MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 500,000 Max Cl/Cd: 79.76 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh108-il-500000-n5.txt Download as CSV file: xf-mh108-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9964 0.08329 0.07989 0.0002 1.0000 0.0034
-14.750 -1.0240 0.07406 0.07050 -0.0052 1.0000 0.0033
-14.500 -1.0504 0.06507 0.06135 -0.0107 1.0000 0.0033
-14.250 -1.0710 0.05720 0.05333 -0.0159 1.0000 0.0033
-14.000 -1.0868 0.05058 0.04652 -0.0203 1.0000 0.0033
-13.750 -1.1005 0.04501 0.04078 -0.0237 1.0000 0.0033
-13.500 -1.1100 0.04084 0.03646 -0.0256 1.0000 0.0034
-13.250 -1.1166 0.03764 0.03313 -0.0262 1.0000 0.0035
-13.000 -1.1236 0.03491 0.03024 -0.0255 1.0000 0.0034
-12.750 -1.1277 0.03277 0.02798 -0.0239 1.0000 0.0034
-12.500 -1.1271 0.03116 0.02625 -0.0220 1.0000 0.0035
-12.250 -1.1274 0.02961 0.02457 -0.0193 1.0000 0.0035
-12.000 -1.1245 0.02834 0.02319 -0.0165 1.0000 0.0036
-11.750 -1.1187 0.02721 0.02195 -0.0139 1.0000 0.0037
-11.500 -1.1086 0.02605 0.02068 -0.0118 1.0000 0.0038
-11.250 -1.0961 0.02498 0.01950 -0.0100 1.0000 0.0039
-11.000 -1.0819 0.02395 0.01837 -0.0084 1.0000 0.0040
-10.750 -1.0667 0.02295 0.01725 -0.0068 1.0000 0.0041
-10.500 -1.0497 0.02204 0.01622 -0.0054 1.0000 0.0043
-10.250 -1.0317 0.02119 0.01527 -0.0041 1.0000 0.0044
-10.000 -1.0126 0.02040 0.01439 -0.0028 1.0000 0.0046
-9.750 -0.9929 0.01964 0.01353 -0.0017 1.0000 0.0047
-9.500 -0.9738 0.01876 0.01256 -0.0004 1.0000 0.0049
-9.250 -0.9533 0.01802 0.01175 0.0007 1.0000 0.0053
-9.000 -0.9317 0.01739 0.01106 0.0016 1.0000 0.0056
-8.750 -0.9095 0.01679 0.01038 0.0026 1.0000 0.0060
-8.500 -0.8868 0.01626 0.00979 0.0034 1.0000 0.0065
-8.250 -0.8643 0.01569 0.00917 0.0044 1.0000 0.0072
-8.000 -0.8416 0.01513 0.00858 0.0052 1.0000 0.0084
-7.750 -0.8182 0.01465 0.00805 0.0061 1.0000 0.0095
-7.500 -0.7955 0.01410 0.00750 0.0070 1.0000 0.0116
-7.250 -0.7722 0.01362 0.00699 0.0079 1.0000 0.0143
-7.000 -0.7489 0.01316 0.00654 0.0087 1.0000 0.0186
-6.750 -0.7225 0.01268 0.00610 0.0089 0.9919 0.0254
-6.500 -0.6783 0.01216 0.00561 0.0053 0.9260 0.0368
-6.250 -0.6511 0.01192 0.00524 0.0056 0.8582 0.0470
-6.000 -0.6286 0.01172 0.00491 0.0069 0.8113 0.0572
-5.750 -0.6050 0.01151 0.00461 0.0079 0.7747 0.0682
-5.500 -0.5807 0.01129 0.00433 0.0086 0.7430 0.0816
-5.250 -0.5559 0.01107 0.00406 0.0093 0.7149 0.0961
