MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=200,000 Ncrit=5
Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 200,000 Max Cl/Cd: 62.81 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh42-il-200000-n5.txt Download as CSV file: xf-mh42-il-200000-n5.csv |
XFOIL Version 6.96 Calculated polar for: MH 42 8.94% 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5133 0.08845 0.08506 -0.0087 1.0000 0.0078 -8.750 -0.5151 0.08374 0.08040 -0.0113 1.0000 0.0077 -8.500 -0.5174 0.07914 0.07585 -0.0141 1.0000 0.0075 -8.250 -0.5237 0.07374 0.07052 -0.0178 1.0000 0.0074 -8.000 -0.5327 0.06815 0.06499 -0.0227 1.0000 0.0073 -7.750 -0.5372 0.06106 0.05785 -0.0288 1.0000 0.0071 -7.500 -0.5401 0.05362 0.05026 -0.0331 1.0000 0.0069 -7.250 -0.5398 0.04683 0.04322 -0.0353 1.0000 0.0067 -7.000 -0.5373 0.04029 0.03628 -0.0361 1.0000 0.0064 -6.750 -0.5306 0.03454 0.03001 -0.0358 1.0000 0.0062 -6.500 -0.5194 0.02991 0.02481 -0.0347 1.0000 0.0061 -6.250 -0.5044 0.02651 0.02091 -0.0334 1.0000 0.0061 -6.000 -0.4878 0.02396 0.01793 -0.0318 1.0000 0.0061 -5.750 -0.4608 0.02161 0.01513 -0.0322 0.9908 0.0062 -5.500 -0.4281 0.01958 0.01274 -0.0334 0.9783 0.0064 -5.250 -0.3954 0.01796 0.01086 -0.0346 0.9662 0.0068 -5.000 -0.3633 0.01661 0.00930 -0.0354 0.9536 0.0075 -4.750 -0.3327 0.01555 0.00805 -0.0360 0.9400 0.0083 -4.500 -0.3040 0.01467 0.00706 -0.0363 0.9258 0.0109 -4.250 -0.2759 0.01413 0.00641 -0.0362 0.9113 0.0151 -4.000 -0.2501 0.01327 0.00538 -0.0356 0.8967 0.0228 -3.750 -0.2250 0.01257 0.00475 -0.0349 0.8824 0.0476 -3.500 -0.2008 0.01189 0.00429 -0.0343 0.8684 0.1000 -3.250 -0.1757 0.01149 0.00397 -0.0337 0.8549 0.1434 -3.000 -0.1507 0.01112 0.00370 -0.0331 0.8418 0.1941 -2.750 -0.1263 0.01068 0.00346 -0.0325 0.8290 0.2638 -2.500 -0.1018 0.01028 0.00323 -0.0318 0.8166 0.3350 -2.000 -0.0534 0.00953 0.00291 -0.0303 0.7924 0.4960 -1.750 -0.0297 0.00919 0.00280 -0.0292 0.7805 0.5810 -1.500 -0.0061 0.00891 0.00273 -0.0280 0.7690 0.6612 -1.250 0.0178 0.00869 0.00266 -0.0267 0.7578 0.7347 -1.000 0.0426 0.00854 0.00262 -0.0255 0.7469 0.8007 -0.750 0.0714 0.00846 0.00257 -0.0251 0.7361 0.8592 -0.500 0.1077 0.00844 0.00253 -0.0264 0.7246 0.9083 -0.250 0.1490 0.00845 0.00244 -0.0289 0.7131 0.9450 0.000 0.1903 0.00847 0.00237 -0.0316 0.7014 0.9719 0.250 0.2322 0.00850 0.00230 -0.0345 0.6894 0.9923 0.500 0.2644 0.00855 0.00224 -0.0355 0.6775 1.0000 0.750 0.2889 0.00862 0.00222 -0.0348 0.6658 1.0000 1.000 0.3137 0.00870 0.00221 -0.0342 0.6538 1.0000 1.250 0.3387 0.00878 0.00222 -0.0336 0.6414 1.0000 1.500 0.3638 0.00887 0.00226 -0.0330 0.6288 1.0000 1.750 0.3891 0.00897 0.00230 -0.0325 0.6160 1.0000 2.000 0.4144 0.00907 0.00235 -0.0319 0.6026 1.0000 2.250 0.4398 0.00918 0.00241 -0.0314 0.5888 1.0000 2.500 0.4653 