MH 81 13% (mh81-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 500,000 Max Cl/Cd: 85.12 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh81-il-500000.txt Download as CSV file: xf-mh81-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3697 0.11032 0.10791 0.0220 0.7427 0.0197
-9.750 -0.3832 0.10189 0.09948 0.0165 0.7400 0.0207
-9.500 -0.3916 0.09475 0.09233 0.0125 0.7323 0.0208
-9.250 -0.3847 0.09170 0.08921 0.0125 0.7148 0.0210
-9.000 -0.3769 0.08914 0.08660 0.0123 0.6982 0.0212
-8.750 -0.3732 0.08540 0.08281 0.0110 0.6849 0.0215
-8.500 -0.3698 0.08186 0.07922 0.0098 0.6725 0.0219
-8.250 -0.3705 0.07732 0.07465 0.0078 0.6616 0.0223
-8.000 -0.3742 0.07232 0.06964 0.0055 0.6530 0.0227
-7.750 -0.3817 0.06676 0.06407 0.0024 0.6446 0.0230
-7.500 -0.3966 0.06062 0.05792 -0.0019 0.6387 0.0232
-7.250 -0.4735 0.05892 0.05599 -0.0123 0.6628 0.0218
-7.000 -0.4681 0.05491 0.05182 -0.0136 0.6508 0.0224
-6.750 -0.4868 0.04259 0.03863 -0.0154 0.6478 0.0248
-6.500 -0.4678 0.04065 0.03669 -0.0152 0.6340 0.0251
-6.250 -0.4493 0.03888 0.03482 -0.0150 0.6209 0.0255
-6.000 -0.4309 0.03677 0.03254 -0.0147 0.6082 0.0262
-5.750 -0.4191 0.03222 0.02720 -0.0133 0.5993 0.0292
-5.500 -0.3967 0.03031 0.02523 -0.0130 0.5869 0.0297
-5.250 -0.3803 0.02197 0.01573 -0.0099 0.5799 0.0181
-5.000 -0.3547 0.01907 0.01215 -0.0083 0.5693 0.0143
-4.750 -0.3288 0.01752 0.01047 -0.0077 0.5579 0.0141
-4.500 -0.3023 0.01640 0.00918 -0.0072 0.5468 0.0139
-4.250 -0.2756 0.01547 0.00809 -0.0066 0.5355 0.0139
-4.000 -0.2487 0.01469 0.00721 -0.0061 0.5246 0.0139
-3.750 -0.2217 0.01407 0.00646 -0.0056 0.5146 0.0142
-3.500 -0.1946 0.01351 0.00582 -0.0052 0.5041 0.0144
-3.250 -0.1683 0.01282 0.00510 -0.0047 0.4943 0.0151
-3.000 -0.1409 0.01244 0.00466 -0.0043 0.4839 0.0161
-2.750 -0.1132 0.01207 0.00422 -0.0040 0.4743 0.0176
-2.500 -0.0858 0.01175 0.00384 -0.0037 0.4651 0.0200
-2.250 -0.0579 0.01141 0.00347 -0.0034 0.4561 0.0247
-2.000 -0.0312 0.01088 0.00306 -0.0030 0.4474 0.0565
-1.750 -0.0046 0.01033 0.00287 -0.0028 0.4386 0.1414
-1.500 0.0225 0.01004 0.00275 -0.0026 0.4299 0.2063
-1.250 0.0492 0.00960 0.00265 -0.0024 0.4215 0.3017
-1.000 0.0738 0.00901 0.00256 -0.0020 0.4138 0.4616
-0.750 0.0959 0.00822 0.00250 -0.0008 0.4067 0.6628
-0.500 0.1149 0.00774 0.00263 0.0018 0.3997 0.8462
-0.250 0.1387 0.00778 0.00275 0.0036 0.3927 0.9139
0.000 0.1659 0.00788 0.00278 0.0044 0.3850 0.9403
0.250 0.1969 0.00801 0.00282 0.0043 0.3778 0.9577
0.500 0.2338 0.00813 0.00285 0.0029 0.3703 0.9685
0.750 0.2755 0.00830 0.00288 0.0003 0.3630 0.9753
1.000 0.3173 0.00839 0.00290 -0.0023 0.3558 0.9815
1.250 0.3604 0.00854 0.00291 -0.0053 0.3485 0.9861
1.500 0.4064 0.00862 0.00293 -0.0088 0.3419 0.9921
1.750 0.4585 0.00871 0.00290 -0.0136 0.3350 0.9986
2.000 0.4897 0.00883 0.00294 -0.0143 0.3297 1.0000
2.250 0.5146 0.00888 0.00297 -0.0137 0.3250 1.0000
2.500 0.5394 0.00898 0.00301 -0.0131 0.3201 1.0000
2.750 0.5638 0.00917 0.00310 -0.0125 0.3153 1.0000
3.000 0.5888 0.00924 0.00318 -0.0119 0.3117 1.0000
3.250 0.6136 0.00934 0.00326 -0.0113 0.3077 1.0000
3.500 0.6382 0.00948 0.00335 -0.0106 0.3036 1.0000
