MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 94 16.03% (mh94-il) Reynolds number: 200,000 Max Cl/Cd: 46.34 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh94-il-200000.txt Download as CSV file: xf-mh94-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 94 16.03%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5403 0.10419 0.10024 -0.0510 1.0000 0.0502
-13.000 -0.8733 0.05757 0.05157 -0.0705 1.0000 0.0286
-12.750 -0.8914 0.05508 0.04894 -0.0679 1.0000 0.0286
-12.500 -0.9079 0.05298 0.04669 -0.0646 1.0000 0.0286
-12.250 -0.9155 0.05089 0.04447 -0.0615 1.0000 0.0285
-12.000 -0.9356 0.04940 0.04283 -0.0566 1.0000 0.0285
-11.750 -0.9547 0.04809 0.04137 -0.0509 1.0000 0.0285
-11.500 -0.9622 0.04638 0.03951 -0.0468 1.0000 0.0285
-11.250 -0.9684 0.04441 0.03736 -0.0429 1.0000 0.0286
-11.000 -0.9606 0.04225 0.03514 -0.0409 1.0000 0.0290
-10.750 -0.9503 0.04072 0.03361 -0.0389 1.0000 0.0294
-10.500 -0.9489 0.03895 0.03164 -0.0355 1.0000 0.0293
-10.250 -0.9437 0.03732 0.02982 -0.0326 1.0000 0.0293
-10.000 -0.9335 0.03583 0.02824 -0.0303 1.0000 0.0296
-9.750 -0.9232 0.03438 0.02664 -0.0278 1.0000 0.0296
-9.500 -0.9109 0.03311 0.02530 -0.0257 1.0000 0.0298
-9.250 -0.8983 0.03194 0.02406 -0.0235 1.0000 0.0303
-9.000 -0.8855 0.03082 0.02286 -0.0213 1.0000 0.0307
-8.750 -0.8727 0.02976 0.02174 -0.0191 1.0000 0.0312
-8.500 -0.8600 0.02877 0.02067 -0.0168 1.0000 0.0318
-8.250 -0.8478 0.02787 0.01966 -0.0145 1.0000 0.0325
-8.000 -0.8362 0.02680 0.01863 -0.0122 1.0000 0.0333
-7.750 -0.8255 0.02593 0.01782 -0.0098 1.0000 0.0343
-7.500 -0.8144 0.02513 0.01702 -0.0074 1.0000 0.0355
-7.250 -0.7978 0.02439 0.01620 -0.0060 0.9992 0.0372
-7.000 -0.7661 0.02349 0.01540 -0.0079 0.9948 0.0404
-6.750 -0.7360 0.02259 0.01451 -0.0093 0.9899 0.0441
-6.500 -0.7051 0.02175 0.01372 -0.0109 0.9848 0.0516
-6.250 -0.6759 0.02080 0.01283 -0.0121 0.9797 0.0631
-6.000 -0.6501 0.01938 0.01173 -0.0130 0.9737 0.1023
-5.750 -0.6265 0.01754 0.01083 -0.0142 0.9686 0.2458
-5.500 -0.6008 0.01673 0.01046 -0.0147 0.9618 0.3366
-5.250 -0.5644 0.01642 0.01042 -0.0168 0.9578 0.4030
-5.000 -0.5378 0.01620 0.01032 -0.0167 0.9505 0.4458
-4.750 -0.5021 0.01615 0.01034 -0.0183 0.9455 0.4823
-4.500 -0.4605 0.01620 0.01042 -0.0209 0.9425 0.5124
-4.250 -0.4372 0.01611 0.01031 -0.0199 0.9333 0.5345
-4.000 -0.3983 0.01615 0.01044 -0.0218 0.9293 0.5593
-3.750 -0.3692 0.01619 0.01050 -0.0218 0.9222 0.5797
-3.500 -0.3344 0.01615 0.01045 -0.0228 0.9162 0.5961
-3.250 -0.2920 0.01606 0.01030 -0.0254 0.9129 0.6108
-3.000 -0.2664 0.01600 0.01029 -0.0247 0.9041 0.6211
-2.750 -0.2275 0.01583 0.01009 -0.0265 0.8993 0.6330
-2.500 -0.1840 0.01565 0.00989 -0.0291 0.8963 0.6450
-2.250 -0.1591 0.01556 0.00983 -0.0282 0.8866 0.6545
-2.000 -0.1183 0.01533 0.00955 -0.0303 0.8822 0.6666
-1.750 -0.0730 0.01505 0.00932 -0.0330 0.8797 0.6757
-1.500 -0.0469 0.01489 0.00911 -0.0324 0.8697 0.6865
-1.250 -0.0042 0.01455 0.00883 -0.0345 0.8657 0.6943
-1.000 0.0439 0.01417 0.00841 -0.0379 0.8628 0.7048
-0.750 0.0727 0.01395 0.00824 -0.0374 0.8528 0.7120
-0.500 0.1151 0.01359 0.00788 -0.0396 0.8468 0.7210
-0.250 0.1494 0.01331 0.00760 -0.0403 0.8373 0.7291
0.000 0.1879 0.01305 0.00735 -0.0417 0.8283 0.7367
0.250 0.2185 0.01285 0.00711 -0.0418 0.8154 0.7461
0.500 0.2542 0.01266 0.00695 -0.0426 0.8036 0.7525
0.750 0.2885 0.01251 0.00676 -0.0434 0.7898 0.7610
1.000 0.3167 0.01242 0.00664 -0.0430 0.7728 0.7686
