MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.97 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh200-il-1000000.txt Download as CSV file: xf-mh200-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4816 0.01881 0.01393 -0.0840 0.8572 0.0064
-7.750 -0.4617 0.01731 0.01220 -0.0829 0.8505 0.0063
-7.500 -0.4404 0.01613 0.01086 -0.0820 0.8442 0.0063
-7.250 -0.4187 0.01507 0.00965 -0.0811 0.8386 0.0062
-7.000 -0.3969 0.01410 0.00857 -0.0802 0.8330 0.0062
-6.750 -0.3736 0.01354 0.00794 -0.0797 0.8283 0.0064
-6.500 -0.3497 0.01303 0.00736 -0.0793 0.8239 0.0067
-6.250 -0.3263 0.01240 0.00667 -0.0787 0.8195 0.0068
-6.000 -0.3026 0.01185 0.00604 -0.0782 0.8154 0.0070
-5.750 -0.2789 0.01126 0.00536 -0.0776 0.8115 0.0070
-5.500 -0.2545 0.01073 0.00477 -0.0772 0.8078 0.0071
-5.250 -0.2292 0.01030 0.00427 -0.0768 0.8042 0.0072
-5.000 -0.2034 0.00994 0.00383 -0.0766 0.8008 0.0075
-4.750 -0.1770 0.00965 0.00347 -0.0765 0.7975 0.0079
-4.500 -0.1509 0.00924 0.00302 -0.0762 0.7944 0.0104
-4.250 -0.1262 0.00861 0.00259 -0.0759 0.7910 0.0539
-4.000 -0.1014 0.00804 0.00231 -0.0758 0.7877 0.1281
-3.750 -0.0755 0.00763 0.00211 -0.0759 0.7845 0.1953
-3.500 -0.0500 0.00709 0.00193 -0.0760 0.7815 0.2899
-3.250 -0.0254 0.00636 0.00173 -0.0760 0.7782 0.4318
-3.000 0.0010 0.00590 0.00159 -0.0761 0.7751 0.5304
-2.750 0.0282 0.00563 0.00153 -0.0762 0.7722 0.6048
-2.500 0.0566 0.00557 0.00152 -0.0764 0.7691 0.6418
-2.250 0.0851 0.00552 0.00151 -0.0766 0.7663 0.6663
-2.000 0.1138 0.00551 0.00150 -0.0768 0.7630 0.6830
-1.750 0.1425 0.00551 0.00150 -0.0770 0.7596 0.6965
-1.500 0.1713 0.00555 0.00150 -0.0772 0.7559 0.7072
-1.250 0.2000 0.00557 0.00150 -0.0774 0.7522 0.7160
-1.000 0.2287 0.00558 0.00151 -0.0776 0.7482 0.7236
-0.750 0.2575 0.00560 0.00151 -0.0778 0.7444 0.7304
-0.250 0.3150 0.00567 0.00154 -0.0783 0.7364 0.7426
0.000 0.3433 0.00566 0.00155 -0.0784 0.7318 0.7475
0.250 0.3718 0.00571 0.00156 -0.0785 0.7268 0.7529
0.500 0.4003 0.00573 0.00158 -0.0787 0.7216 0.7585
0.750 0.4284 0.00573 0.00161 -0.0788 0.7162 0.7636
1.000 0.4568 0.00579 0.00164 -0.0789 0.7111 0.7682
1.500 0.5134 0.00580 0.00167 -0.0792 0.6994 0.7755
1.750 0.5416 0.00582 0.00171 -0.0793 0.6932 0.7788
2.000 0.5697 0.00585 0.00174 -0.0794 0.6858 0.7822
2.250 0.5980 0.00589 0.00177 -0.0796 0.6778 0.7856
2.500 0.6255 0.00592 0.00180 -0.0796 0.6686 0.7889
2.750 0.6530 0.00595 0.00185 -0.0795 0.6569 0.7923
3.000 0.6801 0.00601 0.00191 -0.0794 0.6422 0.7960
3.250 0.7068 0.00611 0.00196 -0.0793 0.6230 0.7994
3.500 0.7322 0.00626 0.00203 -0.0789 0.5960 0.8023
3.750 0.7559 0.00649 0.00215 -0.0782 0.5604 0.8051
4.000 0.7789 0.00680 0.00232 -0.0773 0.5227 0.8079
4.250 0.8015 0.00715 0.00252 -0.0765 0.4826 0.8110