-5.000 -0.5306 0.01087 0.00381 0.0099 0.6894 0.1095
-4.750 -0.5049 0.01069 0.00357 0.0104 0.6664 0.1227
-4.500 -0.4790 0.01051 0.00335 0.0109 0.6455 0.1369
-4.250 -0.4530 0.01034 0.00315 0.0114 0.6255 0.1532
-4.000 -0.4269 0.01018 0.00296 0.0118 0.6059 0.1703
-3.750 -0.4005 0.01003 0.00278 0.0122 0.5878 0.1863
-3.500 -0.3743 0.00986 0.00261 0.0126 0.5715 0.2057
-3.250 -0.3478 0.00972 0.00246 0.0129 0.5550 0.2253
-3.000 -0.3214 0.00958 0.00232 0.0133 0.5387 0.2466
-2.750 -0.2949 0.00945 0.00219 0.0137 0.5233 0.2686
-2.500 -0.2683 0.00931 0.00208 0.0140 0.5095 0.2918
-2.250 -0.2418 0.00918 0.00197 0.0143 0.4959 0.3183
-2.000 -0.2153 0.00905 0.00188 0.0147 0.4821 0.3467
-1.750 -0.1887 0.00893 0.00180 0.0150 0.4688 0.3739
-1.500 -0.1622 0.00882 0.00173 0.0154 0.4562 0.4033
-1.250 -0.1357 0.00870 0.00166 0.0157 0.4450 0.4343
-0.750 -0.0829 0.00849 0.00157 0.0165 0.4230 0.4971
-0.500 -0.0567 0.00838 0.00153 0.0170 0.4121 0.5325
-0.250 -0.0308 0.00827 0.00151 0.0175 0.4022 0.5700
0.000 -0.0050 0.00816 0.00150 0.0180 0.3930 0.6104
0.250 0.0205 0.00804 0.00150 0.0186 0.3847 0.6525
0.500 0.0459 0.00795 0.00151 0.0193 0.3762 0.6938
0.750 0.0713 0.00785 0.00154 0.0200 0.3677 0.7356
1.000 0.0969 0.00778 0.00157 0.0207 0.3599 0.7758
1.250 0.1229 0.00771 0.00163 0.0214 0.3528 0.8155
1.500 0.1502 0.00770 0.00170 0.0218 0.3460 0.8520
1.750 0.1803 0.00773 0.00179 0.0216 0.3387 0.8834
2.000 0.2139 0.00782 0.00190 0.0206 0.3318 0.9083
2.250 0.2498 0.00793 0.00200 0.0191 0.3249 0.9260
2.500 0.2859 0.00808 0.00212 0.0175 0.3180 0.9387
2.750 0.3224 0.00819 0.00222 0.0158 0.3116 0.9475
3.000 0.3552 0.00834 0.00233 0.0149 0.3050 0.9561
3.250 0.3900 0.00846 0.00244 0.0136 0.2992 0.9621
3.500 0.4205 0.00860 0.00256 0.0131 0.2930 0.9693
3.750 0.4560 0.00874 0.00267 0.0115 0.2872 0.9731
4.000 0.4892 0.00886 0.00280 0.0105 0.2811 0.9781
4.250 0.5210 0.00902 0.00293 0.0097 0.2753 0.9826
4.500 0.5575 0.00913 0.00305 0.0078 0.2694 0.9856
4.750 0.5936 0.00926 0.00318 0.0061 0.2631 0.9895
5.000 0.6284 0.00941 0.00333 0.0046 0.2572 0.9933
5.250 0.6643 0.00952 0.00345 0.0029 0.2503 0.9958
5.500 0.6987 0.00966 0.00358 0.0014 0.2435 0.9981
5.750 0.7324 0.00979 0.00372 0.0001 0.2362 1.0000
6.000 0.7563 0.00995 0.00388 0.0009 0.2293 1.0000
6.250 0.7803 0.01011 0.00406 0.0016 0.2212 1.0000
6.500 0.8042 0.01029 0.00424 0.0023 0.2139 1.0000
6.750 0.8279 0.01051 0.00444 0.0031 0.2042 1.0000
