MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.58 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh43-il-1000000-n5.txt Download as CSV file: xf-mh43-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4579 0.07338 0.07201 -0.0051 1.0000 0.0060
-7.000 -0.5729 0.03011 0.02728 -0.0314 0.8582 0.0029
-6.750 -0.5622 0.02499 0.02157 -0.0305 0.8429 0.0028
-6.500 -0.5453 0.02130 0.01739 -0.0296 0.8302 0.0027
-6.250 -0.5246 0.01869 0.01435 -0.0288 0.8185 0.0026
-6.000 -0.5019 0.01657 0.01188 -0.0280 0.8075 0.0026
-5.750 -0.4778 0.01490 0.00991 -0.0274 0.7970 0.0025
-5.500 -0.4529 0.01360 0.00836 -0.0268 0.7873 0.0025
-5.250 -0.4276 0.01251 0.00706 -0.0263 0.7775 0.0024
-5.000 -0.4018 0.01161 0.00600 -0.0258 0.7678 0.0024
-4.750 -0.3756 0.01087 0.00509 -0.0254 0.7584 0.0024
-4.500 -0.3491 0.01027 0.00436 -0.0251 0.7493 0.0024
-4.250 -0.3222 0.00977 0.00371 -0.0248 0.7401 0.0024
-4.000 -0.2950 0.00937 0.00320 -0.0246 0.7313 0.0024
-3.750 -0.2676 0.00903 0.00276 -0.0244 0.7227 0.0025
-3.500 -0.2400 0.00877 0.00240 -0.0242 0.7136 0.0026
-3.250 -0.2123 0.00855 0.00209 -0.0241 0.7051 0.0027
-3.000 -0.1845 0.00838 0.00185 -0.0240 0.6964 0.0030
-2.750 -0.1568 0.00814 0.00161 -0.0239 0.6874 0.0098
-2.500 -0.1293 0.00790 0.00140 -0.0238 0.6789 0.0297
-2.250 -0.1020 0.00763 0.00124 -0.0238 0.6701 0.0648
-2.000 -0.0748 0.00731 0.00110 -0.0238 0.6611 0.1209
-1.750 -0.0477 0.00700 0.00099 -0.0237 0.6523 0.1850
-1.500 -0.0200 0.00684 0.00091 -0.0237 0.6428 0.2219
-1.250 0.0073 0.00660 0.00083 -0.0237 0.6329 0.2838
-1.000 0.0348 0.00642 0.00077 -0.0237 0.6230 0.3323
-0.750 0.0623 0.00625 0.00072 -0.0237 0.6125 0.3854
-0.500 0.0898 0.00611 0.00068 -0.0237 0.6014 0.4360
-0.250 0.1173 0.00598 0.00065 -0.0236 0.5901 0.4858
0.000 0.1447 0.00584 0.00063 -0.0236 0.5790 0.5383
0.250 0.1721 0.00572 0.00063 -0.0235 0.5675 0.5900
0.500 0.1992 0.00561 0.00064 -0.0234 0.5555 0.6443
0.750 0.2263 0.00551 0.00066 -0.0232 0.5427 0.6964
1.000 0.2530 0.00543 0.00069 -0.0229 0.5289 0.7466
1.250 0.2793 0.00534 0.00072 -0.0225 0.5145 0.7995
1.500 0.3048 0.00527 0.00077 -0.0219 0.4991 0.8523
1.750 0.3297 0.00522 0.00084 -0.0211 0.4825 0.9037
2.000 0.3597 0.00525 0.00089 -0.0214 0.4635 0.9532
2.250 0.3995 0.00538 0.00095 -0.0240 0.4389 0.9819
2.500 0.4357 0.00555 0.00102 -0.0260 0.4134 0.9959
2.750 0.4660 0.00573 0.00112 -0.0266 0.3860 1.0000
3.000 0.4921 0.00594 0.00122 -0.0264 0.3589 1.0000
3.250 0.5181 0.00618 0.00134 -0.0261 0.3273 1.0000
3.500 0.5442 0.00642 0.00147 -0.0259 0.2983 1.0000
3.750 0.5704 0.00669 0.00162 -0.0256 0.2690 1.0000
4.000 0.5965 0.00697 0.00180 -0.0254 0.2399 1.0000
4.250 0.6225 0.00729 0.00199 -0.0252 0.2081 1.0000
