MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 500,000 Max Cl/Cd: 91.04 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh102-il-500000-n5.txt Download as CSV file: xf-mh102-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 102 16.99%
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7970 0.08623 0.08194 -0.0486 1.0000 0.0083
-16.000 -0.8066 0.08138 0.07702 -0.0509 1.0000 0.0083
-15.750 -0.8167 0.07653 0.07210 -0.0533 1.0000 0.0083
-15.500 -0.8314 0.07124 0.06673 -0.0558 1.0000 0.0084
-15.250 -0.8477 0.06594 0.06134 -0.0584 1.0000 0.0083
-15.000 -0.8671 0.06028 0.05559 -0.0611 1.0000 0.0084
-14.750 -0.8844 0.05496 0.05017 -0.0637 1.0000 0.0086
-14.500 -0.9001 0.04985 0.04496 -0.0662 1.0000 0.0084
-14.250 -0.9160 0.04467 0.03966 -0.0688 1.0000 0.0086
-14.000 -0.9286 0.03984 0.03472 -0.0714 1.0000 0.0087
-13.750 -0.9404 0.03522 0.02996 -0.0740 1.0000 0.0087
-13.500 -0.9472 0.03168 0.02631 -0.0757 1.0000 0.0088
-13.250 -0.9527 0.02895 0.02348 -0.0761 1.0000 0.0090
-13.000 -0.9572 0.02698 0.02141 -0.0751 1.0000 0.0090
-12.750 -0.9631 0.02552 0.01987 -0.0726 1.0000 0.0093
-12.500 -0.9705 0.02453 0.01882 -0.0687 1.0000 0.0094
-12.250 -0.9678 0.02363 0.01785 -0.0659 0.9983 0.0097
-12.000 -0.9431 0.02242 0.01658 -0.0672 0.9894 0.0101
-11.500 -0.8902 0.02050 0.01453 -0.0694 0.9675 0.0114
-11.000 -0.8211 0.01872 0.01262 -0.0741 0.9345 0.0130
-10.750 -0.7851 0.01795 0.01174 -0.0765 0.9119 0.0146
-10.250 -0.7390 0.01685 0.01040 -0.0756 0.8617 0.0177
-10.000 -0.7189 0.01641 0.00985 -0.0744 0.8409 0.0197
-9.750 -0.6986 0.01597 0.00932 -0.0732 0.8225 0.0223
-9.500 -0.6777 0.01555 0.00882 -0.0722 0.8058 0.0253
-9.250 -0.6563 0.01515 0.00833 -0.0711 0.7902 0.0291
-9.000 -0.6346 0.01472 0.00785 -0.0702 0.7754 0.0346
-8.750 -0.6125 0.01428 0.00738 -0.0693 0.7617 0.0414
-8.250 -0.5683 0.01335 0.00643 -0.0675 0.7362 0.0646
-8.000 -0.5461 0.01282 0.00596 -0.0667 0.7248 0.0834
-7.750 -0.5231 0.01237 0.00557 -0.0660 0.7134 0.1038
-7.500 -0.4988 0.01204 0.00526 -0.0654 0.7015 0.1220
-7.250 -0.4738 0.01177 0.00501 -0.0649 0.6904 0.1370
-7.000 -0.4481 0.01158 0.00480 -0.0644 0.6798 0.1495
-6.750 -0.4216 0.01142 0.00461 -0.0640 0.6698 0.1607
-6.500 -0.3955 0.01128 0.00444 -0.0636 0.6593 0.1703
-6.250 -0.3686 0.01115 0.00428 -0.0633 0.6484 0.1771
-6.000 -0.3420 0.01105 0.00413 -0.0630 0.6384 0.1858
-5.750 -0.3151 0.01094 0.00399 -0.0627 0.6285 0.1937
-5.500 -0.2881 0.01084 0.00386 -0.0624 0.6196 0.2000
-5.250 -0.2606 0.01078 0.00372 -0.0621 0.6099 0.2047
