MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 1,000,000 Max Cl/Cd: 61.25 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh27-il-1000000-n5.txt Download as CSV file: xf-mh27-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
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 -0.3501 0.06785 0.06604 -0.1102 0.9739 0.0022
-10.750 -0.3793 0.05329 0.05133 -0.1243 0.9718 0.0022
-10.500 -0.3949 0.04898 0.04690 -0.1247 0.9685 0.0022
-10.250 -0.4131 0.04488 0.04266 -0.1229 0.9645 0.0022
-10.000 -0.4375 0.04004 0.03759 -0.1193 0.9603 0.0021
-9.750 -0.4577 0.03632 0.03365 -0.1141 0.9563 0.0021
-9.500 -0.4903 0.03205 0.02908 -0.1055 0.9509 0.0020
-9.250 -0.4996 0.02970 0.02650 -0.0999 0.9478 0.0020
-9.000 -0.5126 0.02586 0.02223 -0.0936 0.9447 0.0019
-8.750 -0.5149 0.02329 0.01934 -0.0886 0.9423 0.0019
-8.500 -0.5109 0.02099 0.01670 -0.0845 0.9400 0.0019
-8.250 -0.5004 0.01901 0.01441 -0.0816 0.9382 0.0018
-8.000 -0.4844 0.01761 0.01278 -0.0796 0.9368 0.0018
-7.750 -0.4657 0.01643 0.01140 -0.0781 0.9355 0.0018
-7.500 -0.4465 0.01508 0.00983 -0.0766 0.9343 0.0018
-7.250 -0.4252 0.01440 0.00905 -0.0756 0.9334 0.0018
-7.000 -0.4049 0.01354 0.00806 -0.0743 0.9324 0.0018
-6.750 -0.3839 0.01291 0.00732 -0.0732 0.9314 0.0018
-6.500 -0.3648 0.01237 0.00670 -0.0716 0.9300 0.0019
-6.250 -0.3462 0.01192 0.00619 -0.0698 0.9285 0.0019
-6.000 -0.3269 0.01150 0.00570 -0.0682 0.9268 0.0019
-5.750 -0.3065 0.01110 0.00524 -0.0668 0.9252 0.0020
-5.500 -0.2845 0.01080 0.00488 -0.0658 0.9237 0.0021
-5.250 -0.2620 0.01046 0.00448 -0.0648 0.9223 0.0022
-5.000 -0.2378 0.01022 0.00421 -0.0642 0.9210 0.0023
-4.750 -0.2140 0.00989 0.00383 -0.0635 0.9198 0.0031
-4.500 -0.1890 0.00965 0.00357 -0.0631 0.9187 0.0038
-4.250 -0.1635 0.00948 0.00337 -0.0627 0.9175 0.0044
-4.000 -0.1448 0.00931 0.00323 -0.0609 0.9149 0.0092
-3.750 -0.1239 0.00909 0.00306 -0.0596 0.9121 0.0207
-3.500 -0.1017 0.00875 0.00285 -0.0586 0.9095 0.0494
-3.250 -0.0814 0.00817 0.00261 -0.0573 0.9071 0.1336
-3.000 -0.0585 0.00774 0.00239 -0.0565 0.9050 0.2000
-2.750 -0.0403 0.00745 0.00228 -0.0547 0.9018 0.2531
-2.500 -0.0232 0.00714 0.00217 -0.0526 0.8979 0.3170
-2.250 -0.0075 0.00660 0.00200 -0.0502 0.8944 0.4257
-2.000 0.0138 0.00625 0.00185 -0.0490 0.8917 0.4885
-1.750 0.0264 0.00598 0.00179 -0.0458 0.8872 0.5506
-1.500 0.0361 0.00562 0.00168 -0.0419 0.8821 0.6277
-1.250 0.0491 0.00520 0.00152 -0.0386 0.8780 0.7084
-1.000 0.0537 0.00492 0.00152 -0.0333 0.8709 0.7782
-0.750 0.0768 0.00475 0.00156 -0.0321 0.8659 0.8436
-0.500 0.1007 0.00476 0.00162 -0.0312 0.8595 0.8710
-0.250 0.1270 0.00476 0.00161 -0.0308 0.8519 0.8872
0.000 0.1542 0.00479 0.00164 -0.0306 0.8411 0.8954
0.250 0.1761 0.00477 0.00156 -0.0292 0.8270 0.9025
0.500 0.2076 0.00482 0.00154 -0.0301 0.8079 0.9057
0.750 0.2325 0.00493 0.00154 -0.0294 0.7821 0.9098
1.000 0.2441 0.00506 0.00153 -0.0258 0.7519 0.9163
1.250 0.2642 0.00532 0.00166 -0.0240 0.7187 0.9202
1.500 0.2702 0.00555 0.00177 -0.0190 0.6880 0.9284
1.750 0.2836 0.00586 0.00197 -0.0158 0.6555 0.9336
2.000 0.2955 0.00614 0.00214 -0.0122 0.6236 0.9387
2.250 0.3017 0.00630 0.00220 -0.0075 0.5964 0.9440
2.500 0.3213 0.00657 0.00234 -0.0059 0.5641 0.9457
2.750 0.3402 0.00684 0.00247 -0.0042 0.5285 0.9476
3.000 0.3585 0.00709 0.00260 -0.0024 0.4949 0.9498
3.250 0.3753 0.00730 0.00270 -0.0002 0.4659 0.9527
