MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 500,000 Max Cl/Cd: 92.34 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh84-il-500000.txt Download as CSV file: xf-mh84-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2667 0.08674 0.08398 -0.0196 0.7538 0.0282
-8.250 -0.2598 0.08402 0.08120 -0.0205 0.7400 0.0283
-8.000 -0.4322 0.03226 0.02830 -0.0666 0.7481 0.0177
-7.750 -0.4146 0.02880 0.02448 -0.0685 0.7364 0.0176
-7.500 -0.3933 0.02597 0.02127 -0.0697 0.7244 0.0175
-7.250 -0.3695 0.02370 0.01866 -0.0704 0.7131 0.0174
-7.000 -0.3443 0.02188 0.01651 -0.0708 0.7015 0.0174
-6.750 -0.3178 0.02038 0.01475 -0.0710 0.6900 0.0174
-6.500 -0.2906 0.01928 0.01337 -0.0711 0.6789 0.0176
-6.250 -0.2624 0.01845 0.01230 -0.0711 0.6672 0.0179
-6.000 -0.2351 0.01724 0.01091 -0.0711 0.6565 0.0181
-5.750 -0.2075 0.01626 0.00984 -0.0710 0.6451 0.0184
-5.500 -0.1793 0.01552 0.00900 -0.0709 0.6344 0.0187
-5.250 -0.1510 0.01488 0.00826 -0.0708 0.6233 0.0189
-5.000 -0.1223 0.01430 0.00760 -0.0707 0.6126 0.0193
-4.750 -0.0936 0.01380 0.00699 -0.0706 0.6017 0.0198
-4.500 -0.0646 0.01331 0.00642 -0.0705 0.5911 0.0204
-4.000 -0.0065 0.01236 0.00534 -0.0704 0.5700 0.0223
-3.750 0.0227 0.01206 0.00494 -0.0703 0.5597 0.0238
-3.500 0.0521 0.01166 0.00451 -0.0703 0.5491 0.0259
-3.250 0.0815 0.01135 0.00412 -0.0702 0.5391 0.0296
-3.000 0.1110 0.01100 0.00376 -0.0702 0.5285 0.0370
-2.750 0.1403 0.01061 0.00344 -0.0702 0.5188 0.0597
-2.500 0.1695 0.01035 0.00327 -0.0702 0.5085 0.0906
-2.250 0.1988 0.01020 0.00316 -0.0702 0.4989 0.1144
-2.000 0.2280 0.01009 0.00308 -0.0702 0.4889 0.1364
-1.750 0.2573 0.01001 0.00302 -0.0701 0.4794 0.1581
-1.500 0.2865 0.00997 0.00298 -0.0700 0.4694 0.1795
-1.250 0.3158 0.00992 0.00296 -0.0700 0.4603 0.2017
-1.000 0.3450 0.00990 0.00293 -0.0699 0.4506 0.2219
-0.750 0.3742 0.00988 0.00292 -0.0699 0.4415 0.2420
-0.500 0.4034 0.00988 0.00290 -0.0698 0.4324 0.2608
-0.250 0.4326 0.00986 0.00290 -0.0697 0.4238 0.2802
0.000 0.4617 0.00986 0.00290 -0.0697 0.4145 0.3016
0.250 0.4908 0.00985 0.00291 -0.0696 0.4061 0.3268
0.500 0.5198 0.00984 0.00294 -0.0696 0.3975 0.3576
0.750 0.5487 0.00982 0.00299 -0.0695 0.3895 0.3981
1.000 0.5776 0.00976 0.00305 -0.0695 0.3809 0.4515
1.250 0.6060 0.00972 0.00314 -0.0694 0.3729 0.5205
1.500 0.6343 0.00958 0.00324 -0.0693 0.3650 0.6084
1.750 0.6610 0.00949 0.00337 -0.0688 0.3572 0.7142
2.000 0.6868 0.00896 0.00339 -0.0676 0.3502 1.0000
2.250 0.7157 0.00915 0.00346 -0.0676 0.3423 1.0000
2.500 0.7447 0.00930 0.00355 -0.0676 0.3352 1.0000
2.750 0.7734 0.00948 0.00364 -0.0675 0.3279 1.0000
3.000 0.8020 0.00969 0.00376 -0.0675 0.3210 1.0000
3.250 0.8307 0.00984 0.00387 -0.0674 0.3141 1.0000
3.500 0.8589 0.01008 0.00401 -0.0674 0.3070 1.0000
3.750 0.8875 0.01025 0.00415 -0.0673 0.3011 1.0000
4.000 0.9158 0.01045 0.00429 -0.0672 0.2946 1.0000
4.250 0.9436 0.01072 0.00447 -0.0671 0.2883 1.0000
4.500 0.9720 0.01088 0.00462 -0.0671 0.2825 1.0000
4.750 0.9998 0.01113 0.00480 -0.0670 0.2767 1.0000
5.000 1.0274 0.01139 0.00502 -0.0668 0.2713 1.0000
5.250 1.0554 0.01158 0.00520 -0.0668 0.2659 1.0000
