MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.97 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh43-il-1000000.txt Download as CSV file: xf-mh43-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5357 0.08085 0.07939 -0.0073 1.0000 0.0078
-8.250 -0.5391 0.07635 0.07491 -0.0101 1.0000 0.0078
-8.000 -0.5480 0.07160 0.07020 -0.0134 1.0000 0.0078
-7.750 -0.5554 0.06485 0.06344 -0.0205 1.0000 0.0078
-7.500 -0.5561 0.05745 0.05596 -0.0263 1.0000 0.0077
-7.250 -0.5526 0.05078 0.04916 -0.0299 1.0000 0.0079
-7.000 -0.5454 0.04479 0.04298 -0.0319 1.0000 0.0080
-6.750 -0.5347 0.03964 0.03762 -0.0329 1.0000 0.0083
-6.500 -0.5206 0.03512 0.03285 -0.0333 0.9987 0.0088
-6.250 -0.4921 0.03051 0.02787 -0.0359 0.9550 0.0095
-6.000 -0.4741 0.02794 0.02498 -0.0346 0.9204 0.0104
-5.750 -0.4479 0.02857 0.02546 -0.0334 0.8982 0.0117
-5.500 -0.4274 0.02681 0.02337 -0.0324 0.8794 0.0119
-4.750 -0.3675 0.01352 0.00847 -0.0282 0.8392 0.0065
-4.500 -0.3415 0.01250 0.00732 -0.0276 0.8280 0.0057
-4.250 -0.3169 0.01089 0.00546 -0.0267 0.8175 0.0053
-4.000 -0.2912 0.00991 0.00429 -0.0261 0.8069 0.0051
-3.750 -0.2646 0.00923 0.00345 -0.0256 0.7968 0.0050
-3.500 -0.2375 0.00875 0.00283 -0.0252 0.7870 0.0050
-3.250 -0.2102 0.00841 0.00236 -0.0249 0.7775 0.0052
-3.000 -0.1824 0.00817 0.00200 -0.0247 0.7677 0.0058
-2.750 -0.1558 0.00756 0.00159 -0.0244 0.7584 0.0621
-2.500 -0.1289 0.00719 0.00140 -0.0243 0.7493 0.1221
-2.250 -0.1018 0.00691 0.00127 -0.0243 0.7399 0.1724
-2.000 -0.0747 0.00659 0.00116 -0.0242 0.7307 0.2394
-1.750 -0.0484 0.00616 0.00106 -0.0242 0.7217 0.3438
-1.500 -0.0214 0.00589 0.00098 -0.0241 0.7123 0.4205
-1.250 0.0050 0.00551 0.00091 -0.0239 0.7028 0.5252
-1.000 0.0316 0.00526 0.00087 -0.0237 0.6935 0.6050
-0.750 0.0579 0.00504 0.00084 -0.0233 0.6839 0.6828
-0.500 0.0842 0.00486 0.00083 -0.0229 0.6738 0.7472
-0.250 0.1104 0.00471 0.00081 -0.0224 0.6641 0.8025
0.000 0.1359 0.00460 0.00082 -0.0217 0.6546 0.8534
0.500 0.1890 0.00447 0.00084 -0.0205 0.6343 0.9417
0.750 0.2256 0.00449 0.00085 -0.0223 0.6231 0.9696
1.000 0.2647 0.00454 0.00085 -0.0247 0.6111 0.9849
1.250 0.3034 0.00460 0.00085 -0.0271 0.5985 0.9952
1.500 0.3386 0.00466 0.00085 -0.0287 0.5853 1.0000
1.750 0.3646 0.00473 0.00088 -0.0283 0.5721 1.0000
2.000 0.3908 0.00481 0.00091 -0.0280 0.5577 1.0000
2.250 0.4170 0.00490 0.00094 -0.0276 0.5423 1.0000
2.500 0.4433 0.00500 0.00099 -0.0273 0.5260 1.0000
2.750 0.4696 0.00513 0.00106 -0.0270 0.5080 1.0000
3.000 0.4962 0.00525 0.00113 -0.0267 0.4885 1.0000
3.250 0.5226 0.00541 0.00122 -0.0264 0.4653 1.0000
3.500 0.5491 0.00558 0.00131 -0.0262 0.4411 1.0000
3.750 0.5755 0.00579 0.00144 -0.0260 0.4132 1.0000
4.000 0.6018 0.00602 0.00157 -0.0258 0.3817 1.0000
4.250 0.6278 0.00632 0.00174 -0.0255 0.3441 1.0000
4.500 0.6539 0.00663 0.00192 -0.0253 0.3083 1.0000
4.750 0.6796 0.00701 0.00214 -0.0251 0.2679 1.0000
5.000 0.7052 0.00741 0.00238 -0.0249 0.2275 1.0000
5.250 0.7302 0.00792 0.00269 -0.0247 0.1783 1.0000
5.500 0.7555 0.00837 0.00298 -0.0244 0.1423 1.0000
5.750 0.7803 0.00890 0.00332 -0.0242 0.1047 1.0000
6.000 0.8051 0.00941 0.00368 -0.0239 0.0723 1.0000
6.250 0.8304 0.00984 0.00402 -0.0237 0.0538 1.0000
6.500 0.8556 0.01028 0.00438 -0.0234 0.0376 1.0000
6.750 0.8803 0.01079 0.00479 -0.0231 0.0230 1.0000
7.000 0.9052 0.01124 0.00521 -0.0228 0.0147 1.0000
7.250 0.9280 0.01211 0.00607 -0.0221 0.0036 1.0000
7.500 0.9517 0.01282 0.00691 -0.0215 0.0030 1.0000
7.750 0.9752 0.01349 0.00769 -0.0209 0.0028 1.0000
8.000 0.9978 0.01429 0.00861 -0.0201 0.0027 1.0000
8.250 1.0192 0.01524 0.00969 -0.0193 0.0027 1.0000
8.500 1.0391 0.01636 0.01096 -0.0182 0.0026 1.0000
8.750 1.0577 0.01761 0.01237 -0.0171 0.0026 1.0000
9.000 1.0742 0.01917 0.01411 -0.0156 0.0027 1.0000
9.250 1.0888 0.02100 0.01614 -0.0140 0.0027 1.0000
9.500 1.1019 0.02308 0.01844 -0.0123 0.0028 1.0000
9.750 1.1114 0.02570 0.02132 -0.0103 0.0028 1.0000
10.000 1.1161 0.02887 0.02479 -0.0080 0.0029 1.0000
10.250 1.1061 0.03372 0.03008 -0.0048 0.0031 1.0000
10.500 1.1050 0.03637 0.03288 -0.0022 0.0033 1.0000
10.750 1.1010 0.03811 0.03476 0.0006 0.0033 1.0000
11.000 1.1105 0.03863 0.03534 0.0020 0.0035 1.0000
11.250 1.0931 0.04227 0.03919 0.0037 0.0034 1.0000
11.500 1.0784 0.04606 0.04316 0.0041 0.0034 1.0000
11.750 1.0761 0.04870 0.04592 0.0038 0.0034 1.0000
12.000 1.0582 0.05375 0.05115 0.0022 0.0034 1.0000
12.250 1.0451 0.05868 0.05623 0.0000 0.0034 1.0000
12.500 1.0322 0.06408 0.06177 -0.0030 0.0034 1.0000
12.750 1.0164 0.07059 0.06842 -0.0070 0.0034 1.0000
13.000 0.9855 0.08080 0.07881 -0.0138 0.0033 1.0000
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Polar data table (+)
Polar graphs
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