3.500 0.3849 0.00743 0.00274 0.0036 0.4404 0.9569
3.750 0.4080 0.00771 0.00288 0.0042 0.4035 0.9580
4.000 0.4330 0.00796 0.00303 0.0044 0.3754 0.9591
4.250 0.4572 0.00825 0.00320 0.0048 0.3413 0.9603
4.500 0.4810 0.00853 0.00336 0.0052 0.3109 0.9616
4.750 0.5041 0.00880 0.00352 0.0058 0.2822 0.9631
5.000 0.5257 0.00907 0.00368 0.0068 0.2547 0.9649
5.250 0.5447 0.00931 0.00385 0.0083 0.2302 0.9674
5.500 0.5595 0.00953 0.00399 0.0108 0.2084 0.9705
5.750 0.5850 0.00992 0.00423 0.0107 0.1741 0.9713
6.000 0.6111 0.01027 0.00447 0.0105 0.1475 0.9720
6.250 0.6363 0.01067 0.00475 0.0104 0.1187 0.9727
6.500 0.6627 0.01099 0.00502 0.0102 0.1008 0.9734
6.750 0.6885 0.01136 0.00531 0.0100 0.0816 0.9741
7.000 0.7140 0.01172 0.00560 0.0099 0.0662 0.9749
7.250 0.7388 0.01207 0.00591 0.0099 0.0538 0.9758
7.500 0.7625 0.01245 0.00623 0.0102 0.0416 0.9768
7.750 0.7854 0.01283 0.00658 0.0106 0.0318 0.9781
8.000 0.8072 0.01320 0.00695 0.0113 0.0249 0.9797
8.250 0.8255 0.01352 0.00727 0.0128 0.0207 0.9819
8.500 0.8457 0.01391 0.00765 0.0138 0.0162 0.9832
8.750 0.8708 0.01430 0.00805 0.0136 0.0127 0.9837
9.000 0.8949 0.01476 0.00850 0.0136 0.0099 0.9842
9.250 0.9192 0.01517 0.00893 0.0136 0.0084 0.9848
9.500 0.9429 0.01560 0.00938 0.0136 0.0064 0.9855
9.750 0.9653 0.01610 0.00989 0.0139 0.0047 0.9862
10.000 0.9877 0.01657 0.01041 0.0142 0.0038 0.9870
10.250 1.0088 0.01712 0.01098 0.0147 0.0026 0.9879
10.500 1.0295 0.01768 0.01159 0.0152 0.0020 0.9889
10.750 1.0478 0.01838 0.01234 0.0161 0.0013 0.9901
11.000 1.0669 0.01893 0.01294 0.0169 0.0013 0.9912
11.250 1.0849 0.01951 0.01359 0.0179 0.0012 0.9923
11.500 1.1006 0.02019 0.01435 0.0193 0.0010 0.9935
11.750 1.1182 0.02085 0.01508 0.0202 0.0010 0.9944
12.000 1.1355 0.02166 0.01597 0.0209 0.0010 0.9952
12.250 1.1522 0.02249 0.01689 0.0217 0.0008 0.9961
12.500 1.1680 0.02339 0.01790 0.0226 0.0008 0.9970
12.750 1.1833 0.02427 0.01885 0.0236 0.0007 0.9979
13.000 1.1954 0.02541 0.02009 0.0248 0.0006 0.9987
13.250 1.2088 0.02643 0.02120 0.0259 0.0006 0.9993
13.500 1.2153 0.02803 0.02296 0.0276 0.0005 0.9999
13.750 1.2186 0.02905 0.02406 0.0304 0.0005 1.0000
14.000 1.2171 0.03034 0.02545 0.0338 0.0005 1.0000
14.250 1.2187 0.03146 0.02666 0.0366 0.0004 1.0000
14.500 1.2111 0.03334 0.02868 0.0402 0.0005 1.0000
14.750 1.2127 0.03463 0.03006 0.0425 0.0005 1.0000
15.000 1.2182 0.03569 0.03117 0.0444 0.0004 1.0000
15.250 1.2087 0.03814 0.03379 0.0470 0.0004 1.0000
15.500 1.2081 0.03997 0.03572 0.0487 0.0004 1.0000
15.750 1.1958 0.04314 0.03905 0.0504 0.0004 1.0000
16.000 1.1930 0.04557 0.04158 0.0513 0.0004 1.0000
16.250 1.1946 0.04769 0.04378 0.0519 0.0004 1.0000
16.500 1.1741 0.05264 0.04893 0.0520 0.0004 1.0000
16.750 1.1762 0.05507 0.05142 0.0518 0.0004 1.0000
17.000 1.1510 0.06141 0.05798 0.0503 0.0004 1.0000
17.250 1.1484 0.06488 0.06153 0.0493 0.0004 1.0000
17.500 1.1322 0.07066 0.06745 0.0471 0.0004 1.0000
17.750 1.1117 0.07747 0.07442 0.0442 0.0004 1.0000
18.000 1.0994 0.08314 0.08019 0.0416 0.0003 1.0000
18.250 1.0659 0.09296 0.09019 0.0369 0.0004 1.0000
18.500 1.0193 0.10567 0.10311 0.0309 0.0004 1.0000
18.750 0.9943 0.11447 0.11201 0.0268 0.0004 1.0000
19.000 0.9603 0.12529 0.12296 0.0218 0.0004 1.0000
19.250 0.9272 0.13633 0.13410 0.0168 0.0004 1.0000
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Polar data table (+)
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