MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 200,000 Max Cl/Cd: 86.09 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh116-il-200000-n5.txt Download as CSV file: xf-mh116-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 116 9.84%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3294 0.09991 0.09646 -0.0406 1.0000 0.0124
-9.000 -0.3338 0.09719 0.09380 -0.0400 1.0000 0.0120
-8.750 -0.3384 0.09440 0.09107 -0.0396 0.9996 0.0116
-8.500 -0.3268 0.08910 0.08578 -0.0448 0.9954 0.0110
-8.250 -0.3188 0.08303 0.07974 -0.0505 0.9893 0.0103
-8.000 -0.3152 0.07425 0.07100 -0.0588 0.9812 0.0093
-7.750 -0.3066 0.06865 0.06540 -0.0649 0.9713 0.0091
-7.500 -0.2957 0.06178 0.05854 -0.0742 0.9604 0.0089
-7.250 -0.2801 0.05141 0.04808 -0.0890 0.9502 0.0087
-7.000 -0.2644 0.03703 0.03309 -0.1044 0.9405 0.0083
-6.750 -0.2455 0.03038 0.02574 -0.1094 0.9319 0.0082
-6.500 -0.2213 0.02596 0.02063 -0.1118 0.9256 0.0081
-6.250 -0.1951 0.02306 0.01720 -0.1129 0.9193 0.0082
-6.000 -0.1643 0.02072 0.01439 -0.1144 0.9153 0.0083
-5.750 -0.1390 0.01912 0.01246 -0.1143 0.9079 0.0085
-5.500 -0.1088 0.01772 0.01076 -0.1150 0.9030 0.0089
-5.250 -0.0813 0.01654 0.00938 -0.1152 0.8966 0.0093
-5.000 -0.0526 0.01554 0.00820 -0.1157 0.8907 0.0103
-4.750 -0.0231 0.01479 0.00730 -0.1161 0.8851 0.0123
-4.500 0.0045 0.01413 0.00655 -0.1161 0.8783 0.0169
-4.250 0.0346 0.01338 0.00577 -0.1166 0.8732 0.0322
-4.000 0.0609 0.01288 0.00537 -0.1166 0.8656 0.0604
-3.750 0.0906 0.01248 0.00496 -0.1170 0.8603 0.0852
-3.500 0.1174 0.01219 0.00467 -0.1168 0.8528 0.1092
-3.250 0.1463 0.01189 0.00439 -0.1171 0.8471 0.1371
-3.000 0.1733 0.01164 0.00418 -0.1170 0.8399 0.1691
-2.750 0.2017 0.01141 0.00395 -0.1171 0.8338 0.2022
-2.500 0.2289 0.01120 0.00380 -0.1171 0.8269 0.2382
-2.250 0.2568 0.01101 0.00364 -0.1171 0.8205 0.2763
-2.000 0.2842 0.01082 0.00353 -0.1171 0.8139 0.3199
-1.750 0.3115 0.01062 0.00343 -0.1170 0.8072 0.3702
-1.500 0.3386 0.01044 0.00336 -0.1169 0.8006 0.4260
-1.250 0.3654 0.01025 0.00332 -0.1167 0.7937 0.4885
-1.000 0.3918 0.01006 0.00331 -0.1163 0.7872 0.5574
-0.750 0.4171 0.00987 0.00330 -0.1157 0.7801 0.6315
-0.500 0.4414 0.00969 0.00332 -0.1146 0.7735 0.7097
-0.250 0.4636 0.00952 0.00334 -0.1130 0.7661 0.7904
0.000 0.4866 0.00938 0.00331 -0.1114 0.7593 0.8762
0.250 0.5258 0.00925 0.00319 -0.1135 0.7520 0.9928
0.500 0.5532 0.00933 0.00318 -0.1134 0.7442 1.0000
0.750 0.5806 0.00940 0.00316 -0.1133 0.7363 1.0000
1.000 0.6073 0.00949 0.00320 -0.1131 0.7275 1.0000
1.250 0.6346 0.00958 0.00320 -0.1129 0.7195 1.0000
1.500 0.6613 0.00967 0.00325 -0.1127 0.7103 1.0000
1.750 0.6880 0.00977 0.00330 -0.1124 0.7012 1.0000
2.000 0.7150 0.00988 0.00336 -0.1122 0.6925 1.0000
2.250 0.7414 0.00999 0.00344 -0.1119 0.6823 1.0000
2.500 0.7678 0.01010 0.00353 -0.1116 0.6721 1.0000
2.750 0.7942 0.01022 0.00362 -0.1113 0.6619 1.0000
3.000 0.8205 0.01035 0.00374 -0.1109 0.6510 1.0000
3.250 0.8463 0.01048 0.00386 -0.1105 0.6390 1.0000
3.500 0.8720 0.01063 0.00400 -0.1101 0.6261 1.0000
3.750 0.8974 0.01078 0.00414 -0.1095 0.6123 1.0000
4.000 0.9225 0.01095 0.00431 -0.1090 0.5973 1.0000
