MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 50,000 Max Cl/Cd: 9.88 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh78-il-50000.txt Download as CSV file: xf-mh78-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4864 0.12459 0.11902 0.0369 1.0000 0.2647
-9.250 -0.4414 0.11762 0.11209 0.0389 1.0000 0.2737
-9.000 -0.4806 0.11786 0.11249 0.0351 1.0000 0.2842
-8.750 -0.4285 0.11061 0.10528 0.0372 1.0000 0.2929
-8.500 -0.4457 0.10843 0.10324 0.0351 1.0000 0.3052
-8.250 -0.4154 0.10349 0.09837 0.0354 1.0000 0.3128
-8.000 -0.4247 0.10063 0.09566 0.0338 1.0000 0.3259
-7.750 -0.4022 0.09630 0.09143 0.0334 1.0000 0.3329
-7.500 -0.4068 0.09314 0.08844 0.0319 1.0000 0.3463
-7.250 -0.5744 0.06691 0.06129 -0.0013 1.0000 0.1418
-7.000 -0.5503 0.06232 0.05686 -0.0024 1.0000 0.1376
-6.750 -0.5594 0.05578 0.04969 -0.0037 1.0000 0.1258
-6.500 -0.5425 0.05180 0.04569 -0.0054 1.0000 0.1232
-6.250 -0.5501 0.04985 0.04368 -0.0041 0.9994 0.1214
-6.000 -0.5004 0.04330 0.03615 -0.0114 0.9570 0.1163
-5.750 -0.4521 0.03960 0.03192 -0.0157 0.9168 0.1179
-5.500 -0.4240 0.03763 0.02953 -0.0153 0.8800 0.1221
-5.250 -0.4051 0.03609 0.02745 -0.0128 0.8483 0.1256
-5.000 -0.3857 0.03454 0.02565 -0.0101 0.8216 0.1295
-4.750 -0.3644 0.03344 0.02442 -0.0080 0.7944 0.1374
-4.500 -0.3420 0.03224 0.02310 -0.0060 0.7708 0.1477
-4.250 -0.3182 0.03110 0.02191 -0.0040 0.7489 0.1636
-4.000 -0.2930 0.03003 0.02078 -0.0022 0.7284 0.1902
-3.750 -0.2666 0.02855 0.01967 -0.0007 0.7091 0.2461
-3.500 -0.2508 0.02622 0.01862 0.0021 0.6923 0.3943
-3.250 -0.2379 0.02473 0.01881 0.0079 0.6765 0.6342
-3.000 -0.1685 0.02775 0.02189 0.0117 0.6523 0.8333
-2.750 -0.0482 0.03031 0.02356 0.0034 0.6215 0.9199
-2.500 0.0602 0.02997 0.02255 -0.0097 0.5940 0.9808
-2.250 0.1137 0.02928 0.02151 -0.0161 0.5768 1.0000
-2.000 0.1276 0.02918 0.02112 -0.0151 0.5674 1.0000
-1.750 0.1491 0.02946 0.02129 -0.0160 0.5547 1.0000
-1.500 0.1646 0.02954 0.02109 -0.0145 0.5463 1.0000
-1.250 0.1891 0.03017 0.02168 -0.0160 0.5342 1.0000
-1.000 0.2064 0.03039 0.02163 -0.0144 0.5265 1.0000
-0.750 0.2315 0.03130 0.02254 -0.0160 0.5152 1.0000
-0.500 0.2504 0.03166 0.02270 -0.0148 0.5076 1.0000
-0.250 0.2742 0.03280 0.02381 -0.0160 0.4987 1.0000
0.000 0.2958 0.03370 0.02464 -0.0162 0.4906 1.0000
0.250 0.3130 0.03407 0.02476 -0.0140 0.4851 1.0000
0.500 0.3378 0.03619 0.02703 -0.0172 0.4753 1.0000
0.750 0.3570 0.03720 0.02795 -0.0166 0.4691 1.0000
1.000 0.3746 0.03792 0.02848 -0.0148 0.4644 1.0000
1.250 0.3937 0.04123 0.03201 -0.0190 0.4564 1.0000
1.500 0.4097 0.04289 0.03363 -0.0189 0.4506 1.0000
1.750 0.4265 0.04369 0.03429 -0.0169 0.4465 1.0000
2.000 0.4369 0.04698 0.03765 -0.0188 0.4427 1.0000
2.250 0.4359 0.05155 0.04235 -0.0219 0.4397 1.0000
2.500 0.4304 0.05559 0.04643 -0.0234 0.4389 1.0000
2.750 0.4240 0.05929 0.05012 -0.0238 0.4410 1.0000
3.000 0.4234 0.06235 0.05313 -0.0233 0.4432 1.0000
3.250 0.4284 0.06510 0.05583 -0.0224 0.4453 1.0000
3.500 0.2174 0.07510 0.06603 -0.0239 0.6018 1.0000
3.750 0.2330 0.07701 0.06784 -0.0230 0.5901 1.0000
4.000 0.2326 0.07858 0.06930 -0.0211 0.5810 1.0000
4.250 0.2501 0.08069 0.07133 -0.0204 0.5697 1.0000
4.500 0.2489 0.08216 0.07269 -0.0185 0.5597 1.0000
4.750 0.2709 0.08465 0.07511 -0.0182 0.5488 1.0000
5.000 0.2667 0.08594 0.07631 -0.0164 0.5390 1.0000
5.500 0.3044 0.09180 0.08202 -0.0161 0.5242 1.0000
5.750 0.2965 0.09194 0.08209 -0.0141 0.5111 1.0000
6.000 0.3385 0.09715 0.08726 -0.0153 0.5054 1.0000
6.250 0.3121 0.09593 0.08596 -0.0127 0.4931 1.0000
6.500 0.3413 0.09966 0.08964 -0.0131 0.4867 1.0000
6.750 0.3313 0.10062 0.09054 -0.0120 0.4793 1.0000
7.000 0.3436 0.10271 0.09258 -0.0116 0.4701 1.0000
7.250 0.3841 0.10836 0.09820 -0.0125 0.4652 1.0000
7.500 0.3560 0.10692 0.09670 -0.0108 0.4546 1.0000
7.750 0.3810 0.11035 0.10011 -0.0109 0.4475 1.0000
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