3.750 0.6624 0.00971 0.00350 -0.0100 0.2992 1.0000
4.000 0.6873 0.00980 0.00361 -0.0094 0.2959 1.0000
4.250 0.7121 0.00992 0.00373 -0.0087 0.2924 1.0000
4.500 0.7368 0.01009 0.00386 -0.0081 0.2890 1.0000
4.750 0.7612 0.01032 0.00403 -0.0075 0.2852 1.0000
5.000 0.7860 0.01050 0.00421 -0.0069 0.2820 1.0000
5.250 0.8113 0.01063 0.00436 -0.0064 0.2787 1.0000
5.500 0.8365 0.01080 0.00452 -0.0059 0.2756 1.0000
5.750 0.8616 0.01100 0.00470 -0.0054 0.2725 1.0000
6.000 0.8861 0.01131 0.00495 -0.0049 0.2689 1.0000
6.250 0.9118 0.01147 0.00515 -0.0045 0.2662 1.0000
6.500 0.9377 0.01163 0.00535 -0.0042 0.2631 1.0000
6.750 0.9635 0.01182 0.00555 -0.0039 0.2602 1.0000
7.000 0.9892 0.01205 0.00577 -0.0036 0.2573 1.0000
7.250 1.0144 0.01240 0.00607 -0.0033 0.2539 1.0000
7.500 1.0405 0.01261 0.00632 -0.0031 0.2512 1.0000
7.750 1.0667 0.01279 0.00656 -0.0029 0.2484 1.0000
8.000 1.0928 0.01301 0.00681 -0.0027 0.2456 1.0000
8.250 1.1186 0.01326 0.00707 -0.0025 0.2428 1.0000
8.500 1.1437 0.01362 0.00740 -0.0023 0.2395 1.0000
8.750 1.1692 0.01391 0.00774 -0.0021 0.2367 1.0000
9.000 1.1952 0.01413 0.00803 -0.0020 0.2341 1.0000
9.250 1.2208 0.01437 0.00832 -0.0019 0.2312 1.0000
9.500 1.2461 0.01464 0.00861 -0.0017 0.2282 1.0000
9.750 1.2703 0.01506 0.00900 -0.0014 0.2249 1.0000
10.000 1.2951 0.01538 0.00939 -0.0012 0.2222 1.0000
10.250 1.3201 0.01563 0.00973 -0.0011 0.2193 1.0000
10.500 1.3447 0.01591 0.01006 -0.0009 0.2162 1.0000
10.750 1.3685 0.01624 0.01042 -0.0006 0.2130 1.0000
11.000 1.3907 0.01678 0.01093 -0.0002 0.2095 1.0000
11.250 1.4147 0.01704 0.01132 0.0000 0.2069 1.0000
11.500 1.4380 0.01735 0.01172 0.0003 0.2036 1.0000
11.750 1.4603 0.01771 0.01213 0.0007 0.2003 1.0000
12.000 1.4806 0.01824 0.01265 0.0012 0.1969 1.0000
12.250 1.5016 0.01868 0.01318 0.0017 0.1939 1.0000
12.500 1.5223 0.01907 0.01369 0.0022 0.1906 1.0000
12.750 1.5412 0.01954 0.01421 0.0029 0.1870 1.0000
13.000 1.5566 0.02022 0.01488 0.0038 0.1835 1.0000
13.250 1.5715 0.02080 0.01558 0.0049 0.1805 1.0000
13.500 1.5828 0.02142 0.01631 0.0064 0.1773 1.0000
13.750 1.5911 0.02228 0.01723 0.0078 0.1741 1.0000
14.000 1.5963 0.02351 0.01847 0.0090 0.1708 1.0000
14.250 1.6043 0.02473 0.01980 0.0096 0.1676 1.0000
14.500 1.6130 0.02602 0.02120 0.0099 0.1638 1.0000
14.750 1.6170 0.02779 0.02301 0.0101 0.1600 1.0000
15.000 1.6182 0.02993 0.02520 0.0101 0.1560 1.0000
15.250 1.6236 0.03183 0.02723 0.0099 0.1520 1.0000
15.500 1.6224 0.03442 0.02987 0.0095 0.1478 1.0000
15.750 1.6170 0.03750 0.03299 0.0089 0.1441 1.0000
16.000 1.6171 0.04015 0.03577 0.0083 0.1401 1.0000
16.250 1.6086 0.04375 0.03943 0.0073 0.1360 1.0000
16.500 1.5960 0.04787 0.04359 0.0061 0.1326 1.0000
16.750 1.5904 0.05134 0.04719 0.0051 0.1290 1.0000
17.000 1.5777 0.05574 0.05166 0.0036 0.1253 1.0000
17.250 1.5589 0.06108 0.05702 0.0015 0.1216 1.0000
17.500 1.5498 0.06541 0.06148 -0.0002 0.1181 1.0000
17.750 1.5352 0.07055 0.06670 -0.0023 0.1144 1.0000
18.000 1.5167 0.07634 0.07252 -0.0048 0.1111 1.0000
18.250 1.5035 0.08156 0.07784 -0.0070 0.1075 1.0000
18.500 1.4876 0.08730 0.08365 -0.0097 0.1036 1.0000
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