-5.000 -0.2338 0.01068 0.00358 -0.0618 0.6006 0.2094
-4.750 -0.2066 0.01060 0.00345 -0.0615 0.5907 0.2144
-4.500 -0.1792 0.01055 0.00334 -0.0612 0.5819 0.2190
-4.250 -0.1518 0.01049 0.00322 -0.0610 0.5731 0.2231
-4.000 -0.1247 0.01041 0.00312 -0.0607 0.5653 0.2283
-3.750 -0.0971 0.01035 0.00303 -0.0605 0.5567 0.2333
-3.500 -0.0697 0.01033 0.00294 -0.0603 0.5483 0.2381
-3.250 -0.0423 0.01026 0.00285 -0.0600 0.5397 0.2435
-2.750 0.0128 0.01019 0.00272 -0.0596 0.5248 0.2545
-2.500 0.0402 0.01015 0.00266 -0.0594 0.5174 0.2608
-2.250 0.0676 0.01012 0.00261 -0.0592 0.5104 0.2676
-2.000 0.0954 0.01011 0.00256 -0.0590 0.5028 0.2733
-1.500 0.1503 0.01006 0.00250 -0.0586 0.4897 0.2888
-1.250 0.1777 0.01004 0.00248 -0.0584 0.4830 0.2967
-1.000 0.2050 0.01005 0.00247 -0.0581 0.4767 0.3051
-0.750 0.2327 0.01004 0.00246 -0.0580 0.4705 0.3131
-0.500 0.2601 0.01003 0.00246 -0.0578 0.4642 0.3232
-0.250 0.2872 0.01004 0.00247 -0.0575 0.4585 0.3337
0.000 0.3150 0.01004 0.00248 -0.0574 0.4526 0.3446
0.250 0.3422 0.01004 0.00250 -0.0572 0.4467 0.3555
0.500 0.3692 0.01008 0.00253 -0.0569 0.4412 0.3668
0.750 0.3968 0.01007 0.00256 -0.0567 0.4361 0.3809
1.000 0.4239 0.01007 0.00260 -0.0565 0.4306 0.3955
1.250 0.4506 0.01011 0.00265 -0.0562 0.4252 0.4100
1.500 0.4780 0.01012 0.00270 -0.0560 0.4206 0.4252
1.750 0.5051 0.01012 0.00276 -0.0558 0.4154 0.4431
2.000 0.5316 0.01014 0.00282 -0.0555 0.4104 0.4636
2.250 0.5581 0.01017 0.00290 -0.0552 0.4057 0.4855
2.500 0.5851 0.01016 0.00298 -0.0549 0.4012 0.5089
3.000 0.6371 0.01019 0.00317 -0.0541 0.3913 0.5695
3.250 0.6631 0.01018 0.00328 -0.0537 0.3871 0.6041
3.500 0.6889 0.01016 0.00339 -0.0533 0.3822 0.6413
3.750 0.7139 0.01017 0.00351 -0.0526 0.3771 0.6817
4.000 0.7380 0.01020 0.00365 -0.0518 0.3724 0.7242
4.250 0.7628 0.01016 0.00378 -0.0511 0.3677 0.7691
4.500 0.7864 0.01016 0.00392 -0.0501 0.3625 0.8155
4.750 0.8094 0.01020 0.00408 -0.0489 0.3572 0.8639
5.000 0.8372 0.01025 0.00425 -0.0487 0.3521 0.9147
5.250 0.8800 0.01040 0.00443 -0.0518 0.3454 0.9555
5.500 0.9216 0.01062 0.00462 -0.0548 0.3384 0.9825
5.750 0.9597 0.01079 0.00479 -0.0570 0.3318 1.0000
6.000 0.9815 0.01097 0.00495 -0.0559 0.3251 1.0000
6.250 1.0038 0.01116 0.00511 -0.0549 0.3190 1.0000
6.500 1.0264 0.01134 0.00529 -0.0539 0.3120 1.0000
6.750 1.0479 0.01157 0.00548 -0.0528 0.3052 1.0000
7.000 1.0706 0.01176 0.00568 -0.0519 0.2980 1.0000
7.250 1.0916 0.01203 0.00591 -0.0507 0.2906 1.0000
7.500 1.1137 0.01225 0.00613 -0.0497 0.2833 1.0000
