MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 100,000 Max Cl/Cd: 53.44 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh200-il-100000.txt Download as CSV file: xf-mh200-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 200 12.97%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3314 0.09725 0.09307 -0.0413 1.0000 0.1276
-9.500 -0.3548 0.09540 0.09133 -0.0399 1.0000 0.1317
-9.250 -0.4178 0.09338 0.08949 -0.0415 1.0000 0.1338
-9.000 -0.4885 0.09097 0.08674 -0.0499 1.0000 0.1335
-8.750 -0.4554 0.08803 0.08380 -0.0446 1.0000 0.1372
-8.500 -0.4666 0.08658 0.08244 -0.0410 1.0000 0.1395
-8.250 -0.4913 0.08511 0.08107 -0.0378 1.0000 0.1415
-8.000 -0.5266 0.08337 0.07945 -0.0351 1.0000 0.1430
-7.750 -0.5643 0.08174 0.07790 -0.0321 1.0000 0.1433
-7.500 -0.6126 0.07927 0.07541 -0.0311 1.0000 0.1464
-6.250 -0.6577 0.04897 0.04289 -0.0277 1.0000 0.0643
-6.000 -0.6349 0.04301 0.03622 -0.0277 0.9978 0.0513
-5.750 -0.6086 0.03881 0.03158 -0.0287 0.9949 0.0475
-5.500 -0.5795 0.03509 0.02699 -0.0289 0.9920 0.0436
-5.250 -0.5498 0.03301 0.02439 -0.0291 0.9889 0.0425
-5.000 -0.5197 0.03091 0.02212 -0.0300 0.9858 0.0441
-4.500 -0.4596 0.02820 0.01910 -0.0310 0.9794 0.0505
-4.250 -0.4308 0.02710 0.01785 -0.0310 0.9758 0.0529
-4.000 -0.4016 0.02561 0.01650 -0.0317 0.9726 0.0627
-3.750 -0.3704 0.02436 0.01534 -0.0328 0.9695 0.0830
-3.500 -0.3575 0.02042 0.01425 -0.0315 0.9666 0.5115
-3.250 -0.3457 0.02096 0.01547 -0.0264 0.9617 0.6907
-3.000 -0.3282 0.02226 0.01674 -0.0222 0.9572 0.7621
-2.750 -0.3206 0.02298 0.01739 -0.0167 0.9519 0.7996
-2.500 -0.3082 0.02356 0.01784 -0.0123 0.9468 0.8280
-2.250 -0.2882 0.02418 0.01832 -0.0094 0.9423 0.8531
-2.000 -0.2812 0.02424 0.01827 -0.0048 0.9364 0.8753
-1.750 -0.2605 0.02452 0.01841 -0.0026 0.9312 0.8979
-1.500 -0.2313 0.02485 0.01857 -0.0024 0.9264 0.9184
-1.250 -0.1932 0.02515 0.01867 -0.0042 0.9211 0.9365
-1.000 -0.1277 0.02574 0.01904 -0.0116 0.9174 0.9505
-0.750 -0.0433 0.02640 0.01945 -0.0227 0.9148 0.9610
-0.500 0.0183 0.02671 0.01961 -0.0300 0.9101 0.9715
-0.250 0.0806 0.02691 0.01967 -0.0377 0.9052 0.9795
0.000 0.1450 0.02705 0.01971 -0.0455 0.9012 0.9858
0.250 0.1931 0.02717 0.01975 -0.0507 0.8947 0.9931
0.500 0.2490 0.02720 0.01973 -0.0571 0.8891 0.9992
0.750 0.2770 0.02730 0.01980 -0.0582 0.8815 1.0000
1.000 0.3018 0.02736 0.01984 -0.0586 0.8731 1.0000
1.250 0.3122 0.02753 0.02000 -0.0565 0.8627 1.0000
1.500 0.3573 0.02745 0.01992 -0.0600 0.8569 1.0000
1.750 0.3617 0.02764 0.02012 -0.0567 0.8451 1.0000
2.000 0.3753 0.02777 0.02025 -0.0549 0.8344 1.0000
2.250 0.4245 0.02754 0.02004 -0.0587 0.8283 1.0000
2.500 0.4309 0.02766 0.02018 -0.0554 0.8159 1.0000
2.750 0.4449 0.02769 0.02023 -0.0534 0.8043 1.0000
