MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 100,000 Max Cl/Cd: 46.4 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh27-il-100000-n5.txt Download as CSV file: xf-mh27-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4349 0.09620 0.09172 -0.0356 1.0000 0.0153
-9.750 -0.4468 0.09091 0.08648 -0.0366 1.0000 0.0151
-9.500 -0.4636 0.08418 0.07980 -0.0385 1.0000 0.0144
-9.250 -0.4942 0.07147 0.06702 -0.0449 1.0000 0.0129
-8.750 -0.6148 0.07281 0.06793 -0.0402 1.0000 0.0127
-8.500 -0.6398 0.07051 0.06557 -0.0353 1.0000 0.0126
-8.250 -0.6628 0.06803 0.06301 -0.0300 1.0000 0.0126
-8.000 -0.6783 0.06542 0.06029 -0.0257 1.0000 0.0125
-7.750 -0.6918 0.06253 0.05728 -0.0213 1.0000 0.0124
-7.500 -0.7053 0.05905 0.05356 -0.0166 1.0000 0.0124
-7.250 -0.7118 0.05634 0.05068 -0.0126 1.0000 0.0122
-7.000 -0.7157 0.05284 0.04687 -0.0088 0.9992 0.0122
-6.750 -0.7087 0.04904 0.04262 -0.0069 0.9958 0.0121
-6.500 -0.6997 0.04544 0.03856 -0.0047 0.9927 0.0121
-6.250 -0.6880 0.04231 0.03497 -0.0026 0.9894 0.0121
-6.000 -0.6721 0.03955 0.03162 -0.0006 0.9863 0.0129
-5.750 -0.6552 0.03704 0.02882 0.0003 0.9838 0.0142
-5.500 -0.6364 0.03506 0.02648 0.0018 0.9807 0.0145
-5.250 -0.6154 0.03353 0.02466 0.0028 0.9776 0.0165
-5.000 -0.5900 0.03164 0.02240 0.0034 0.9751 0.0169
-4.750 -0.5617 0.02980 0.02021 0.0037 0.9731 0.0178
-4.500 -0.5322 0.02834 0.01852 0.0035 0.9713 0.0188
-4.250 -0.5099 0.02718 0.01713 0.0047 0.9678 0.0197
-4.000 -0.4884 0.02589 0.01576 0.0059 0.9643 0.0219
-3.750 -0.4627 0.02522 0.01501 0.0060 0.9610 0.0282
-3.500 -0.4365 0.02434 0.01403 0.0062 0.9584 0.0346
-3.250 -0.4179 0.02342 0.01319 0.0081 0.9538 0.0573
-3.000 -0.3982 0.02213 0.01258 0.0092 0.9498 0.1671
-2.750 -0.2836 0.02113 0.01458 -0.0065 0.9612 0.8529
-2.500 -0.2495 0.02197 0.01516 -0.0070 0.9587 0.8996
-2.250 -0.2004 0.02288 0.01577 -0.0107 0.9579 0.9282
-2.000 -0.1354 0.02372 0.01631 -0.0180 0.9585 0.9522
-1.750 -0.0778 0.02413 0.01648 -0.0243 0.9582 0.9670
-1.500 -0.0323 0.02417 0.01635 -0.0285 0.9556 0.9752
-1.250 0.0103 0.02422 0.01624 -0.0322 0.9524 0.9834
-1.000 0.0590 0.02414 0.01603 -0.0372 0.9498 0.9894
-0.750 0.1066 0.02412 0.01590 -0.0420 0.9474 0.9953
-0.500 0.1552 0.02406 0.01575 -0.0471 0.9453 1.0000
-0.250 0.1776 0.02392 0.01556 -0.0466 0.9376 1.0000
0.000 0.2117 0.02383 0.01543 -0.0485 0.9326 1.0000
0.250 0.2354 0.02368 0.01526 -0.0482 0.9245 1.0000
0.500 0.2698 0.02355 0.01510 -0.0500 0.9192 1.0000
0.750 0.2926 0.02338 0.01494 -0.0494 0.9103 1.0000
1.000 0.3296 0.02318 0.01474 -0.0516 0.9051 1.0000
1.250 0.3506 0.02297 0.01457 -0.0505 0.8948 1.0000
1.500 0.3768 0.02273 0.01436 -0.0504 0.8858 1.0000
1.750 0.4108 0.02241 0.01408 -0.0518 0.8787 1.0000
2.000 0.4318 0.02215 0.01387 -0.0505 0.8671 1.0000
