MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.37 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh24-il-1000000-n5.txt Download as CSV file: xf-mh24-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4849 0.10773 0.10606 -0.0272 1.0000 0.0039
-10.750 -0.4832 0.10499 0.10333 -0.0282 1.0000 0.0042
-10.500 -0.4828 0.10132 0.09968 -0.0294 1.0000 0.0043
-10.250 -0.4837 0.09738 0.09575 -0.0307 1.0000 0.0043
-10.000 -0.4820 0.09463 0.09302 -0.0315 1.0000 0.0046
-9.500 -0.4800 0.08602 0.08444 -0.0366 0.9920 0.0048
-9.250 -0.4767 0.08077 0.07919 -0.0412 0.9892 0.0049
-9.000 -0.4731 0.07488 0.07332 -0.0477 0.9865 0.0050
-8.750 -0.4719 0.06655 0.06496 -0.0599 0.9834 0.0050
-8.500 -0.4739 0.06006 0.05837 -0.0658 0.9771 0.0049
-8.250 -0.4752 0.05409 0.05226 -0.0685 0.9708 0.0049
-8.000 -0.4742 0.04995 0.04799 -0.0686 0.9656 0.0050
-7.750 -0.4712 0.04642 0.04432 -0.0675 0.9608 0.0053
-7.500 -0.4684 0.04240 0.04012 -0.0659 0.9565 0.0054
-7.250 -0.4619 0.03905 0.03659 -0.0640 0.9529 0.0057
-7.000 -0.4554 0.03545 0.03278 -0.0616 0.9494 0.0058
-6.750 -0.4457 0.03231 0.02941 -0.0593 0.9461 0.0060
-6.500 -0.4351 0.02919 0.02603 -0.0567 0.9434 0.0061
-6.250 -0.4216 0.02657 0.02316 -0.0545 0.9408 0.0062
-6.000 -0.4083 0.02375 0.02004 -0.0520 0.9377 0.0061
-5.500 -0.3767 0.01665 0.01206 -0.0461 0.9321 0.0034
-5.250 -0.3552 0.01496 0.01012 -0.0448 0.9302 0.0033
-5.000 -0.3325 0.01340 0.00832 -0.0436 0.9281 0.0032
-4.750 -0.3092 0.01229 0.00707 -0.0426 0.9254 0.0031
-4.500 -0.2861 0.01134 0.00600 -0.0415 0.9224 0.0030
-4.250 -0.2633 0.01050 0.00505 -0.0403 0.9195 0.0029
-4.000 -0.2399 0.00987 0.00432 -0.0393 0.9170 0.0029
-3.750 -0.2161 0.00934 0.00370 -0.0384 0.9142 0.0029
-3.500 -0.1917 0.00890 0.00319 -0.0377 0.9108 0.0028
-3.250 -0.1667 0.00856 0.00278 -0.0370 0.9073 0.0028
-3.000 -0.1411 0.00828 0.00240 -0.0365 0.9040 0.0029
-2.750 -0.1151 0.00807 0.00214 -0.0361 0.9006 0.0029
-2.500 -0.0890 0.00788 0.00191 -0.0357 0.8964 0.0031
-2.250 -0.0626 0.00772 0.00171 -0.0354 0.8921 0.0035
-2.000 -0.0378 0.00737 0.00151 -0.0348 0.8879 0.0469
-1.750 -0.0140 0.00695 0.00138 -0.0341 0.8820 0.1258
-1.500 0.0054 0.00612 0.00119 -0.0328 0.8762 0.3192
-1.250 0.0239 0.00537 0.00107 -0.0313 0.8685 0.5053
-1.000 0.0464 0.00500 0.00097 -0.0302 0.8601 0.5942
-0.750 0.0669 0.00457 0.00086 -0.0287 0.8489 0.6981
-0.500 0.0872 0.00421 0.00082 -0.0270 0.8339 0.7945
-0.250 0.1106 0.00414 0.00083 -0.0258 0.8122 0.8518
0.000 0.1350 0.00421 0.00083 -0.0249 0.7838 0.8771
0.250 0.1587 0.00435 0.00087 -0.0238 0.7508 0.8946
0.500 0.1821 0.00453 0.00092 -0.0228 0.7146 0.9054
0.750 0.2053 0.00474 0.00098 -0.0218 0.6758 0.9131
1.000 0.2290 0.00494 0.00104 -0.0209 0.6381 0.9184
1.250 0.2523 0.00515 0.00111 -0.0200 0.6005 0.9240
1.500 0.2753 0.00537 0.00119 -0.0190 0.5616 0.9302
1.750 0.2978 0.00562 0.00131 -0.0178 0.5225 0.9371
