MH33 (mh33-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 200,000 Max Cl/Cd: 59.5 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh33-il-200000.txt Download as CSV file: xf-mh33-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH33
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5489 0.11881 0.11517 -0.0068 1.0000 0.0277
-10.250 -0.5428 0.11405 0.11040 -0.0047 1.0000 0.0294
-7.000 -0.5460 0.06137 0.05797 -0.0309 1.0000 0.0452
-6.750 -0.5427 0.05715 0.05364 -0.0318 1.0000 0.0472
-6.000 -0.5262 0.04522 0.04117 -0.0307 1.0000 0.0562
-5.750 -0.5149 0.04242 0.03818 -0.0294 1.0000 0.0605
-5.500 -0.5065 0.03877 0.03405 -0.0279 1.0000 0.0673
-5.250 -0.4919 0.03626 0.03150 -0.0265 1.0000 0.0704
-5.000 -0.4789 0.03367 0.02852 -0.0248 1.0000 0.0804
-4.750 -0.4506 0.02499 0.01851 -0.0200 1.0000 0.0264
-4.500 -0.4316 0.02176 0.01490 -0.0183 1.0000 0.0245
-4.250 -0.4097 0.01939 0.01216 -0.0166 1.0000 0.0229
-4.000 -0.3869 0.01755 0.01005 -0.0151 1.0000 0.0221
-3.750 -0.3642 0.01601 0.00836 -0.0136 1.0000 0.0222
-3.500 -0.3422 0.01481 0.00706 -0.0122 1.0000 0.0227
-3.250 -0.3201 0.01381 0.00598 -0.0108 1.0000 0.0246
-3.000 -0.2977 0.01284 0.00487 -0.0095 1.0000 0.0300
-2.750 -0.2780 0.01068 0.00400 -0.0086 1.0000 0.2724
-2.500 -0.2608 0.00952 0.00392 -0.0071 1.0000 0.5141
-2.250 -0.2447 0.00883 0.00384 -0.0044 1.0000 0.6789
-2.000 -0.2271 0.00846 0.00406 -0.0009 1.0000 0.8628
-1.750 -0.1368 0.00862 0.00403 -0.0127 1.0000 0.9891
-1.500 -0.1025 0.00864 0.00388 -0.0145 1.0000 1.0000
-1.250 -0.0899 0.00865 0.00378 -0.0119 1.0000 1.0000
-1.000 -0.0756 0.00871 0.00371 -0.0097 1.0000 1.0000
-0.750 -0.0599 0.00879 0.00370 -0.0078 1.0000 1.0000
-0.500 -0.0388 0.00892 0.00375 -0.0070 0.9992 1.0000
-0.250 0.0109 0.00913 0.00387 -0.0119 0.9923 1.0000
0.000 0.0597 0.00926 0.00393 -0.0165 0.9845 1.0000
0.250 0.1080 0.00934 0.00397 -0.0208 0.9764 1.0000
0.500 0.1601 0.00936 0.00399 -0.0259 0.9693 1.0000
0.750 0.2070 0.00928 0.00393 -0.0298 0.9591 1.0000
1.000 0.2575 0.00914 0.00383 -0.0343 0.9501 1.0000
1.250 0.3072 0.00892 0.00366 -0.0385 0.9398 1.0000
1.500 0.3450 0.00869 0.00348 -0.0400 0.9227 1.0000
1.750 0.3803 0.00846 0.00331 -0.0410 0.9026 1.0000
2.000 0.4098 0.00828 0.00315 -0.0406 0.8756 1.0000
2.250 0.4359 0.00817 0.00303 -0.0395 0.8413 1.0000
2.500 0.4609 0.00815 0.00293 -0.0382 0.7992 1.0000
2.750 0.4839 0.00827 0.00294 -0.0365 0.7489 1.0000
3.000 0.5054 0.00850 0.00299 -0.0347 0.6928 1.0000
3.250 0.5260 0.00884 0.00309 -0.0328 0.6331 1.0000
3.500 0.5460 0.00924 0.00325 -0.0310 0.5703 1.0000
3.750 0.5658 0.00969 0.00346 -0.0292 0.5063 1.0000
4.000 0.5856 0.01020 0.00371 -0.0276 0.4415 1.0000
4.250 0.6057 0.01074 0.00406 -0.0262 0.3781 1.0000
4.500 0.6263 0.01131 0.00441 -0.0249 0.3189 1.0000
4.750 0.6471 0.01193 0.00481 -0.0237 0.2604 1.0000
5.000 0.6680 0.01261 0.00527 -0.0226 0.2061 1.0000
5.250 0.6889 0.01337 0.00582 -0.0215 0.1584 1.0000
5.500 0.7099 0.01417 0.00644 -0.0205 0.1155 1.0000
5.750 0.7302 0.01513 0.00720 -0.0194 0.0820 1.0000
6.000 0.7504 0.01623 0.00825 -0.0180 0.0591 1.0000
6.250 0.7697 0.01759 0.00970 -0.0164 0.0466 1.0000
6.500 0.7901 0.01916 0.01141 -0.0148 0.0406 1.0000
6.750 0.8097 0.02094 0.01320 -0.0136 0.0337 1.0000
7.000 0.8323 0.02220 0.01473 -0.0123 0.0282 1.0000
7.250 0.8499 0.02490 0.01761 -0.0109 0.0217 1.0000
7.500 0.8717 0.02499 0.01785 -0.0100 0.0158 1.0000
8.000 0.8976 0.03222 0.02596 -0.0059 0.0125 1.0000
8.250 0.9077 0.03572 0.02994 -0.0038 0.0124 1.0000
8.500 0.9125 0.03969 0.03440 -0.0014 0.0124 1.0000
8.750 0.9112 0.04406 0.03924 0.0011 0.0123 1.0000
9.000 0.9049 0.04845 0.04401 0.0033 0.0125 1.0000
9.250 0.8928 0.05285 0.04871 0.0054 0.0126 1.0000
9.750 0.7942 0.05263 0.04899 0.0103 0.0131 1.0000
10.000 0.7815 0.05682 0.05332 0.0090 0.0133 1.0000
10.250 0.7627 0.06265 0.05929 0.0056 0.0133 1.0000
10.500 0.7452 0.06966 0.06642 0.0009 0.0134 1.0000
10.750 0.7325 0.07710 0.07397 -0.0041 0.0136 1.0000
11.000 0.7176 0.08642 0.08337 -0.0097 0.0139 1.0000
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