7.750 1.1338 0.01255 0.00639 -0.0484 0.2752 1.0000
8.000 1.1549 0.01281 0.00664 -0.0473 0.2679 1.0000
8.250 1.1741 0.01313 0.00694 -0.0459 0.2601 1.0000
8.500 1.1938 0.01343 0.00722 -0.0446 0.2534 1.0000
8.750 1.2113 0.01376 0.00754 -0.0429 0.2459 1.0000
9.000 1.2271 0.01410 0.00787 -0.0409 0.2395 1.0000
9.250 1.2429 0.01444 0.00821 -0.0389 0.2327 1.0000
9.500 1.2565 0.01488 0.00863 -0.0367 0.2265 1.0000
9.750 1.2727 0.01524 0.00901 -0.0350 0.2201 1.0000
10.000 1.2861 0.01573 0.00949 -0.0329 0.2138 1.0000
10.250 1.3007 0.01620 0.00996 -0.0311 0.2078 1.0000
10.500 1.3143 0.01672 0.01050 -0.0292 0.2016 1.0000
10.750 1.3259 0.01735 0.01113 -0.0272 0.1962 1.0000
11.000 1.3399 0.01792 0.01172 -0.0256 0.1906 1.0000
11.250 1.3508 0.01865 0.01246 -0.0237 0.1850 1.0000
11.500 1.3618 0.01943 0.01326 -0.0221 0.1798 1.0000
11.750 1.3732 0.02024 0.01409 -0.0205 0.1742 1.0000
12.000 1.3808 0.02130 0.01515 -0.0188 0.1688 1.0000
12.250 1.3919 0.02222 0.01611 -0.0175 0.1642 1.0000
12.500 1.4005 0.02335 0.01726 -0.0161 0.1589 1.0000
12.750 1.4064 0.02472 0.01865 -0.0148 0.1542 1.0000
13.000 1.4160 0.02591 0.01989 -0.0138 0.1499 1.0000
13.250 1.4223 0.02738 0.02138 -0.0127 0.1451 1.0000
13.500 1.4261 0.02912 0.02315 -0.0117 0.1409 1.0000
13.750 1.4333 0.03064 0.02473 -0.0110 0.1369 1.0000
14.000 1.4370 0.03251 0.02663 -0.0102 0.1324 1.0000
14.500 1.4431 0.03654 0.03076 -0.0091 0.1252 1.0000
14.750 1.4447 0.03878 0.03304 -0.0087 0.1211 1.0000
15.000 1.4427 0.04143 0.03572 -0.0083 0.1173 1.0000
15.250 1.4448 0.04374 0.03810 -0.0081 0.1143 1.0000
15.500 1.4450 0.04632 0.04073 -0.0081 0.1104 1.0000
15.750 1.4419 0.04930 0.04375 -0.0081 0.1070 1.0000
16.000 1.4401 0.05221 0.04672 -0.0083 0.1041 1.0000
16.250 1.4393 0.05508 0.04965 -0.0085 0.1004 1.0000
16.500 1.4358 0.05832 0.05293 -0.0088 0.0972 1.0000
16.750 1.4305 0.06183 0.05649 -0.0094 0.0944 1.0000
17.000 1.4292 0.06493 0.05966 -0.0099 0.0914 1.0000
17.250 1.4239 0.06856 0.06334 -0.0106 0.0879 1.0000
17.500 1.4176 0.07239 0.06722 -0.0114 0.0854 1.0000
17.750 1.4160 0.07566 0.07056 -0.0121 0.0829 1.0000
18.000 1.4121 0.07930 0.07426 -0.0130 0.0803 1.0000
18.250 1.4055 0.08335 0.07836 -0.0142 0.0775 1.0000
18.500 1.4003 0.08725 0.08231 -0.0153 0.0751 1.0000
18.750 1.3968 0.09099 0.08612 -0.0164 0.0726 1.0000
19.000 1.3921 0.09492 0.09012 -0.0177 0.0703 1.0000
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Polar data table (+)
Polar graphs
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