MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 100,000 Max Cl/Cd: 45.83 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh102-il-100000-n5.txt Download as CSV file: xf-mh102-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4869 0.14336 0.13769 -0.0250 1.0000 0.0290
-15.750 -0.5754 0.11703 0.11105 -0.0373 1.0000 0.0289
-15.500 -0.5936 0.10917 0.10305 -0.0412 1.0000 0.0292
-15.250 -0.6053 0.10297 0.09671 -0.0442 1.0000 0.0297
-15.000 -0.6168 0.09699 0.09056 -0.0470 1.0000 0.0306
-14.750 -0.6199 0.09288 0.08641 -0.0488 1.0000 0.0314
-14.500 -0.6196 0.08954 0.08306 -0.0502 1.0000 0.0320
-14.250 -0.6234 0.08549 0.07897 -0.0519 1.0000 0.0332
-14.000 -0.6276 0.08150 0.07489 -0.0536 1.0000 0.0343
-13.750 -0.6324 0.07764 0.07096 -0.0551 1.0000 0.0355
-13.500 -0.6356 0.07422 0.06756 -0.0565 1.0000 0.0366
-13.250 -0.6403 0.07063 0.06394 -0.0578 1.0000 0.0378
-13.000 -0.6451 0.06706 0.06031 -0.0590 1.0000 0.0389
-12.750 -0.6527 0.06319 0.05641 -0.0605 1.0000 0.0403
-12.500 -0.6608 0.05935 0.05256 -0.0620 1.0000 0.0413
-12.250 -0.6721 0.05511 0.04829 -0.0637 1.0000 0.0426
-12.000 -0.6837 0.05089 0.04400 -0.0655 1.0000 0.0439
-11.750 -0.6973 0.04655 0.03958 -0.0673 1.0000 0.0452
-11.500 -0.7140 0.04223 0.03521 -0.0691 1.0000 0.0459
-11.250 -0.7311 0.03872 0.03163 -0.0696 1.0000 0.0467
-11.000 -0.7494 0.03621 0.02907 -0.0679 1.0000 0.0476
-10.750 -0.7693 0.03453 0.02733 -0.0639 1.0000 0.0492
-10.500 -0.7827 0.03311 0.02588 -0.0599 1.0000 0.0511
-10.250 -0.7947 0.03177 0.02455 -0.0557 1.0000 0.0536
-10.000 -0.7981 0.03051 0.02324 -0.0528 0.9981 0.0576
-9.750 -0.7721 0.02845 0.02115 -0.0556 0.9849 0.0687
-9.500 -0.7462 0.02669 0.01942 -0.0577 0.9717 0.0848
-9.250 -0.7188 0.02533 0.01813 -0.0595 0.9587 0.1067
-9.000 -0.6878 0.02444 0.01724 -0.0613 0.9469 0.1302
-8.750 -0.6522 0.02386 0.01661 -0.0635 0.9372 0.1508
-8.500 -0.6208 0.02347 0.01611 -0.0646 0.9242 0.1668
-8.250 -0.5885 0.02315 0.01564 -0.0658 0.9118 0.1804
-8.000 -0.5546 0.02284 0.01517 -0.0671 0.9005 0.1931
-7.750 -0.5238 0.02257 0.01465 -0.0679 0.8874 0.2051
-7.500 -0.4945 0.02240 0.01447 -0.0681 0.8736 0.2142
-7.250 -0.4655 0.02208 0.01394 -0.0683 0.8604 0.2236
-7.000 -0.4357 0.02184 0.01361 -0.0686 0.8481 0.2312
-6.750 -0.4099 0.02149 0.01302 -0.0682 0.8335 0.2390
-6.500 -0.3827 0.02121 0.01272 -0.0679 0.8201 0.2447
-6.250 -0.3552 0.02090 0.01224 -0.0676 0.8080 0.2515
-6.000 -0.3291 0.02057 0.01174 -0.0672 0.7947 0.2576
-5.750 -0.3029 0.02031 0.01144 -0.0667 0.7819 0.2632