5.500 1.0828 0.01186 0.00541 -0.0666 0.2605 1.0000
5.750 1.1099 0.01216 0.00567 -0.0665 0.2556 1.0000
6.000 1.1376 0.01236 0.00588 -0.0664 0.2512 1.0000
6.250 1.1646 0.01263 0.00612 -0.0662 0.2464 1.0000
6.500 1.1907 0.01303 0.00643 -0.0660 0.2413 1.0000
6.750 1.2181 0.01321 0.00666 -0.0659 0.2376 1.0000
7.000 1.2448 0.01348 0.00692 -0.0657 0.2334 1.0000
7.250 1.2707 0.01384 0.00723 -0.0654 0.2293 1.0000
7.500 1.2963 0.01422 0.00759 -0.0652 0.2254 1.0000
7.750 1.3229 0.01446 0.00787 -0.0650 0.2219 1.0000
8.000 1.3488 0.01476 0.00817 -0.0648 0.2180 1.0000
8.250 1.3736 0.01517 0.00853 -0.0644 0.2142 1.0000
8.500 1.3980 0.01561 0.00896 -0.0641 0.2108 1.0000
8.750 1.4236 0.01588 0.00929 -0.0638 0.2079 1.0000
9.000 1.4484 0.01622 0.00965 -0.0635 0.2047 1.0000
9.250 1.4722 0.01664 0.01006 -0.0630 0.2014 1.0000
9.500 1.4938 0.01725 0.01061 -0.0624 0.1976 1.0000
9.750 1.5181 0.01755 0.01099 -0.0620 0.1952 1.0000
10.000 1.5415 0.01792 0.01141 -0.0616 0.1924 1.0000
10.250 1.5638 0.01836 0.01186 -0.0610 0.1896 1.0000
10.500 1.5843 0.01889 0.01239 -0.0602 0.1868 1.0000
10.750 1.6021 0.01964 0.01311 -0.0592 0.1837 1.0000
11.000 1.6233 0.02003 0.01359 -0.0586 0.1817 1.0000
11.250 1.6429 0.02050 0.01412 -0.0577 0.1792 1.0000
11.500 1.6604 0.02105 0.01471 -0.0567 0.1768 1.0000
11.750 1.6725 0.02172 0.01540 -0.0549 0.1745 1.0000
12.000 1.6811 0.02261 0.01629 -0.0530 0.1723 1.0000
12.250 1.6902 0.02362 0.01733 -0.0514 0.1702 1.0000
12.500 1.7028 0.02443 0.01824 -0.0503 0.1686 1.0000
12.750 1.7145 0.02538 0.01927 -0.0492 0.1666 1.0000
13.000 1.7254 0.02644 0.02040 -0.0483 0.1647 1.0000
13.250 1.7350 0.02767 0.02167 -0.0475 0.1626 1.0000
13.500 1.7426 0.02912 0.02313 -0.0467 0.1607 1.0000
13.750 1.7485 0.03077 0.02477 -0.0458 0.1584 1.0000
14.000 1.7577 0.03220 0.02631 -0.0453 0.1571 1.0000
14.250 1.7663 0.03374 0.02795 -0.0449 0.1556 1.0000
14.500 1.7738 0.03541 0.02971 -0.0446 0.1539 1.0000
14.750 1.7804 0.03721 0.03158 -0.0443 0.1522 1.0000
15.000 1.7858 0.03917 0.03361 -0.0442 0.1505 1.0000
15.250 1.7897 0.04129 0.03575 -0.0441 0.1488 1.0000
15.500 1.7938 0.04337 0.03784 -0.0438 0.1469 1.0000
15.750 1.7980 0.04553 0.04008 -0.0437 0.1455 1.0000
16.000 1.8006 0.04798 0.04265 -0.0440 0.1442 1.0000
16.250 1.8027 0.05049 0.04527 -0.0443 0.1428 1.0000
16.500 1.8046 0.05312 0.04800 -0.0447 0.1412 1.0000
16.750 1.8061 0.05584 0.05079 -0.0452 0.1397 1.0000
17.000 1.8069 0.05866 0.05367 -0.0458 0.1383 1.0000
17.250 1.8089 0.06133 0.05636 -0.0462 0.1367 1.0000
17.500 1.8143 0.06348 0.05851 -0.0463 0.1347 1.0000
17.750 1.8113 0.06712 0.06230 -0.0475 0.1337 1.0000
18.000 1.8082 0.07083 0.06615 -0.0488 0.1323 1.0000
18.250 1.8052 0.07457 0.07000 -0.0501 0.1308 1.0000
18.500 1.8031 0.07826 0.07378 -0.0515 0.1293 1.0000
18.750 1.8015 0.08185 0.07744 -0.0528 0.1278 1.0000
19.000 1.8012 0.08524 0.08086 -0.0541 0.1263 1.0000
19.250 1.8089 0.08720 0.08280 -0.0544 0.1244 1.0000
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Polar data table (+)
Polar graphs
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