MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 200,000 Max Cl/Cd: 61.8 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh43-il-200000-n5.txt Download as CSV file: xf-mh43-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5303 0.08791 0.08458 -0.0043 1.0000 0.0096
-8.500 -0.5317 0.08327 0.07999 -0.0070 1.0000 0.0093
-8.250 -0.5345 0.07850 0.07527 -0.0100 1.0000 0.0091
-8.000 -0.5402 0.07341 0.07024 -0.0138 1.0000 0.0089
-7.750 -0.5465 0.06712 0.06398 -0.0199 1.0000 0.0088
-7.500 -0.5476 0.05994 0.05673 -0.0258 1.0000 0.0085
-7.250 -0.5470 0.05243 0.04905 -0.0300 1.0000 0.0082
-7.000 -0.5443 0.04476 0.04105 -0.0324 1.0000 0.0077
-6.750 -0.5391 0.03715 0.03288 -0.0333 1.0000 0.0072
-6.500 -0.5267 0.03182 0.02697 -0.0330 1.0000 0.0069
-6.250 -0.5094 0.02806 0.02268 -0.0324 1.0000 0.0067
-6.000 -0.4897 0.02518 0.01934 -0.0317 1.0000 0.0066
-5.750 -0.4688 0.02281 0.01657 -0.0309 1.0000 0.0066
-5.500 -0.4401 0.02060 0.01399 -0.0315 0.9839 0.0067
-5.250 -0.4073 0.01864 0.01172 -0.0327 0.9652 0.0068
-5.000 -0.3755 0.01708 0.00992 -0.0336 0.9481 0.0071
-4.750 -0.3454 0.01587 0.00852 -0.0341 0.9313 0.0075
-4.500 -0.3175 0.01495 0.00737 -0.0340 0.9152 0.0082
-4.250 -0.2911 0.01419 0.00643 -0.0336 0.8999 0.0092
-4.000 -0.2651 0.01357 0.00560 -0.0329 0.8856 0.0113
-3.750 -0.2402 0.01281 0.00482 -0.0322 0.8723 0.0250
-3.500 -0.2165 0.01193 0.00428 -0.0316 0.8597 0.0880
-3.250 -0.1917 0.01143 0.00394 -0.0310 0.8477 0.1492
-3.000 -0.1660 0.01111 0.00366 -0.0306 0.8361 0.1890
-2.750 -0.1408 0.01070 0.00342 -0.0301 0.8250 0.2507
-2.500 -0.1161 0.01026 0.00318 -0.0296 0.8145 0.3316
-2.250 -0.0913 0.00988 0.00300 -0.0290 0.8044 0.4100
-2.000 -0.0668 0.00950 0.00286 -0.0283 0.7941 0.4958
-1.750 -0.0425 0.00916 0.00276 -0.0274 0.7839 0.5813
-1.500 -0.0186 0.00886 0.00269 -0.0263 0.7743 0.6630
-1.250 0.0052 0.00865 0.00262 -0.0250 0.7650 0.7369
-1.000 0.0299 0.00848 0.00258 -0.0238 0.7550 0.8024
-0.750 0.0576 0.00839 0.00254 -0.0231 0.7454 0.8611
-0.500 0.0921 0.00835 0.00248 -0.0240 0.7360 0.9113
-0.250 0.1326 0.00834 0.00237 -0.0264 0.7260 0.9503
0.000 0.1737 0.00835 0.00229 -0.0291 0.7153 0.9794
0.250 0.2149 0.00836 0.00221 -0.0319 0.7045 1.0000
0.500 0.2396 0.00841 0.00218 -0.0313 0.6937 1.0000
0.750 0.2646 0.00848 0.00215 -0.0307 0.6827 1.0000
1.000 0.2898 0.00855 0.00214 -0.0301 0.6712 1.0000
1.250 0.3153 0.00862 0.00216 -0.0296 0.6592 1.0000
1.500 0.3410 0.00870 0.00218 -0.0291 0.6471 1.0000
1.750 0.3668 0.00879 0.00224 -0.0287 0.6348 1.0000
2.000 0.3927 0.00888 0.00229 -0.0282 0.6219 1.0000
