MH 23 8% (mh23-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 500,000 Max Cl/Cd: 66.59 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh23-il-500000-n5.txt Download as CSV file: xf-mh23-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5021 0.07535 0.07321 -0.0329 1.0000 0.0040
-8.250 -0.5149 0.07160 0.06951 -0.0348 1.0000 0.0041
-8.000 -0.5281 0.06725 0.06514 -0.0364 0.9966 0.0040
-7.750 -0.5218 0.06070 0.05849 -0.0421 0.9913 0.0040
-7.500 -0.5130 0.05260 0.05020 -0.0465 0.9870 0.0045
-7.250 -0.5051 0.04562 0.04296 -0.0491 0.9839 0.0047
-7.000 -0.4895 0.04039 0.03747 -0.0504 0.9817 0.0046
-6.750 -0.4810 0.03694 0.03377 -0.0502 0.9775 0.0052
-6.500 -0.4611 0.03611 0.03279 -0.0506 0.9750 0.0062
-6.250 -0.4430 0.03268 0.02909 -0.0502 0.9723 0.0066
-6.000 -0.4167 0.03121 0.02746 -0.0501 0.9707 0.0085
-5.750 -0.4038 0.02687 0.02268 -0.0484 0.9672 0.0076
-5.500 -0.3895 0.02333 0.01871 -0.0458 0.9629 0.0067
-5.250 -0.3701 0.01976 0.01462 -0.0437 0.9598 0.0058
-5.000 -0.3462 0.01724 0.01170 -0.0424 0.9576 0.0052
-4.750 -0.3202 0.01584 0.01004 -0.0417 0.9559 0.0049
-4.500 -0.2971 0.01485 0.00890 -0.0406 0.9530 0.0048
-4.250 -0.2734 0.01397 0.00790 -0.0396 0.9497 0.0047
-4.000 -0.2488 0.01316 0.00698 -0.0388 0.9466 0.0046
-3.750 -0.2244 0.01226 0.00598 -0.0379 0.9439 0.0045
-3.500 -0.2010 0.01162 0.00522 -0.0369 0.9407 0.0044
-3.250 -0.1792 0.01095 0.00446 -0.0355 0.9364 0.0045
-3.000 -0.1555 0.01040 0.00381 -0.0345 0.9327 0.0045
-2.750 -0.1304 0.00999 0.00327 -0.0337 0.9297 0.0047
-2.500 -0.1063 0.00971 0.00287 -0.0328 0.9250 0.0051
-2.250 -0.0811 0.00948 0.00256 -0.0320 0.9205 0.0064
-2.000 -0.0569 0.00902 0.00228 -0.0312 0.9167 0.0550
-1.750 -0.0388 0.00806 0.00210 -0.0297 0.9110 0.2576
-1.500 -0.0275 0.00670 0.00192 -0.0268 0.9052 0.5789
-1.250 -0.0094 0.00616 0.00181 -0.0246 0.8995 0.7023
-1.000 0.0113 0.00573 0.00179 -0.0226 0.8933 0.8154
-0.750 0.0460 0.00562 0.00183 -0.0237 0.8891 0.8859
-0.500 0.0854 0.00568 0.00189 -0.0260 0.8824 0.9168
-0.250 0.1204 0.00575 0.00193 -0.0272 0.8753 0.9371
0.000 0.1518 0.00582 0.00198 -0.0277 0.8654 0.9492
0.250 0.1810 0.00585 0.00198 -0.0278 0.8532 0.9568
0.500 0.2160 0.00585 0.00193 -0.0293 0.8370 0.9602
0.750 0.2465 0.00587 0.00186 -0.0297 0.8117 0.9651
1.000 0.2754 0.00595 0.00178 -0.0297 0.7749 0.9697
1.250 0.3102 0.00613 0.00176 -0.0311 0.7293 0.9727
1.500 0.3423 0.00640 0.00180 -0.0321 0.6780 0.9770
1.750 0.3698 0.00671 0.00190 -0.0321 0.6254 0.9819
2.000 0.4036 0.00702 0.00196 -0.0336 0.5661 0.9841
2.250 0.4353 0.00733 0.00204 -0.0348 0.5096 0.9867
2.500 0.4653 0.00764 0.00214 -0.0356 0.4567 0.9893
2.750 0.4939 0.00795 0.00226 -0.0361 0.4059 0.9917
3.250 0.5517 0.00862 0.00257 -0.0373 0.3036 0.9953
3.500 0.5814 0.00894 0.00273 -0.0381 0.2595 0.9970
3.750 0.6106 0.00927 0.00290 -0.0388 0.2165 0.9986
4.000 0.6399 0.00961 0.00310 -0.0395 0.1805 1.0000
4.250 0.6614 0.00995 0.00335 -0.0385 0.1458 1.0000
4.500 0.6817 0.01041 0.00362 -0.0373 0.1044 1.0000
4.750 0.7028 0.01077 0.00389 -0.0361 0.0806 1.0000
5.000 0.7236 0.01115 0.00419 -0.0350 0.0593 1.0000
5.250 0.7433 0.01166 0.00455 -0.0336 0.0334 1.0000
5.500 0.7636 0.01209 0.00491 -0.0324 0.0204 1.0000
5.750 0.7847 0.01242 0.00526 -0.0312 0.0160 1.0000
6.000 0.8054 0.01278 0.00565 -0.0299 0.0121 1.0000
6.250 0.8247 0.01329 0.00619 -0.0284 0.0046 1.0000
6.500 0.8443 0.01377 0.00671 -0.0270 0.0029 1.0000
6.750 0.8629 0.01437 0.00739 -0.0252 0.0020 1.0000
7.000 0.8813 0.01500 0.00815 -0.0235 0.0017 1.0000
7.250 0.8984 0.01575 0.00905 -0.0215 0.0016 1.0000
7.500 0.9141 0.01665 0.01012 -0.0193 0.0015 1.0000
7.750 0.9281 0.01772 0.01136 -0.0168 0.0015 1.0000
8.000 0.9419 0.01881 0.01261 -0.0143 0.0015 1.0000
8.250 0.9550 0.01998 0.01397 -0.0118 0.0015 1.0000
8.500 0.9671 0.02132 0.01550 -0.0091 0.0014 1.0000
8.750 0.9779 0.02284 0.01725 -0.0063 0.0014 1.0000
9.000 0.9874 0.02452 0.01917 -0.0034 0.0014 1.0000
9.250 0.9938 0.02655 0.02150 -0.0001 0.0014 1.0000
9.500 0.9983 0.02866 0.02389 0.0033 0.0014 1.0000
9.750 0.9983 0.03109 0.02663 0.0072 0.0014 1.0000
10.000 0.9943 0.03364 0.02949 0.0113 0.0014 1.0000
10.250 0.9836 0.03603 0.03215 0.0163 0.0014 1.0000
10.500 0.9734 0.03836 0.03470 0.0204 0.0014 1.0000
10.750 0.9578 0.04140 0.03799 0.0241 0.0015 1.0000
11.000 0.9380 0.04512 0.04196 0.0268 0.0015 1.0000
11.250 0.9200 0.04907 0.04611 0.0278 0.0015 1.0000
11.500 0.9061 0.05318 0.05038 0.0271 0.0015 1.0000
11.750 0.8853 0.05946 0.05684 0.0238 0.0015 1.0000
12.000 0.8716 0.06625 0.06377 0.0187 0.0015 1.0000
12.250 0.8509 0.07712 0.07479 0.0106 0.0015 1.0000
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Polar data table (+)
Polar graphs
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