MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 500,000 Max Cl/Cd: 76.17 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh61-il-500000-n5.txt Download as CSV file: xf-mh61-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6077 0.09413 0.09218 0.0139 0.9257 0.0048
-9.500 -0.6159 0.08893 0.08691 0.0120 0.8943 0.0048
-9.250 -0.6248 0.08311 0.08105 0.0091 0.8759 0.0047
-9.000 -0.6359 0.07640 0.07431 0.0052 0.8613 0.0046
-8.750 -0.6542 0.06516 0.06302 -0.0041 0.8474 0.0046
-8.500 -0.6769 0.05900 0.05668 -0.0078 0.8334 0.0046
-8.250 -0.6931 0.05367 0.05113 -0.0086 0.8231 0.0045
-8.000 -0.7010 0.04837 0.04556 -0.0088 0.8150 0.0044
-7.750 -0.7033 0.04318 0.04003 -0.0084 0.8079 0.0042
-7.500 -0.7002 0.03809 0.03454 -0.0075 0.8012 0.0040
-7.250 -0.6925 0.03326 0.02925 -0.0062 0.7951 0.0038
-7.000 -0.6812 0.02850 0.02394 -0.0046 0.7895 0.0036
-6.750 -0.6655 0.02439 0.01925 -0.0030 0.7837 0.0033
-6.500 -0.6453 0.02171 0.01615 -0.0018 0.7786 0.0032
-6.250 -0.6227 0.01973 0.01384 -0.0009 0.7729 0.0032
-6.000 -0.5991 0.01822 0.01206 -0.0001 0.7675 0.0031
-5.750 -0.5749 0.01692 0.01056 0.0006 0.7621 0.0031
-5.500 -0.5503 0.01584 0.00927 0.0012 0.7565 0.0031
-5.250 -0.5256 0.01488 0.00815 0.0018 0.7516 0.0031
-5.000 -0.5003 0.01403 0.00718 0.0024 0.7459 0.0032
-4.750 -0.4749 0.01331 0.00634 0.0028 0.7406 0.0032
-4.500 -0.4489 0.01268 0.00560 0.0032 0.7353 0.0034
-4.250 -0.4225 0.01215 0.00496 0.0036 0.7298 0.0035
-4.000 -0.3959 0.01170 0.00440 0.0039 0.7247 0.0037
-3.750 -0.3687 0.01131 0.00392 0.0041 0.7189 0.0041
-3.500 -0.3414 0.01099 0.00346 0.0043 0.7134 0.0048
-3.250 -0.3140 0.01064 0.00305 0.0046 0.7079 0.0078
-3.000 -0.2873 0.01020 0.00270 0.0048 0.7019 0.0331
-2.750 -0.2644 0.00909 0.00229 0.0052 0.6965 0.1873
-2.500 -0.2387 0.00856 0.00210 0.0053 0.6902 0.2758
-2.000 -0.1848 0.00803 0.00181 0.0056 0.6776 0.3734
-1.750 -0.1574 0.00786 0.00169 0.0057 0.6714 0.4084
-1.500 -0.1299 0.00770 0.00159 0.0057 0.6645 0.4415
-1.250 -0.1024 0.00756 0.00150 0.0058 0.6578 0.4734
-1.000 -0.0750 0.00741 0.00142 0.0059 0.6506 0.5064
-0.500 -0.0206 0.00712 0.00130 0.0062 0.6357 0.5786
-0.250 0.0062 0.00697 0.00125 0.0065 0.6281 0.6196
0.000 0.0328 0.00681 0.00121 0.0068 0.6198 0.6651
0.250 0.0587 0.00664 0.00119 0.0073 0.6116 0.7155
0.500 0.0843 0.00646 0.00117 0.0079 0.6030 0.7710
0.750 0.1103 0.00627 0.00119 0.0085 0.5937 0.8319
1.000 0.1425 0.00615 0.00122 0.0079 0.5839 0.8947
1.250 0.1906 0.00619 0.00128 0.0036 0.5725 0.9371
1.500 0.2355 0.00626 0.00131 -0.0001 0.5605 0.9580
1.750 0.2734 0.00635 0.00136 -0.0023 0.5482 0.9711
2.250 0.3419 0.00655 0.00146 -0.0051 0.5217 0.9904
2.500 0.3772 0.00665 0.00151 -0.0068 0.5073 0.9960
2.750 0.4138 0.00675 0.00159 -0.0088 0.4916 1.0000
3.000 0.4405 0.00686 0.00166 -0.0087 0.4759 1.0000