2.250 0.4187 0.00898 0.00235 -0.0278 0.6082 1.0000
2.500 0.4448 0.00909 0.00242 -0.0274 0.5937 1.0000
2.750 0.4709 0.00921 0.00254 -0.0270 0.5782 1.0000
3.000 0.4970 0.00934 0.00264 -0.0266 0.5616 1.0000
3.250 0.5232 0.00948 0.00276 -0.0263 0.5428 1.0000
3.500 0.5491 0.00965 0.00289 -0.0259 0.5224 1.0000
3.750 0.5752 0.00982 0.00307 -0.0255 0.4993 1.0000
4.000 0.6009 0.01004 0.00324 -0.0251 0.4736 1.0000
4.250 0.6265 0.01029 0.00343 -0.0247 0.4447 1.0000
4.500 0.6518 0.01059 0.00366 -0.0243 0.4112 1.0000
4.750 0.6767 0.01095 0.00392 -0.0238 0.3740 1.0000
5.000 0.7012 0.01139 0.00424 -0.0234 0.3333 1.0000
5.250 0.7254 0.01190 0.00466 -0.0230 0.2902 1.0000
5.500 0.7492 0.01247 0.00509 -0.0226 0.2472 1.0000
5.750 0.7728 0.01308 0.00558 -0.0222 0.2051 1.0000
6.000 0.7959 0.01378 0.00611 -0.0218 0.1632 1.0000
6.250 0.8188 0.01451 0.00670 -0.0213 0.1261 1.0000
6.500 0.8413 0.01528 0.00734 -0.0209 0.0942 1.0000
6.750 0.8637 0.01607 0.00804 -0.0203 0.0688 1.0000
7.000 0.8859 0.01687 0.00880 -0.0198 0.0492 1.0000
7.250 0.9078 0.01772 0.00968 -0.0191 0.0370 1.0000
7.500 0.9287 0.01871 0.01080 -0.0183 0.0282 1.0000
7.750 0.9481 0.01986 0.01198 -0.0174 0.0205 1.0000
8.000 0.9695 0.02066 0.01286 -0.0167 0.0146 1.0000
8.250 0.9877 0.02191 0.01422 -0.0157 0.0104 1.0000
8.500 1.0069 0.02292 0.01531 -0.0149 0.0075 1.0000
8.750 1.0196 0.02483 0.01740 -0.0133 0.0065 1.0000
9.000 1.0348 0.02635 0.01914 -0.0120 0.0058 1.0000
9.250 1.0480 0.02811 0.02111 -0.0105 0.0053 1.0000
9.500 1.0600 0.03001 0.02323 -0.0089 0.0050 1.0000
9.750 1.0702 0.03208 0.02553 -0.0073 0.0047 1.0000
10.000 1.0784 0.03427 0.02796 -0.0056 0.0045 1.0000
10.250 1.0823 0.03658 0.03053 -0.0036 0.0044 1.0000
10.500 1.0816 0.03906 0.03333 -0.0013 0.0043 1.0000
10.750 1.0786 0.04171 0.03623 0.0004 0.0043 1.0000
11.000 1.0724 0.04474 0.03951 0.0015 0.0041 1.0000
11.250 1.0642 0.04826 0.04329 0.0019 0.0042 1.0000
11.500 1.0537 0.05230 0.04758 0.0015 0.0042 1.0000
11.750 1.0415 0.05682 0.05233 0.0003 0.0042 1.0000
12.000 1.0274 0.06204 0.05778 -0.0019 0.0042 1.0000
12.250 1.0107 0.06819 0.06414 -0.0051 0.0042 1.0000
12.500 0.9933 0.07506 0.07121 -0.0093 0.0043 1.0000
12.750 0.9745 0.08302 0.07934 -0.0144 0.0043 1.0000
13.000 0.9554 0.09187 0.08835 -0.0202 0.0044 1.0000
13.250 0.9330 0.10260 0.09916 -0.0271 0.0045 1.0000
13.500 0.9097 0.11464 0.11130 -0.0342 0.0047 1.0000
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Polar data table (+)
Polar graphs
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