MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 500,000 Max Cl/Cd: 80.61 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh44-il-500000.txt Download as CSV file: xf-mh44-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5522 0.08476 0.08267 -0.0085 1.0000 0.0150
-9.000 -0.5554 0.07996 0.07790 -0.0113 1.0000 0.0153
-8.750 -0.5646 0.07341 0.07139 -0.0160 1.0000 0.0151
-8.500 -0.5911 0.06167 0.05962 -0.0272 1.0000 0.0149
-8.250 -0.6104 0.05470 0.05246 -0.0296 1.0000 0.0147
-8.000 -0.6122 0.05095 0.04858 -0.0301 1.0000 0.0150
-7.750 -0.6098 0.04737 0.04485 -0.0303 1.0000 0.0154
-7.500 -0.6041 0.04381 0.04110 -0.0302 1.0000 0.0160
-7.250 -0.5958 0.04020 0.03727 -0.0298 1.0000 0.0166
-7.000 -0.5846 0.03675 0.03350 -0.0289 1.0000 0.0179
-6.750 -0.5620 0.03729 0.03363 -0.0274 1.0000 0.0197
-6.500 -0.5582 0.02908 0.02492 -0.0274 0.9896 0.0212
-6.250 -0.5308 0.02211 0.01724 -0.0268 0.9794 0.0119
-6.000 -0.5014 0.01919 0.01392 -0.0272 0.9702 0.0112
-5.750 -0.4734 0.01823 0.01276 -0.0272 0.9593 0.0123
-5.500 -0.4496 0.01680 0.01112 -0.0262 0.9481 0.0123
-5.250 -0.4280 0.01520 0.00933 -0.0246 0.9374 0.0117
-5.000 -0.4072 0.01401 0.00798 -0.0227 0.9276 0.0114
-4.750 -0.3856 0.01308 0.00692 -0.0212 0.9176 0.0114
-4.500 -0.3635 0.01231 0.00605 -0.0197 0.9086 0.0115
-4.000 -0.3171 0.01113 0.00464 -0.0173 0.8911 0.0126
-3.750 -0.2931 0.01059 0.00398 -0.0161 0.8829 0.0143
-3.500 -0.2712 0.00959 0.00316 -0.0147 0.8743 0.0665
-3.250 -0.2487 0.00886 0.00285 -0.0138 0.8655 0.1694
-3.000 -0.2253 0.00838 0.00267 -0.0130 0.8575 0.2521
-2.750 -0.2008 0.00798 0.00251 -0.0123 0.8481 0.3220
-2.500 -0.1755 0.00774 0.00236 -0.0117 0.8393 0.3680
-2.250 -0.1509 0.00744 0.00223 -0.0109 0.8305 0.4284
-2.000 -0.1267 0.00710 0.00213 -0.0101 0.8205 0.5018
-1.750 -0.1024 0.00682 0.00202 -0.0092 0.8109 0.5657
-1.500 -0.0785 0.00656 0.00191 -0.0082 0.8012 0.6277
-1.250 -0.0550 0.00627 0.00184 -0.0070 0.7898 0.6960
-1.000 -0.0320 0.00596 0.00177 -0.0057 0.7781 0.7728
-0.750 -0.0047 0.00567 0.00173 -0.0050 0.7661 0.8608
-0.500 0.0522 0.00561 0.00174 -0.0109 0.7530 0.9298
-0.250 0.1039 0.00569 0.00173 -0.0158 0.7380 0.9548
0.000 0.1424 0.00581 0.00176 -0.0178 0.7218 0.9717
0.250 0.1816 0.00594 0.00177 -0.0201 0.7040 0.9839
0.500 0.2239 0.00604 0.00176 -0.0231 0.6844 0.9924
0.750 0.2678 0.00611 0.00172 -0.0266 0.6634 0.9989
1.000 0.2969 0.00618 0.00167 -0.0269 0.6436 1.0000
1.250 0.3217 0.00624 0.00165 -0.0263 0.6238 1.0000
1.500 0.3466 0.00633 0.00164 -0.0256 0.6040 1.0000
1.750 0.3718 0.00641 0.00164 -0.0251 0.5835 1.0000
2.000 0.3971 0.00651 0.00166 -0.0245 0.5636 1.0000
2.250 0.4224 0.00663 0.00170 -0.0240 0.5434 1.0000
2.500 0.4477 0.00676 0.00175 -0.0235 0.5225 1.0000
2.750 0.4731 0.00690 0.00181 -0.0230 0.5022 1.0000