4.250 0.9472 0.01114 0.00448 -0.1083 0.5808 1.0000
4.500 0.9715 0.01134 0.00468 -0.1076 0.5620 1.0000
4.750 0.9953 0.01157 0.00488 -0.1068 0.5417 1.0000
5.000 1.0185 0.01183 0.00513 -0.1059 0.5188 1.0000
5.250 1.0408 0.01214 0.00539 -0.1049 0.4929 1.0000
5.500 1.0622 0.01251 0.00568 -0.1037 0.4636 1.0000
5.750 1.0822 0.01296 0.00602 -0.1023 0.4306 1.0000
6.000 1.1009 0.01348 0.00641 -0.1008 0.3947 1.0000
6.250 1.1187 0.01408 0.00690 -0.0991 0.3598 1.0000
6.500 1.1361 0.01470 0.00741 -0.0974 0.3251 1.0000
6.750 1.1529 0.01537 0.00797 -0.0957 0.2921 1.0000
7.000 1.1691 0.01608 0.00856 -0.0939 0.2597 1.0000
7.250 1.1849 0.01681 0.00919 -0.0921 0.2290 1.0000
7.500 1.2001 0.01757 0.00986 -0.0902 0.2007 1.0000
7.750 1.2146 0.01836 0.01056 -0.0883 0.1745 1.0000
8.000 1.2267 0.01920 0.01134 -0.0860 0.1485 1.0000
8.250 1.2378 0.02010 0.01213 -0.0835 0.1251 1.0000
8.500 1.2497 0.02097 0.01294 -0.0813 0.1049 1.0000
8.750 1.2611 0.02189 0.01382 -0.0790 0.0885 1.0000
9.000 1.2722 0.02285 0.01476 -0.0768 0.0733 1.0000
9.250 1.2831 0.02385 0.01576 -0.0746 0.0601 1.0000
9.500 1.2926 0.02497 0.01686 -0.0724 0.0468 1.0000
9.750 1.3003 0.02627 0.01810 -0.0702 0.0336 1.0000
10.000 1.3071 0.02767 0.01947 -0.0679 0.0237 1.0000
10.250 1.3136 0.02915 0.02098 -0.0657 0.0171 1.0000
10.500 1.3186 0.03082 0.02272 -0.0635 0.0126 1.0000
10.750 1.3235 0.03254 0.02452 -0.0615 0.0098 1.0000
11.000 1.3285 0.03431 0.02641 -0.0596 0.0075 1.0000
11.250 1.3341 0.03606 0.02829 -0.0580 0.0065 1.0000
11.500 1.3345 0.03838 0.03073 -0.0561 0.0056 1.0000
11.750 1.3372 0.04055 0.03307 -0.0546 0.0052 1.0000
12.000 1.3385 0.04292 0.03563 -0.0532 0.0047 1.0000
12.250 1.3393 0.04543 0.03831 -0.0521 0.0045 1.0000
12.500 1.3388 0.04818 0.04123 -0.0511 0.0042 1.0000
12.750 1.3378 0.05107 0.04429 -0.0503 0.0040 1.0000
13.000 1.3358 0.05418 0.04757 -0.0497 0.0038 1.0000
13.250 1.3328 0.05752 0.05107 -0.0494 0.0037 1.0000
13.500 1.3288 0.06115 0.05486 -0.0494 0.0036 1.0000
13.750 1.3231 0.06517 0.05905 -0.0497 0.0035 1.0000
14.000 1.3170 0.06940 0.06345 -0.0502 0.0034 1.0000
14.250 1.3090 0.07412 0.06839 -0.0512 0.0033 1.0000
14.500 1.3015 0.07897 0.07342 -0.0524 0.0033 1.0000
14.750 1.2915 0.08441 0.07905 -0.0540 0.0033 1.0000
15.000 1.2822 0.09000 0.08482 -0.0560 0.0032 1.0000
15.250 1.2716 0.09605 0.09106 -0.0583 0.0032 1.0000
15.500 1.2621 0.10212 0.09731 -0.0610 0.0032 1.0000
15.750 1.2519 0.10857 0.10395 -0.0640 0.0032 1.0000
16.000 1.2413 0.11536 0.11093 -0.0675 0.0032 1.0000
16.250 1.2304 0.12245 0.11820 -0.0713 0.0032 1.0000
16.500 1.2192 0.12986 0.12579 -0.0756 0.0032 1.0000
16.750 1.2079 0.13750 0.13359 -0.0800 0.0032 1.0000
17.000 1.1967 0.14544 0.14170 -0.0849 0.0032 1.0000
17.250 1.1854 0.15366 0.15007 -0.0900 0.0032 1.0000
17.500 1.1754 0.16183 0.15839 -0.0951 0.0032 1.0000
17.750 1.1653 0.17044 0.16713 -0.1005 0.0033 1.0000
18.000 1.1546 0.17966 0.17649 -0.1062 0.0033 1.0000
18.250 1.1388 0.19139 0.18833 -0.1132 0.0034 1.0000
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Polar data table (+)
Polar graphs
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