-5.500 -0.2758 0.02003 0.01097 -0.0664 0.7707 0.2698
-5.250 -0.2500 0.01975 0.01059 -0.0659 0.7580 0.2757
-5.000 -0.2238 0.01952 0.01031 -0.0654 0.7464 0.2816
-4.750 -0.1970 0.01928 0.00990 -0.0650 0.7357 0.2885
-4.500 -0.1714 0.01905 0.00962 -0.0645 0.7236 0.2945
-4.250 -0.1448 0.01886 0.00935 -0.0640 0.7135 0.3013
-4.000 -0.1187 0.01868 0.00902 -0.0636 0.7022 0.3089
-3.750 -0.0926 0.01848 0.00882 -0.0631 0.6921 0.3152
-3.500 -0.0663 0.01833 0.00858 -0.0626 0.6817 0.3234
-3.250 -0.0403 0.01817 0.00838 -0.0621 0.6715 0.3312
-3.000 -0.0139 0.01803 0.00818 -0.0616 0.6621 0.3395
-2.750 0.0122 0.01792 0.00801 -0.0612 0.6523 0.3484
-2.500 0.0385 0.01780 0.00786 -0.0607 0.6434 0.3579
-2.250 0.0645 0.01771 0.00774 -0.0602 0.6338 0.3682
-2.000 0.0908 0.01761 0.00760 -0.0598 0.6252 0.3790
-1.750 0.1167 0.01754 0.00753 -0.0593 0.6165 0.3901
-1.500 0.1430 0.01748 0.00743 -0.0589 0.6082 0.4033
-1.250 0.1690 0.01742 0.00738 -0.0584 0.6003 0.4166
-1.000 0.1948 0.01736 0.00736 -0.0579 0.5917 0.4308
-0.750 0.2213 0.01732 0.00729 -0.0574 0.5848 0.4468
-0.500 0.2467 0.01730 0.00733 -0.0569 0.5765 0.4643
-0.250 0.2729 0.01727 0.00731 -0.0564 0.5697 0.4836
0.000 0.2984 0.01726 0.00737 -0.0558 0.5622 0.5050
0.250 0.3239 0.01724 0.00742 -0.0552 0.5549 0.5290
0.750 0.3751 0.01725 0.00760 -0.0541 0.5414 0.5866
1.000 0.4005 0.01725 0.00768 -0.0533 0.5350 0.6209
1.250 0.4256 0.01726 0.00779 -0.0525 0.5290 0.6586
1.500 0.4494 0.01730 0.00799 -0.0515 0.5219 0.6999
1.750 0.4745 0.01732 0.00811 -0.0505 0.5160 0.7452
2.000 0.5001 0.01738 0.00829 -0.0496 0.5100 0.7920
2.250 0.5283 0.01749 0.00851 -0.0492 0.5031 0.8408
2.500 0.5645 0.01760 0.00862 -0.0504 0.4971 0.8870
2.750 0.6052 0.01779 0.00884 -0.0528 0.4900 0.9277
3.000 0.6486 0.01798 0.00901 -0.0559 0.4829 0.9614
3.250 0.6944 0.01815 0.00907 -0.0595 0.4768 0.9878
3.500 0.7235 0.01842 0.00936 -0.0602 0.4697 1.0000
3.750 0.7436 0.01863 0.00951 -0.0589 0.4640 1.0000
4.000 0.7656 0.01885 0.00961 -0.0579 0.4591 1.0000
4.250 0.7844 0.01915 0.00996 -0.0564 0.4526 1.0000
4.500 0.8058 0.01940 0.01017 -0.0553 0.4467 1.0000
4.750 0.8295 0.01963 0.01029 -0.0546 0.4419 1.0000
5.000 0.8487 0.01998 0.01072 -0.0532 0.4352 1.0000
5.250 0.8705 0.02025 0.01097 -0.0522 0.4292 1.0000
5.500 0.8948 0.02049 0.01112 -0.0515 0.4242 1.0000
5.750 0.9138 0.02087 0.01160 -0.0502 0.4173 1.0000
6.000 0.9357 0.02116 0.01188 -0.0493 0.4112 1.0000
6.250 0.9591 0.02144 0.01210 -0.0485 0.4058 1.0000
6.500 0.9778 0.02185 0.01261 -0.0472 0.3988 1.0000