3.000 0.4985 0.00705 0.00188 -0.0225 0.4820 1.0000
3.500 0.5493 0.00738 0.00209 -0.0216 0.4406 1.0000
3.750 0.5746 0.00757 0.00220 -0.0211 0.4201 1.0000
4.000 0.5999 0.00775 0.00233 -0.0206 0.3988 1.0000
4.500 0.6502 0.00819 0.00264 -0.0197 0.3541 1.0000
4.750 0.6752 0.00844 0.00282 -0.0192 0.3320 1.0000
5.000 0.7000 0.00872 0.00302 -0.0187 0.3079 1.0000
5.250 0.7247 0.00899 0.00325 -0.0182 0.2841 1.0000
5.500 0.7492 0.00931 0.00348 -0.0177 0.2598 1.0000
5.750 0.7734 0.00967 0.00374 -0.0172 0.2363 1.0000
6.000 0.7977 0.01000 0.00402 -0.0166 0.2141 1.0000
6.250 0.8216 0.01039 0.00434 -0.0160 0.1916 1.0000
6.500 0.8453 0.01079 0.00467 -0.0154 0.1701 1.0000
6.750 0.8688 0.01120 0.00502 -0.0148 0.1508 1.0000
7.000 0.8922 0.01162 0.00539 -0.0142 0.1320 1.0000
7.250 0.9149 0.01212 0.00580 -0.0135 0.1128 1.0000
7.500 0.9378 0.01258 0.00622 -0.0128 0.0969 1.0000
7.750 0.9603 0.01307 0.00670 -0.0121 0.0830 1.0000
8.000 0.9825 0.01359 0.00720 -0.0113 0.0703 1.0000
8.250 1.0041 0.01416 0.00774 -0.0104 0.0588 1.0000
8.500 1.0251 0.01478 0.00835 -0.0095 0.0486 1.0000
8.750 1.0445 0.01557 0.00911 -0.0084 0.0395 1.0000
9.000 1.0655 0.01614 0.00973 -0.0074 0.0339 1.0000
9.250 1.0833 0.01706 0.01071 -0.0060 0.0285 1.0000
9.500 1.1036 0.01762 0.01130 -0.0051 0.0246 1.0000
9.750 1.1162 0.01895 0.01270 -0.0031 0.0213 1.0000
10.000 1.1388 0.01921 0.01302 -0.0025 0.0190 1.0000
10.250 1.1570 0.01987 0.01371 -0.0013 0.0168 1.0000
10.500 1.1691 0.02103 0.01494 0.0005 0.0146 1.0000
10.750 1.1888 0.02148 0.01546 0.0015 0.0131 1.0000
11.000 1.2050 0.02218 0.01621 0.0028 0.0117 1.0000
11.250 1.2126 0.02348 0.01759 0.0050 0.0104 1.0000
11.500 1.2223 0.02440 0.01864 0.0072 0.0092 1.0000
11.750 1.2281 0.02543 0.01978 0.0098 0.0084 1.0000
12.000 1.2342 0.02659 0.02098 0.0118 0.0071 1.0000
12.250 1.2328 0.02847 0.02300 0.0140 0.0057 1.0000
12.500 1.2394 0.02988 0.02451 0.0151 0.0050 1.0000
12.750 1.2401 0.03193 0.02665 0.0162 0.0045 1.0000
13.000 1.2349 0.03471 0.02957 0.0170 0.0043 1.0000
13.250 1.2215 0.03868 0.03372 0.0170 0.0040 1.0000
13.500 1.2198 0.04168 0.03687 0.0166 0.0039 1.0000
13.750 1.2180 0.04492 0.04027 0.0158 0.0034 1.0000
14.000 1.2054 0.04971 0.04521 0.0141 0.0038 1.0000
14.250 1.1990 0.05398 0.04963 0.0124 0.0037 1.0000
14.500 1.1907 0.05874 0.05455 0.0102 0.0034 1.0000
14.750 1.1771 0.06445 0.06041 0.0075 0.0033 1.0000
15.000 1.1647 0.07016 0.06626 0.0047 0.0032 1.0000
15.250 1.1483 0.07655 0.07279 0.0017 0.0036 1.0000
15.500 1.1347 0.08296 0.07933 -0.0015 0.0033 1.0000
15.750 1.1178 0.08994 0.08645 -0.0049 0.0033 1.0000
16.000 1.1011 0.09714 0.09377 -0.0085 0.0033 1.0000
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Polar data table (+)
Polar graphs
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