MH33 (mh33-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 500,000 Max Cl/Cd: 72.88 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh33-il-500000.txt Download as CSV file: xf-mh33-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5348 0.08196 0.07975 -0.0171 1.0000 0.0114
-8.250 -0.5383 0.07766 0.07549 -0.0195 1.0000 0.0116
-8.000 -0.5466 0.07310 0.07097 -0.0227 1.0000 0.0116
-7.750 -0.5541 0.06780 0.06568 -0.0271 1.0000 0.0116
-7.500 -0.5564 0.06229 0.06011 -0.0305 1.0000 0.0116
-7.250 -0.5569 0.05721 0.05495 -0.0323 1.0000 0.0119
-7.000 -0.5559 0.05239 0.05001 -0.0329 1.0000 0.0121
-6.750 -0.5531 0.04796 0.04542 -0.0325 1.0000 0.0124
-6.500 -0.5488 0.04384 0.04112 -0.0313 1.0000 0.0130
-6.250 -0.5427 0.03995 0.03701 -0.0295 1.0000 0.0137
-6.000 -0.5336 0.03641 0.03322 -0.0273 1.0000 0.0149
-5.750 -0.5115 0.03634 0.03287 -0.0250 1.0000 0.0169
-4.750 -0.4634 0.02282 0.01807 -0.0163 1.0000 0.0166
-4.500 -0.4445 0.02091 0.01588 -0.0146 1.0000 0.0167
-4.250 -0.4257 0.01652 0.01102 -0.0127 1.0000 0.0144
-4.000 -0.4018 0.01414 0.00832 -0.0113 0.9999 0.0122
-3.750 -0.3687 0.01240 0.00635 -0.0118 0.9980 0.0109
-3.500 -0.3339 0.01143 0.00525 -0.0131 0.9956 0.0105
-3.250 -0.2983 0.01063 0.00434 -0.0146 0.9933 0.0106
-3.000 -0.2639 0.01002 0.00360 -0.0159 0.9899 0.0113
-2.750 -0.2274 0.00956 0.00303 -0.0175 0.9865 0.0157
-2.500 -0.1935 0.00827 0.00260 -0.0195 0.9837 0.2192
-2.250 -0.1560 0.00761 0.00249 -0.0220 0.9814 0.3652
-2.000 -0.1290 0.00673 0.00240 -0.0223 0.9755 0.5714
-1.750 -0.0949 0.00622 0.00231 -0.0236 0.9717 0.6936
-1.500 -0.0597 0.00578 0.00230 -0.0248 0.9690 0.8117
-1.250 -0.0297 0.00562 0.00233 -0.0246 0.9637 0.8966
-1.000 0.0082 0.00561 0.00233 -0.0262 0.9598 0.9370
-0.750 0.0500 0.00559 0.00228 -0.0287 0.9567 0.9584
-0.500 0.0910 0.00558 0.00222 -0.0312 0.9519 0.9709
-0.250 0.1358 0.00553 0.00214 -0.0346 0.9458 0.9785
0.000 0.1812 0.00547 0.00205 -0.0381 0.9389 0.9844
0.250 0.2257 0.00538 0.00194 -0.0415 0.9283 0.9903
0.500 0.2678 0.00530 0.00183 -0.0444 0.9124 0.9962
0.750 0.3048 0.00521 0.00170 -0.0462 0.8903 1.0000
1.000 0.3273 0.00518 0.00158 -0.0448 0.8596 1.0000
1.250 0.3491 0.00522 0.00149 -0.0433 0.8215 1.0000
1.500 0.3706 0.00533 0.00144 -0.0417 0.7763 1.0000
1.750 0.3918 0.00551 0.00142 -0.0402 0.7279 1.0000
2.000 0.4129 0.00573 0.00144 -0.0387 0.6769 1.0000
2.250 0.4342 0.00598 0.00148 -0.0373 0.6256 1.0000
2.500 0.4555 0.00625 0.00156 -0.0359 0.5739 1.0000
2.750 0.4769 0.00655 0.00169 -0.0346 0.5211 1.0000
3.000 0.4984 0.00687 0.00181 -0.0334 0.4680 1.0000
3.250 0.5200 0.00723 0.00196 -0.0322 0.4134 1.0000
3.500 0.5418 0.00758 0.00212 -0.0311 0.3629 1.0000
3.750 0.5640 0.00793 0.00231 -0.0301 0.3179 1.0000
4.000 0.5861 0.00832 0.00252 -0.0291 0.2705 1.0000
4.250 0.6084 0.00871 0.00278 -0.0281 0.2287 1.0000
4.500 0.6305 0.00914 0.00304 -0.0272 0.1849 1.0000
4.750 0.6526 0.00961 0.00333 -0.0262 0.1423 1.0000
5.000 0.6753 0.01003 0.00364 -0.0254 0.1121 1.0000
5.250 0.6984 0.01047 0.00398 -0.0245 0.0871 1.0000
5.500 0.7215 0.01092 0.00437 -0.0237 0.0652 1.0000
5.750 0.7442 0.01148 0.00482 -0.0229 0.0432 1.0000
6.000 0.7670 0.01206 0.00538 -0.0221 0.0276 1.0000
6.250 0.7900 0.01263 0.00597 -0.0212 0.0201 1.0000
6.500 0.8134 0.01314 0.00650 -0.0205 0.0156 1.0000
6.750 0.8364 0.01375 0.00720 -0.0197 0.0119 1.0000
7.000 0.8558 0.01507 0.00864 -0.0181 0.0055 1.0000
7.250 0.8767 0.01609 0.00980 -0.0168 0.0046 1.0000
7.500 0.8968 0.01724 0.01110 -0.0155 0.0041 1.0000
7.750 0.9154 0.01870 0.01275 -0.0140 0.0038 1.0000
8.000 0.9326 0.02051 0.01479 -0.0123 0.0037 1.0000
8.250 0.9492 0.02252 0.01708 -0.0105 0.0037 1.0000
8.500 0.9638 0.02498 0.01988 -0.0086 0.0037 1.0000
8.750 0.9720 0.02880 0.02422 -0.0058 0.0039 1.0000
9.000 0.9665 0.03492 0.03105 -0.0019 0.0044 1.0000
9.250 0.9513 0.04128 0.03799 0.0020 0.0049 1.0000
9.500 0.9383 0.04583 0.04287 0.0048 0.0051 1.0000
9.750 0.9144 0.04997 0.04726 0.0084 0.0053 1.0000
10.000 0.8976 0.05342 0.05087 0.0097 0.0053 1.0000
10.250 0.8743 0.05860 0.05622 0.0082 0.0054 1.0000
10.500 0.8573 0.06470 0.06245 0.0034 0.0053 1.0000
10.750 0.8408 0.07412 0.07200 -0.0051 0.0052 1.0000
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Polar data table (+)
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