750 1.1752 0.01691 0.01103 0.0180 0.0693 1.0000
11.250 1.2071 0.01847 0.01255 0.0209 0.0496 1.0000
11.500 1.2215 0.01930 0.01338 0.0224 0.0416 1.0000
11.750 1.2340 0.02024 0.01434 0.0242 0.0347 1.0000
12.000 1.2433 0.02133 0.01543 0.0262 0.0286 1.0000
12.250 1.2505 0.02245 0.01656 0.0283 0.0238 1.0000
12.500 1.2531 0.02357 0.01775 0.0311 0.0206 1.0000
12.750 1.2491 0.02502 0.01924 0.0341 0.0180 1.0000
13.000 1.2430 0.02711 0.02142 0.0358 0.0162 1.0000
13.250 1.2415 0.02940 0.02383 0.0360 0.0148 1.0000
13.500 1.2373 0.03242 0.02694 0.0353 0.0136 1.0000
13.750 1.2265 0.03664 0.03128 0.0336 0.0126 1.0000
14.000 1.2173 0.04092 0.03568 0.0318 0.0118 1.0000
14.250 1.2092 0.04512 0.04001 0.0300 0.0109 1.0000
14.500 1.1989 0.04965 0.04465 0.0280 0.0106 1.0000
14.750 1.1862 0.05452 0.04963 0.0260 0.0103 1.0000
15.000 1.1710 0.05975 0.05498 0.0238 0.0102 1.0000
15.250 1.1567 0.06493 0.06025 0.0216 0.0099 1.0000
15.500 1.1398 0.07053 0.06595 0.0192 0.0096 1.0000
15.750 1.1248 0.07612 0.07163 0.0167 0.0093 1.0000
16.000 1.1002 0.08336 0.07897 0.0134 0.0089 1.0000
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Polar data table (+)
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