4.500 0.6486 0.00758 0.00219 -0.0250 0.1826 1.0000
4.750 0.6745 0.00793 0.00241 -0.0248 0.1522 1.0000
5.000 0.7003 0.00828 0.00265 -0.0246 0.1255 1.0000
5.250 0.7255 0.00876 0.00298 -0.0244 0.0909 1.0000
5.500 0.7513 0.00911 0.00325 -0.0242 0.0711 1.0000
5.750 0.7767 0.00953 0.00357 -0.0240 0.0500 1.0000
6.000 0.8017 0.01001 0.00393 -0.0237 0.0294 1.0000
6.250 0.8273 0.01037 0.00425 -0.0234 0.0208 1.0000
6.500 0.8527 0.01074 0.00460 -0.0232 0.0143 1.0000
6.750 0.8780 0.01114 0.00497 -0.0229 0.0088 1.0000
7.000 0.9033 0.01154 0.00536 -0.0227 0.0052 1.0000
7.250 0.9277 0.01206 0.00590 -0.0223 0.0021 1.0000
7.500 0.9522 0.01256 0.00647 -0.0218 0.0014 1.0000
7.750 0.9769 0.01301 0.00698 -0.0215 0.0013 1.0000
8.000 1.0012 0.01351 0.00755 -0.0211 0.0012 1.0000
8.250 1.0250 0.01407 0.00819 -0.0206 0.0012 1.0000
8.500 1.0481 0.01470 0.00892 -0.0200 0.0012 1.0000
8.750 1.0709 0.01536 0.00966 -0.0194 0.0011 1.0000
9.000 1.0926 0.01613 0.01054 -0.0187 0.0011 1.0000
9.250 1.1134 0.01699 0.01152 -0.0179 0.0011 1.0000
9.500 1.1334 0.01791 0.01255 -0.0171 0.0011 1.0000
9.750 1.1519 0.01897 0.01378 -0.0160 0.0011 1.0000
10.000 1.1692 0.02011 0.01506 -0.0149 0.0011 1.0000
10.250 1.1849 0.02135 0.01645 -0.0136 0.0010 1.0000
10.500 1.1988 0.02271 0.01797 -0.0121 0.0010 1.0000
10.750 1.2110 0.02412 0.01954 -0.0105 0.0010 1.0000
11.000 1.2176 0.02598 0.02161 -0.0084 0.0010 1.0000
11.250 1.2231 0.02751 0.02330 -0.0061 0.0010 1.0000
11.500 1.2227 0.02906 0.02499 -0.0031 0.0010 1.0000
11.750 1.2184 0.03110 0.02721 -0.0005 0.0010 1.0000
12.000 1.2169 0.03314 0.02939 0.0010 0.0010 1.0000
12.250 1.2107 0.03589 0.03232 0.0022 0.0010 1.0000
12.500 1.2055 0.03881 0.03540 0.0026 0.0010 1.0000
12.750 1.1984 0.04221 0.03896 0.0024 0.0010 1.0000
13.000 1.1987 0.04492 0.04177 0.0018 0.0009 1.0000
13.250 1.1742 0.05131 0.04842 -0.0002 0.0010 1.0000
13.500 1.1655 0.05592 0.05317 -0.0023 0.0010 1.0000
13.750 1.1514 0.06178 0.05919 -0.0054 0.0010 1.0000
14.000 1.1223 0.07088 0.06850 -0.0105 0.0010 1.0000
14.250 1.1169 0.07618 0.07388 -0.0137 0.0010 1.0000
14.500 1.0879 0.08681 0.08469 -0.0202 0.0010 1.0000
14.750 1.0742 0.09478 0.09276 -0.0249 0.0010 1.0000
15.000 1.0660 0.10163 0.09968 -0.0288 0.0010 1.0000
15.250 1.0230 0.11759 0.11582 -0.0377 0.0010 1.0000
15.500 0.9946 0.13046 0.12879 -0.0445 0.0011 1.0000
15.750 0.9712 0.14253 0.14094 -0.0507 0.0011 1.0000
16.000 0.9420 0.15719 0.15566 -0.0580 0.0012 1.0000
16.250 0.8820 0.18621 0.18466 -0.0703 0.0013 1.0000
16.500 0.8781 0.19496 0.19338 -0.0742 0.0013 1.0000
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Polar data table (+)
Polar graphs
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