1.250 0.3449 0.01238 0.00659 -0.0424 0.7549 0.7759
1.500 0.3733 0.01234 0.00646 -0.0422 0.7356 0.7851
1.750 0.3994 0.01236 0.00644 -0.0412 0.7145 0.7913
2.000 0.4227 0.01240 0.00642 -0.0399 0.6904 0.8000
2.250 0.4459 0.01244 0.00638 -0.0386 0.6645 0.8075
2.500 0.4680 0.01255 0.00638 -0.0370 0.6381 0.8151
2.750 0.4890 0.01264 0.00637 -0.0354 0.6102 0.8242
3.000 0.5087 0.01279 0.00643 -0.0333 0.5835 0.8312
3.250 0.5284 0.01292 0.00646 -0.0316 0.5551 0.8411
3.500 0.5457 0.01310 0.00654 -0.0291 0.5279 0.8483
3.750 0.5635 0.01327 0.00661 -0.0270 0.4993 0.8582
4.000 0.5791 0.01347 0.00670 -0.0243 0.4723 0.8664
4.250 0.5956 0.01367 0.00681 -0.0221 0.4445 0.8770
4.500 0.6093 0.01388 0.00693 -0.0190 0.4188 0.8861
4.750 0.6240 0.01409 0.00705 -0.0164 0.3933 0.8972
5.000 0.6371 0.01430 0.00718 -0.0134 0.3691 0.9086
5.250 0.6496 0.01453 0.00731 -0.0104 0.3459 0.9206
5.500 0.6632 0.01476 0.00746 -0.0076 0.3242 0.9339
5.750 0.6818 0.01505 0.00768 -0.0060 0.3013 0.9475
6.000 0.7074 0.01550 0.00802 -0.0060 0.2769 0.9602
6.250 0.7387 0.01609 0.00848 -0.0073 0.2519 0.9716
6.500 0.7744 0.01674 0.00900 -0.0096 0.2268 0.9814
6.750 0.8118 0.01752 0.00961 -0.0125 0.2050 0.9898
7.000 0.8426 0.01819 0.01016 -0.0141 0.1887 1.0000
7.250 0.8393 0.01826 0.01023 -0.0092 0.1816 1.0000
7.500 0.8529 0.01881 0.01064 -0.0074 0.1728 1.0000
7.750 0.8722 0.01931 0.01114 -0.0065 0.1646 1.0000
8.000 0.8905 0.01999 0.01170 -0.0054 0.1580 1.0000
8.250 0.9113 0.02059 0.01231 -0.0047 0.1524 1.0000
8.500 0.9311 0.02117 0.01287 -0.0038 0.1472 1.0000
8.750 0.9526 0.02207 0.01361 -0.0033 0.1423 1.0000
9.000 0.9727 0.02260 0.01424 -0.0024 0.1387 1.0000
9.250 0.9930 0.02323 0.01488 -0.0016 0.1350 1.0000
9.500 1.0140 0.02394 0.01556 -0.0010 0.1318 1.0000
9.750 1.0419 0.02501 0.01652 -0.0015 0.1286 1.0000
10.000 1.0605 0.02566 0.01730 -0.0004 0.1262 1.0000
10.250 1.0802 0.02638 0.01809 0.0004 0.1237 1.0000
10.500 1.1002 0.02712 0.01885 0.0012 0.1211 1.0000
10.750 1.1226 0.02794 0.01964 0.0015 0.1188 1.0000
11.000 1.1569 0.02940 0.02102 -0.0002 0.1162 1.0000
11.250 1.1724 0.03021 0.02198 0.0013 0.1149 1.0000
11.500 1.1888 0.03111 0.02303 0.0025 0.1132 1.0000
11.750 1.2047 0.03205 0.02408 0.0037 0.1115 1.0000
12.000 1.2208 0.03300 0.02511 0.0048 0.1097 1.0000
12.250 1.2390 0.03400 0.02615 0.0056 0.1081 1.0000
12.500 1.2604 0.03511 0.02727 0.0059 0.1066 1.0000
12.750 1.2916 0.03690 0.02904 0.0045 0.1049 1.0000
13.000 1.3020 0.03843 0.03075 0.0061 0.1038 1.0000
13.250 1.3056 0.03968 0.03221 0.0086 0.1029 1.0000
13.500 1.3093 0.04112 0.03384 0.0108 0.1018 1.0000
13.750 1.3129 0.04263 0.03553 0.0128 0.1007 1.0000
14.000 1.3170 0.04429 0.03735 0.0146 0.0996 1.0000
14.250 1.3213 0.04604 0.03925 0.0162 0.0987 1.0000
14.500 1.3244 0.04785 0.04120 0.0177 0.0977 1.0000
14.750 1.3270 0.04967 0.04314 0.0191 0.0968 1.0000
15.000 1.3309 0.05155 0.04511 0.0201 0.0959 1.0000
15.250 1.3436 0.05329 0.04686 0.0205 0.0947 1.0000
15.500 1.3510 0.05668 0.05033 0.0207 0.0936 1.0000
15.750 1.3294 0.05986 0.05378 0.0225 0.0933 1.0000
16.000 1.3033 0.06381 0.05799 0.0236 0.0931 1.0000
16.250 1.2723 0.06871 0.06317 0.0237 0.0929 1.0000
16.500 1.2338 0.07503 0.06977 0.0225 0.0928 1.0000
16.750 1.1805 0.08404 0.07908 0.0191 0.0928 1.0000
17.000 1.0868 0.10099 0.09640 0.0099 0.0933 1.0000
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Polar data table (+)
Polar graphs
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