2.250 0.4542 0.02186 0.01364 -0.0495 0.8556 1.0000
2.500 0.4777 0.02154 0.01342 -0.0486 0.8436 1.0000
2.750 0.5012 0.02119 0.01315 -0.0476 0.8311 1.0000
3.000 0.5244 0.02081 0.01285 -0.0465 0.8176 1.0000
3.250 0.5470 0.02042 0.01258 -0.0451 0.8033 1.0000
3.500 0.5723 0.01998 0.01223 -0.0443 0.7874 1.0000
3.750 0.6037 0.01943 0.01178 -0.0445 0.7704 1.0000
4.000 0.6334 0.01897 0.01141 -0.0443 0.7471 1.0000
4.250 0.6801 0.01824 0.01078 -0.0473 0.7169 1.0000
4.500 0.7547 0.01749 0.00999 -0.0558 0.6593 1.0000
4.750 0.8031 0.01745 0.00974 -0.0596 0.5868 1.0000
5.000 0.8269 0.01782 0.00990 -0.0587 0.5228 1.0000
5.250 0.8411 0.01833 0.01018 -0.0560 0.4654 1.0000
5.500 0.8515 0.01890 0.01053 -0.0527 0.4132 1.0000
5.750 0.8600 0.01951 0.01094 -0.0491 0.3654 1.0000
6.000 0.8681 0.02011 0.01138 -0.0454 0.3215 1.0000
6.250 0.8752 0.02076 0.01186 -0.0417 0.2792 1.0000
6.500 0.8819 0.02143 0.01238 -0.0379 0.2409 1.0000
6.750 0.8878 0.02208 0.01291 -0.0340 0.2044 1.0000
7.000 0.8934 0.02276 0.01346 -0.0301 0.1734 1.0000
7.250 0.8986 0.02349 0.01407 -0.0262 0.1446 1.0000
7.500 0.9045 0.02423 0.01479 -0.0224 0.1200 1.0000
7.750 0.9100 0.02503 0.01553 -0.0186 0.0977 1.0000
8.000 0.9149 0.02587 0.01632 -0.0147 0.0814 1.0000
8.250 0.9195 0.02676 0.01720 -0.0108 0.0684 1.0000
8.500 0.9243 0.02765 0.01811 -0.0070 0.0579 1.0000
8.750 0.9270 0.02868 0.01917 -0.0029 0.0518 1.0000
9.000 0.9309 0.02970 0.02032 0.0011 0.0464 1.0000
9.250 0.9318 0.03092 0.02155 0.0052 0.0424 1.0000
9.500 0.9382 0.03195 0.02277 0.0086 0.0380 1.0000
9.750 0.9427 0.03305 0.02396 0.0120 0.0341 1.0000
10.000 0.9447 0.03455 0.02550 0.0156 0.0319 1.0000
10.250 0.9519 0.03614 0.02728 0.0186 0.0295 1.0000
10.500 0.9577 0.03745 0.02880 0.0216 0.0262 1.0000
10.750 0.9612 0.03880 0.03034 0.0247 0.0242 1.0000
11.000 0.9625 0.04071 0.03232 0.0278 0.0224 1.0000
11.250 0.9662 0.04303 0.03485 0.0306 0.0211 1.0000
11.500 0.9663 0.04489 0.03705 0.0339 0.0191 1.0000
11.750 0.9646 0.04686 0.03927 0.0370 0.0179 1.0000
12.000 0.9599 0.04882 0.04143 0.0400 0.0166 1.0000
12.250 0.9532 0.05134 0.04416 0.0430 0.0159 1.0000
12.500 0.9445 0.05390 0.04689 0.0456 0.0153 1.0000
12.750 0.9346 0.05681 0.05000 0.0479 0.0150 1.0000
13.000 0.9219 0.06005 0.05341 0.0497 0.0146 1.0000
13.250 0.9086 0.06357 0.05715 0.0510 0.0146 1.0000
13.500 0.8914 0.06775 0.06152 0.0517 0.0143 1.0000
13.750 0.8754 0.07211 0.06611 0.0516 0.0144 1.0000
14.000 0.8564 0.07721 0.07138 0.0506 0.0143 1.0000
14.250 0.8367 0.08299 0.07736 0.0486 0.0143 1.0000
14.500 0.8169 0.08943 0.08397 0.0456 0.0143 1.0000
14.750 0.7866 0.09941 0.09425 0.0399 0.0152 1.0000
15.000 0.7407 0.11517 0.11020 0.0308 0.0166 1.0000
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Polar data table (+)
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