2.000 0.3199 0.00587 0.00142 -0.0166 0.4845 0.9437
2.250 0.3436 0.00611 0.00153 -0.0158 0.4470 0.9477
2.500 0.3673 0.00634 0.00163 -0.0151 0.4108 0.9510
2.750 0.3905 0.00656 0.00172 -0.0143 0.3764 0.9542
3.000 0.4146 0.00679 0.00181 -0.0137 0.3409 0.9564
3.250 0.4394 0.00703 0.00195 -0.0132 0.3060 0.9582
3.500 0.4644 0.00728 0.00208 -0.0129 0.2730 0.9600
3.750 0.4890 0.00754 0.00222 -0.0124 0.2406 0.9621
4.000 0.5133 0.00780 0.00236 -0.0119 0.2089 0.9644
4.250 0.5368 0.00808 0.00252 -0.0113 0.1783 0.9668
4.500 0.5600 0.00833 0.00270 -0.0105 0.1536 0.9692
4.750 0.5861 0.00866 0.00290 -0.0105 0.1228 0.9707
5.000 0.6117 0.00903 0.00314 -0.0104 0.0911 0.9724
5.250 0.6380 0.00934 0.00337 -0.0104 0.0718 0.9740
5.500 0.6639 0.00967 0.00362 -0.0104 0.0529 0.9758
5.750 0.6883 0.01011 0.00392 -0.0101 0.0295 0.9779
6.000 0.7131 0.01042 0.00423 -0.0097 0.0205 0.9801
6.250 0.7381 0.01072 0.00452 -0.0095 0.0152 0.9821
6.500 0.7671 0.01103 0.00482 -0.0101 0.0112 0.9830
6.750 0.7956 0.01139 0.00517 -0.0107 0.0080 0.9840
7.000 0.8240 0.01171 0.00552 -0.0112 0.0057 0.9850
7.250 0.8507 0.01232 0.00609 -0.0114 0.0014 0.9861
7.500 0.8782 0.01271 0.00655 -0.0118 0.0013 0.9872
7.750 0.9051 0.01317 0.00708 -0.0120 0.0012 0.9885
8.000 0.9311 0.01371 0.00770 -0.0120 0.0011 0.9900
8.250 0.9562 0.01426 0.00839 -0.0119 0.0011 0.9917
8.500 0.9803 0.01485 0.00907 -0.0117 0.0010 0.9935
8.750 1.0051 0.01560 0.00994 -0.0116 0.0010 0.9950
9.000 1.0295 0.01640 0.01087 -0.0116 0.0010 0.9967
9.250 1.0525 0.01738 0.01200 -0.0113 0.0010 0.9987
9.500 1.0712 0.01839 0.01315 -0.0101 0.0010 1.0000
9.750 1.0771 0.01925 0.01415 -0.0062 0.0010 1.0000
10.000 1.0854 0.02008 0.01510 -0.0029 0.0010 1.0000
10.250 1.0925 0.02112 0.01629 0.0005 0.0010 1.0000
10.500 1.0947 0.02245 0.01780 0.0047 0.0010 1.0000
10.750 1.1000 0.02349 0.01898 0.0082 0.0010 1.0000
11.000 1.0996 0.02515 0.02086 0.0123 0.0010 1.0000
11.250 1.1027 0.02652 0.02242 0.0157 0.0010 1.0000
11.500 1.0982 0.02860 0.02473 0.0197 0.0010 1.0000
11.750 1.0987 0.03020 0.02650 0.0227 0.0010 1.0000
12.000 1.0896 0.03268 0.02922 0.0264 0.0010 1.0000
12.250 1.0786 0.03538 0.03215 0.0297 0.0010 1.0000
12.500 1.0696 0.03801 0.03496 0.0321 0.0010 1.0000
12.750 1.0507 0.04186 0.03905 0.0341 0.0010 1.0000
13.000 1.0313 0.04626 0.04366 0.0346 0.0010 1.0000
13.250 1.0173 0.05064 0.04820 0.0338 0.0010 1.0000
13.500 1.0036 0.05569 0.05339 0.0317 0.0010 1.0000
13.750 0.9817 0.06316 0.06104 0.0272 0.0010 1.0000
14.000 0.9715 0.06949 0.06748 0.0230 0.0010 1.0000
14.250 0.9409 0.08134 0.07950 0.0153 0.0010 1.0000
14.500 0.9258 0.08983 0.08807 0.0104 0.0010 1.0000
14.750 0.8963 0.10180 0.10014 0.0043 0.0010 1.0000
15.000 0.8629 0.11473 0.11310 -0.0017 0.0010 1.0000
15.250 0.8480 0.12301 0.12141 -0.0056 0.0010 1.0000
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