0.00930 0.00249 -0.0309 0.5742 1.0000 2.750 0.4908 0.00944 0.00260 -0.0304 0.5590 1.0000 3.000 0.5164 0.00958 0.00271 -0.0299 0.5427 1.0000 3.250 0.5420 0.00972 0.00283 -0.0294 0.5251 1.0000 3.500 0.5675 0.00989 0.00296 -0.0289 0.5062 1.0000 3.750 0.5930 0.01008 0.00313 -0.0285 0.4861 1.0000 4.000 0.6183 0.01028 0.00330 -0.0280 0.4643 1.0000 4.250 0.6436 0.01051 0.00349 -0.0275 0.4408 1.0000 4.500 0.6686 0.01078 0.00370 -0.0270 0.4150 1.0000 4.750 0.6934 0.01108 0.00398 -0.0265 0.3869 1.0000 5.000 0.7179 0.01143 0.00426 -0.0260 0.3566 1.0000 5.250 0.7421 0.01182 0.00457 -0.0255 0.3247 1.0000 5.500 0.7660 0.01226 0.00492 -0.0250 0.2904 1.0000 5.750 0.7894 0.01277 0.00533 -0.0245 0.2561 1.0000 6.000 0.8128 0.01331 0.00578 -0.0239 0.2220 1.0000 6.250 0.8355 0.01392 0.00627 -0.0233 0.1877 1.0000 6.500 0.8580 0.01456 0.00687 -0.0228 0.1554 1.0000 6.750 0.8796 0.01531 0.00748 -0.0221 0.1234 1.0000 7.000 0.9013 0.01605 0.00812 -0.0215 0.0969 1.0000 7.250 0.9231 0.01676 0.00880 -0.0208 0.0764 1.0000 7.500 0.9441 0.01757 0.00957 -0.0201 0.0599 1.0000 7.750 0.9648 0.01838 0.01039 -0.0193 0.0456 1.0000 8.000 0.9844 0.01932 0.01133 -0.0183 0.0356 1.0000 8.250 1.0041 0.02022 0.01234 -0.0173 0.0291 1.0000 8.500 1.0219 0.02130 0.01355 -0.0162 0.0237 1.0000 8.750 1.0402 0.02227 0.01462 -0.0151 0.0192 1.0000 9.000 1.0553 0.02355 0.01599 -0.0138 0.0156 1.0000 9.250 1.0720 0.02459 0.01717 -0.0126 0.0125 1.0000 9.500 1.0824 0.02622 0.01887 -0.0109 0.0100 1.0000 9.750 1.0968 0.02736 0.02019 -0.0095 0.0087 1.0000 10.000 1.1072 0.02882 0.02182 -0.0077 0.0074 1.0000 10.250 1.1145 0.03033 0.02347 -0.0057 0.0067 1.0000 10.500 1.1175 0.03199 0.02527 -0.0033 0.0063 1.0000 10.750 1.1151 0.03424 0.02767 -0.0010 0.0059 1.0000 11.000 1.1111 0.03693 0.03053 0.0009 0.0057 1.0000 11.250 1.1115 0.03936 0.03318 0.0022 0.0055 1.0000 11.500 1.1108 0.04202 0.03605 0.0030 0.0054 1.0000 11.750 1.1077 0.04507 0.03932 0.0035 0.0053 1.0000 12.000 1.1027 0.04851 0.04304 0.0035 0.0052 1.0000 12.250 1.0957 0.05237 0.04713 0.0030 0.0051 1.0000 12.500 1.0870 0.05667 0.05165 0.0019 0.0051 1.0000 12.750 1.0759 0.06156 0.05676 0.0001 0.0050 1.0000 13.000 1.0631 0.06705 0.06246 -0.0024 0.0050 1.0000 13.250 1.0483 0.07322 0.06884 -0.0056 0.0050 1.0000 13.500 1.0355 0.07938 0.07518 -0.0091 0.0050 1.0000 13.750 1.0193 0.08664 0.08261 -0.0134 0.0050 1.0000 14.000 1.0031 0.09446 0.09059 -0.0182 0.0051 1.0000 14.250 0.9847 0.10342 0.09970 -0.0236 0.0051 1.0000 14.500 0.9681 0.11246 0.10882 -0.0291 0.0052 1.0000 14.750 0.9500 0.12238 0.11884 -0.0348 0.0053 1.0000 15.000 0.9315 0.13291 0.12946 -0.0406 0.0054 1.0000 15.250 0.9129 0.14398 0.14058 -0.0465 0.0056 1.0000 |
Polar data table (+)
Polar graphs
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