MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 500,000 Max Cl/Cd: 86.94 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh43-il-500000.txt Download as CSV file: xf-mh43-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 43 8.5%
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 -0.5251 0.08505 0.08298 -0.0057 1.0000 0.0150
-8.250 -0.5260 0.08085 0.07881 -0.0082 1.0000 0.0152
-8.000 -0.5292 0.07646 0.07446 -0.0111 1.0000 0.0153
-5.250 -0.3972 0.02007 0.01521 -0.0357 0.9595 0.0127
-5.000 -0.3711 0.01693 0.01173 -0.0352 0.9391 0.0100
-4.750 -0.3484 0.01477 0.00922 -0.0336 0.9193 0.0091
-4.500 -0.3257 0.01323 0.00738 -0.0320 0.9026 0.0086
-4.250 -0.3023 0.01209 0.00603 -0.0307 0.8878 0.0083
-4.000 -0.2780 0.01123 0.00499 -0.0297 0.8743 0.0083
-3.750 -0.2528 0.01057 0.00417 -0.0289 0.8617 0.0087
-3.500 -0.2267 0.01007 0.00351 -0.0282 0.8498 0.0097
-3.250 -0.2007 0.00932 0.00274 -0.0275 0.8386 0.0368
-3.000 -0.1756 0.00868 0.00243 -0.0272 0.8279 0.1233
-2.750 -0.1502 0.00819 0.00225 -0.0269 0.8179 0.2095
-2.500 -0.1244 0.00775 0.00206 -0.0266 0.8075 0.2953
-2.250 -0.0982 0.00739 0.00192 -0.0264 0.7973 0.3724
-2.000 -0.0726 0.00699 0.00181 -0.0261 0.7877 0.4708
-1.750 -0.0482 0.00655 0.00173 -0.0254 0.7785 0.5911
-1.500 -0.0233 0.00622 0.00168 -0.0246 0.7684 0.6843
-1.250 0.0011 0.00597 0.00164 -0.0236 0.7589 0.7656
-1.000 0.0253 0.00580 0.00161 -0.0225 0.7498 0.8310
-0.750 0.0501 0.00568 0.00160 -0.0213 0.7401 0.8864
-0.500 0.0801 0.00564 0.00158 -0.0213 0.7303 0.9322
-0.250 0.1192 0.00566 0.00152 -0.0235 0.7205 0.9627
0.000 0.1596 0.00570 0.00147 -0.0260 0.7104 0.9816
0.250 0.2019 0.00572 0.00142 -0.0291 0.6993 0.9939
0.500 0.2379 0.00574 0.00138 -0.0309 0.6883 1.0000
0.750 0.2630 0.00578 0.00136 -0.0304 0.6777 1.0000
1.000 0.2884 0.00584 0.00135 -0.0298 0.6671 1.0000
1.250 0.3139 0.00590 0.00134 -0.0293 0.6561 1.0000
1.500 0.3397 0.00596 0.00135 -0.0289 0.6443 1.0000
1.750 0.3657 0.00602 0.00139 -0.0285 0.6322 1.0000
2.000 0.3918 0.00609 0.00142 -0.0281 0.6195 1.0000
2.250 0.4181 0.00617 0.00145 -0.0277 0.6063 1.0000
2.500 0.4444 0.00626 0.00150 -0.0273 0.5922 1.0000
2.750 0.4708 0.00636 0.00158 -0.0270 0.5772 1.0000
3.000 0.4973 0.00647 0.00165 -0.0267 0.5612 1.0000
3.250 0.5239 0.00658 0.00174 -0.0264 0.5433 1.0000
3.500 0.5504 0.00671 0.00183 -0.0261 0.5241 1.0000
3.750 0.5769 0.00687 0.00196 -0.0259 0.5015 1.0000
4.000 0.6033 0.00705 0.00209 -0.0256 0.4771 1.0000
4.250 0.6296 0.00727 0.00224 -0.0254 0.4488 1.0000
4.500 0.6555 0.00754 0.00241 -0.0251 0.4155 1.0000
4.750 0.6812 0.00786 0.00262 -0.0248 0.3767 1.0000
5.000 0.7066 0.00825 0.00287 -0.0245 0.3353 1.0000
5.250 0.7316 0.00872 0.00320 -0.0242 0.2891 1.0000
5.500 0.7561 0.00926 0.00354 -0.0239 0.2401 1.0000
5.750 0.7802 0.00988 0.00393 -0.0236 0.1882 1.0000
6.000 0.8043 0.01050 0.00436 -0.0233 0.1453 1.0000
6.250 0.8286 0.01107 0.00480 -0.0230 0.1120 1.0000
6.500 0.8523 0.01174 0.00530 -0.0226 0.0798 1.0000
6.750 0.8757 0.01242 0.00584 -0.0222 0.0516 1.0000
7.000 0.8987 0.01316 0.00645 -0.0217 0.0310 1.0000
7.250 0.9220 0.01384 0.00716 -0.0212 0.0206 1.0000
7.500 0.9442 0.01473 0.00807 -0.0205 0.0105 1.0000
7.750 0.9614 0.01646 0.00998 -0.0189 0.0063 1.0000
8.000 0.9817 0.01753 0.01120 -0.0179 0.0058 1.0000
8.250 1.0002 0.01885 0.01267 -0.0167 0.0054 1.0000
8.500 1.0174 0.02035 0.01434 -0.0153 0.0052 1.0000
8.750 1.0336 0.02205 0.01623 -0.0138 0.0051 1.0000
9.000 1.0486 0.02409 0.01849 -0.0122 0.0051 1.0000
9.250 1.0620 0.02649 0.02115 -0.0106 0.0051 1.0000
9.500 1.0732 0.02927 0.02422 -0.0088 0.0052 1.0000
9.750 1.0799 0.03253 0.02782 -0.0068 0.0054 1.0000
10.000 1.0812 0.03603 0.03166 -0.0045 0.0056 1.0000
10.250 1.0749 0.03963 0.03559 -0.0019 0.0057 1.0000
10.500 1.0610 0.04281 0.03902 0.0013 0.0059 1.0000
10.750 1.0467 0.04612 0.04254 0.0031 0.0060 1.0000
11.000 1.0242 0.05089 0.04755 0.0035 0.0061 1.0000
11.250 1.0081 0.05532 0.05217 0.0026 0.0062 1.0000
11.500 0.9908 0.06048 0.05750 0.0005 0.0062 1.0000
11.750 0.9703 0.06684 0.06402 -0.0029 0.0063 1.0000
12.000 0.9545 0.07314 0.07047 -0.0069 0.0063 1.0000
12.250 0.9278 0.08248 0.07995 -0.0131 0.0064 1.0000
12.500 0.9155 0.08990 0.08749 -0.0184 0.0064 1.0000
12.750 0.8260 0.09365 0.09146 -0.0199 0.0061 1.0000
13.000 0.8065 0.10334 0.10125 -0.0254 0.0061 1.0000
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Polar data table (+)
Polar graphs
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