7.000 0.8516 0.01072 0.00466 0.0039 0.1945 1.0000
7.250 0.8750 0.01097 0.00491 0.0046 0.1837 1.0000
7.500 0.8980 0.01127 0.00519 0.0054 0.1719 1.0000
7.750 0.9207 0.01161 0.00550 0.0063 0.1599 1.0000
8.000 0.9430 0.01199 0.00584 0.0072 0.1481 1.0000
8.250 0.9652 0.01237 0.00620 0.0080 0.1362 1.0000
8.500 0.9871 0.01279 0.00661 0.0090 0.1243 1.0000
8.750 1.0089 0.01321 0.00702 0.0099 0.1139 1.0000
9.000 1.0303 0.01365 0.00745 0.0108 0.1048 1.0000
9.250 1.0510 0.01415 0.00793 0.0118 0.0949 1.0000
9.500 1.0715 0.01467 0.00843 0.0129 0.0843 1.0000
9.750 1.0915 0.01522 0.00896 0.0139 0.0740 1.0000
10.000 1.1110 0.01580 0.00954 0.0151 0.0648 1.0000
10.250 1.1293 0.01645 0.01017 0.0163 0.0551 1.0000
10.500 1.1470 0.01715 0.01084 0.0175 0.0468 1.0000
10.750 1.1633 0.01791 0.01159 0.0189 0.0385 1.0000
11.000 1.1797 0.01864 0.01232 0.0203 0.0321 1.0000
11.250 1.1943 0.01946 0.01315 0.0219 0.0263 1.0000
11.500 1.2075 0.02034 0.01403 0.0235 0.0218 1.0000
11.750 1.2203 0.02118 0.01494 0.0252 0.0185 1.0000
12.000 1.2306 0.02214 0.01593 0.0271 0.0156 1.0000
12.250 1.2377 0.02318 0.01700 0.0292 0.0130 1.0000
12.500 1.2393 0.02423 0.01811 0.0322 0.0116 1.0000
12.750 1.2401 0.02552 0.01949 0.0344 0.0102 1.0000
13.000 1.2403 0.02723 0.02128 0.0356 0.0095 1.0000
13.250 1.2396 0.02947 0.02361 0.0358 0.0088 1.0000
13.500 1.2397 0.03200 0.02625 0.0353 0.0081 1.0000
13.750 1.2382 0.03501 0.02938 0.0342 0.0076 1.0000
14.000 1.2334 0.03861 0.03308 0.0328 0.0069 1.0000
14.250 1.2255 0.04273 0.03730 0.0310 0.0064 1.0000
14.500 1.2173 0.04692 0.04161 0.0292 0.0062 1.0000
14.750 1.2088 0.05121 0.04601 0.0274 0.0060 1.0000
15.000 1.1979 0.05582 0.05074 0.0255 0.0060 1.0000
15.250 1.1868 0.06049 0.05552 0.0236 0.0057 1.0000
15.500 1.1736 0.06550 0.06063 0.0215 0.0056 1.0000
15.750 1.1617 0.07040 0.06563 0.0194 0.0054 1.0000
16.000 1.1471 0.07591 0.07124 0.0170 0.0051 1.0000
16.250 1.1344 0.08130 0.07675 0.0146 0.0050 1.0000
16.500 1.1234 0.08652 0.08206 0.0123 0.0050 1.0000
16.750 1.1100 0.09224 0.08788 0.0097 0.0048 1.0000
17.000 1.1009 0.09738 0.09312 0.0074 0.0049 1.0000
17.250 1.0871 0.10340 0.09923 0.0046 0.0047 1.0000
17.500 1.0745 0.10934 0.10525 0.0018 0.0045 1.0000
17.750 1.0636 0.11511 0.11111 -0.0010 0.0044 1.0000
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Polar data table (+)
Polar graphs
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