3.250 0.4672 0.00700 0.00174 -0.0085 0.4583 1.0000
3.750 0.5206 0.00733 0.00198 -0.0083 0.4191 1.0000
4.000 0.5473 0.00754 0.00211 -0.0082 0.3979 1.0000
4.250 0.5738 0.00776 0.00227 -0.0081 0.3751 1.0000
4.500 0.6003 0.00800 0.00245 -0.0081 0.3522 1.0000
4.750 0.6266 0.00827 0.00267 -0.0080 0.3278 1.0000
5.000 0.6528 0.00857 0.00290 -0.0079 0.3020 1.0000
5.250 0.6787 0.00892 0.00315 -0.0078 0.2724 1.0000
5.500 0.7041 0.00937 0.00345 -0.0077 0.2339 1.0000
5.750 0.7294 0.00981 0.00378 -0.0076 0.2009 1.0000
6.000 0.7540 0.01035 0.00416 -0.0074 0.1628 1.0000
6.250 0.7777 0.01103 0.00463 -0.0072 0.1190 1.0000
6.500 0.8012 0.01167 0.00515 -0.0070 0.0865 1.0000
6.750 0.8247 0.01227 0.00565 -0.0066 0.0619 1.0000
7.000 0.8472 0.01297 0.00621 -0.0062 0.0373 1.0000
7.250 0.8695 0.01365 0.00679 -0.0057 0.0209 1.0000
7.500 0.8919 0.01426 0.00736 -0.0052 0.0122 1.0000
7.750 0.9145 0.01480 0.00793 -0.0046 0.0084 1.0000
8.000 0.9360 0.01547 0.00863 -0.0039 0.0050 1.0000
8.250 0.9568 0.01617 0.00939 -0.0032 0.0037 1.0000
8.500 0.9758 0.01708 0.01040 -0.0022 0.0029 1.0000
8.750 0.9952 0.01785 0.01132 -0.0012 0.0027 1.0000
9.000 1.0131 0.01874 0.01233 -0.0001 0.0025 1.0000
9.250 1.0297 0.01968 0.01339 0.0011 0.0024 1.0000
9.500 1.0448 0.02069 0.01451 0.0024 0.0023 1.0000
9.750 1.0573 0.02185 0.01580 0.0040 0.0022 1.0000
10.000 1.0680 0.02306 0.01713 0.0057 0.0021 1.0000
10.250 1.0747 0.02433 0.01853 0.0078 0.0021 1.0000
10.500 1.0779 0.02567 0.01999 0.0102 0.0021 1.0000
10.750 1.0813 0.02727 0.02172 0.0120 0.0020 1.0000
11.000 1.0850 0.02904 0.02362 0.0134 0.0020 1.0000
11.250 1.0879 0.03102 0.02575 0.0146 0.0020 1.0000
11.500 1.0908 0.03310 0.02796 0.0155 0.0019 1.0000
11.750 1.0924 0.03542 0.03045 0.0162 0.0019 1.0000
12.000 1.0926 0.03796 0.03315 0.0167 0.0019 1.0000
12.250 1.0904 0.04088 0.03627 0.0169 0.0019 1.0000
12.500 1.0873 0.04402 0.03959 0.0168 0.0019 1.0000
12.750 1.0819 0.04758 0.04333 0.0164 0.0019 1.0000
13.000 1.0758 0.05137 0.04729 0.0155 0.0019 1.0000
13.250 1.0676 0.05563 0.05172 0.0143 0.0019 1.0000
13.500 1.0572 0.06042 0.05670 0.0125 0.0019 1.0000
13.750 1.0446 0.06580 0.06226 0.0102 0.0019 1.0000
14.000 1.0309 0.07177 0.06840 0.0073 0.0019 1.0000
14.250 1.0191 0.07778 0.07456 0.0042 0.0019 1.0000
14.500 1.0054 0.08446 0.08139 0.0006 0.0019 1.0000
14.750 0.9861 0.09263 0.08973 -0.0038 0.0019 1.0000
15.000 0.9697 0.10057 0.09780 -0.0082 0.0020 1.0000
15.250 0.9462 0.11059 0.10799 -0.0136 0.0020 1.0000
15.500 0.9252 0.12051 0.11803 -0.0188 0.0020 1.0000
15.750 0.9051 0.13075 0.12835 -0.0240 0.0021 1.0000
16.000 0.8753 0.14451 0.14222 -0.0306 0.0021 1.0000
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Polar data table (+)
Polar graphs
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