6.750 0.9998 0.02213 0.01288 -0.0462 0.3927 1.0000
7.000 1.0208 0.02249 0.01325 -0.0452 0.3867 1.0000
7.250 1.0395 0.02290 0.01374 -0.0439 0.3797 1.0000
7.500 1.0615 0.02318 0.01398 -0.0429 0.3737 1.0000
7.750 1.0789 0.02365 0.01455 -0.0415 0.3669 1.0000
8.000 1.0974 0.02404 0.01498 -0.0401 0.3601 1.0000
8.250 1.1177 0.02439 0.01529 -0.0390 0.3541 1.0000
8.500 1.1318 0.02493 0.01597 -0.0372 0.3466 1.0000
8.750 1.1504 0.02530 0.01632 -0.0358 0.3404 1.0000
9.000 1.1638 0.02586 0.01697 -0.0339 0.3333 1.0000
9.250 1.1776 0.02636 0.01753 -0.0320 0.3264 1.0000
9.500 1.1922 0.02682 0.01798 -0.0302 0.3204 1.0000
9.750 1.1989 0.02752 0.01879 -0.0275 0.3132 1.0000
10.000 1.2120 0.02802 0.01927 -0.0256 0.3072 1.0000
10.250 1.2185 0.02887 0.02022 -0.0231 0.3003 1.0000
10.500 1.2269 0.02964 0.02104 -0.0210 0.2936 1.0000
10.750 1.2365 0.03044 0.02185 -0.0192 0.2875 1.0000
11.000 1.2408 0.03158 0.02309 -0.0172 0.2807 1.0000
11.250 1.2514 0.03239 0.02388 -0.0157 0.2748 1.0000
11.500 1.2532 0.03384 0.02545 -0.0139 0.2681 1.0000
11.750 1.2586 0.03511 0.02677 -0.0124 0.2619 1.0000
12.000 1.2658 0.03635 0.02802 -0.0112 0.2561 1.0000
12.250 1.2652 0.03823 0.03002 -0.0099 0.2496 1.0000
12.500 1.2727 0.03953 0.03132 -0.0089 0.2439 1.0000
12.750 1.2726 0.04159 0.03347 -0.0079 0.2381 1.0000
13.000 1.2723 0.04371 0.03568 -0.0071 0.2320 1.0000
13.250 1.2818 0.04499 0.03690 -0.0064 0.2268 1.0000
13.500 1.2739 0.04804 0.04014 -0.0060 0.2209 1.0000
13.750 1.2746 0.05030 0.04246 -0.0057 0.2155 1.0000
14.000 1.2798 0.05214 0.04431 -0.0053 0.2104 1.0000
14.250 1.2701 0.05571 0.04805 -0.0054 0.2049 1.0000
14.500 1.2717 0.05808 0.05045 -0.0054 0.1999 1.0000
14.750 1.2741 0.06042 0.05282 -0.0053 0.1951 1.0000
15.000 1.2620 0.06467 0.05724 -0.0061 0.1898 1.0000
15.250 1.2638 0.06722 0.05983 -0.0064 0.1850 1.0000
15.500 1.2652 0.06989 0.06254 -0.0067 0.1805 1.0000
15.750 1.2487 0.07514 0.06797 -0.0082 0.1756 1.0000
16.000 1.2496 0.07801 0.07088 -0.0088 0.1710 1.0000
16.250 1.2538 0.08046 0.07334 -0.0092 0.1669 1.0000
16.500 1.2283 0.08747 0.08058 -0.0117 0.1620 1.0000
16.750 1.2275 0.09081 0.08397 -0.0127 0.1577 1.0000
17.000 1.2411 0.09189 0.08501 -0.0127 0.1539 1.0000
17.250 1.1965 0.10250 0.09591 -0.0173 0.1490 1.0000
17.500 1.1913 0.10679 0.10027 -0.0189 0.1448 1.0000
17.750 1.2212 0.10507 0.09847 -0.0176 0.1416 1.0000
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Polar data table (+)
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