3.000 0.5114 0.02704 0.01968 -0.0594 0.7995 1.0000
3.250 0.5222 0.02698 0.01965 -0.0565 0.7868 1.0000
3.500 0.5388 0.02681 0.01953 -0.0544 0.7748 1.0000
3.750 0.6189 0.02554 0.01842 -0.0620 0.7708 1.0000
4.000 0.6322 0.02531 0.01825 -0.0592 0.7582 1.0000
4.250 0.6527 0.02489 0.01790 -0.0573 0.7462 1.0000
4.500 0.7229 0.02334 0.01653 -0.0628 0.7411 1.0000
4.750 0.7402 0.02287 0.01614 -0.0603 0.7278 1.0000
5.000 0.7618 0.02226 0.01564 -0.0583 0.7145 1.0000
5.250 0.7886 0.02150 0.01498 -0.0571 0.7006 1.0000
5.500 0.8196 0.02061 0.01420 -0.0565 0.6856 1.0000
5.750 0.8539 0.01963 0.01333 -0.0563 0.6689 1.0000
6.000 0.8700 0.01922 0.01303 -0.0536 0.6457 1.0000
6.250 0.8956 0.01858 0.01246 -0.0523 0.6191 1.0000
6.500 0.9234 0.01799 0.01187 -0.0513 0.5851 1.0000
6.750 0.9481 0.01779 0.01153 -0.0500 0.5414 1.0000
7.000 0.9668 0.01809 0.01163 -0.0480 0.4909 1.0000
7.250 0.9828 0.01872 0.01196 -0.0459 0.4408 1.0000
7.500 0.9956 0.01956 0.01253 -0.0436 0.3943 1.0000
7.750 1.0074 0.02051 0.01321 -0.0412 0.3531 1.0000
8.000 1.0184 0.02149 0.01403 -0.0389 0.3156 1.0000
8.250 1.0285 0.02253 0.01486 -0.0365 0.2829 1.0000
8.500 1.0377 0.02362 0.01577 -0.0340 0.2532 1.0000
8.750 1.0464 0.02478 0.01682 -0.0315 0.2250 1.0000
9.000 1.0550 0.02600 0.01795 -0.0292 0.1984 1.0000
9.250 1.0637 0.02734 0.01920 -0.0270 0.1737 1.0000
9.500 1.0728 0.02881 0.02053 -0.0250 0.1519 1.0000
9.750 1.0832 0.03031 0.02200 -0.0231 0.1324 1.0000
10.000 1.0948 0.03189 0.02349 -0.0215 0.1164 1.0000
10.250 1.1115 0.03364 0.02520 -0.0205 0.1031 1.0000
10.500 1.1279 0.03544 0.02707 -0.0194 0.0918 1.0000
10.750 1.1483 0.03753 0.02928 -0.0189 0.0824 1.0000
11.000 1.1746 0.04000 0.03169 -0.0192 0.0739 1.0000
11.250 1.1823 0.04182 0.03384 -0.0171 0.0682 1.0000
11.500 1.2071 0.04497 0.03700 -0.0175 0.0620 1.0000
11.750 1.2074 0.04712 0.03956 -0.0147 0.0585 1.0000
12.000 1.2127 0.04949 0.04214 -0.0130 0.0548 1.0000
12.250 1.2257 0.05374 0.04646 -0.0126 0.0509 1.0000
12.500 1.2119 0.05622 0.04936 -0.0094 0.0496 1.0000
12.750 1.1988 0.05934 0.05285 -0.0069 0.0483 1.0000
13.000 1.1850 0.06285 0.05670 -0.0051 0.0469 1.0000
13.250 1.1694 0.06693 0.06108 -0.0038 0.0462 1.0000
13.500 1.1504 0.07150 0.06595 -0.0031 0.0459 1.0000
13.750 1.1284 0.07661 0.07135 -0.0032 0.0459 1.0000
14.000 1.1032 0.08242 0.07743 -0.0042 0.0462 1.0000
14.250 1.0757 0.08903 0.08429 -0.0064 0.0468 1.0000
14.500 1.0472 0.09650 0.09197 -0.0098 0.0476 1.0000
14.750 1.0189 0.10487 0.10051 -0.0145 0.0486 1.0000
15.000 0.9920 0.11414 0.10990 -0.0200 0.0498 1.0000
15.250 0.9704 0.12348 0.11930 -0.0255 0.0508 1.0000
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Polar data table (+)
Polar graphs
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