4.500 0.8238 0.00754 0.00274 -0.0756 0.4409 0.8139
4.750 0.8453 0.00795 0.00298 -0.0747 0.3972 0.8167
5.000 0.8672 0.00832 0.00321 -0.0737 0.3593 0.8196
5.250 0.8888 0.00873 0.00347 -0.0728 0.3233 0.8226
5.500 0.9102 0.00915 0.00375 -0.0718 0.2864 0.8258
5.750 0.9320 0.00955 0.00402 -0.0710 0.2565 0.8289
6.000 0.9536 0.00992 0.00429 -0.0700 0.2293 0.8320
6.250 0.9744 0.01032 0.00458 -0.0690 0.2022 0.8352
6.500 0.9958 0.01069 0.00488 -0.0680 0.1811 0.8387
6.750 1.0176 0.01104 0.00518 -0.0672 0.1628 0.8424
7.000 1.0384 0.01142 0.00549 -0.0661 0.1442 0.8459
7.250 1.0582 0.01182 0.00583 -0.0649 0.1260 0.8496
7.500 1.0782 0.01221 0.00617 -0.0637 0.1101 0.8538
7.750 1.0977 0.01264 0.00654 -0.0625 0.0950 0.8583
8.000 1.1149 0.01308 0.00695 -0.0608 0.0797 0.8630
8.250 1.1293 0.01357 0.00737 -0.0586 0.0646 0.8685
8.500 1.1442 0.01406 0.00782 -0.0565 0.0528 0.8746
8.750 1.1585 0.01455 0.00829 -0.0544 0.0430 0.8816
9.000 1.1738 0.01502 0.00876 -0.0525 0.0357 0.8893
9.250 1.1881 0.01550 0.00926 -0.0504 0.0301 0.8988
9.500 1.2024 0.01595 0.00975 -0.0483 0.0265 0.9108
10.000 1.2305 0.01678 0.01076 -0.0442 0.0205 1.0000
10.250 1.2466 0.01741 0.01139 -0.0429 0.0180 1.0000
10.500 1.2624 0.01805 0.01205 -0.0416 0.0160 1.0000
10.750 1.2789 0.01863 0.01266 -0.0403 0.0146 1.0000
11.000 1.2936 0.01934 0.01337 -0.0389 0.0130 1.0000
11.250 1.3071 0.02012 0.01419 -0.0374 0.0114 1.0000
11.500 1.3226 0.02078 0.01489 -0.0362 0.0102 1.0000
11.750 1.3355 0.02162 0.01576 -0.0348 0.0089 1.0000
12.000 1.3482 0.02250 0.01667 -0.0334 0.0073 1.0000
12.250 1.3584 0.02358 0.01775 -0.0318 0.0050 1.0000
12.500 1.3691 0.02465 0.01887 -0.0303 0.0043 1.0000
12.750 1.3762 0.02602 0.02029 -0.0285 0.0030 1.0000
13.000 1.3848 0.02730 0.02164 -0.0270 0.0026 1.0000
13.250 1.3874 0.02911 0.02355 -0.0251 0.0019 1.0000
13.500 1.3949 0.03055 0.02508 -0.0238 0.0017 1.0000
13.750 1.4020 0.03206 0.02668 -0.0225 0.0016 1.0000
14.000 1.4075 0.03374 0.02846 -0.0213 0.0015 1.0000
14.250 1.4118 0.03558 0.03040 -0.0201 0.0014 1.0000
14.500 1.4107 0.03799 0.03292 -0.0188 0.0012 1.0000
14.750 1.4183 0.03961 0.03462 -0.0181 0.0013 1.0000
15.000 1.4103 0.04288 0.03805 -0.0170 0.0012 1.0000
15.250 1.4117 0.04530 0.04057 -0.0164 0.0012 1.0000
15.500 1.4063 0.04859 0.04399 -0.0160 0.0011 1.0000
15.750 1.3908 0.05328 0.04887 -0.0159 0.0011 1.0000
16.000 1.3911 0.05627 0.05196 -0.0161 0.0011 1.0000
16.250 1.3678 0.06262 0.05854 -0.0172 0.0010 1.0000
16.500 1.3575 0.06760 0.06365 -0.0186 0.0010 1.0000
16.750 1.3512 0.07219 0.06836 -0.0202 0.0010 1.0000
17.000 1.3336 0.07892 0.07526 -0.0229 0.0010 1.0000
17.250 1.3202 0.08528 0.08178 -0.0257 0.0010 1.0000
17.500 1.3016 0.09288 0.08954 -0.0294 0.0010 1.0000
17.750 1.2852 0.10043 0.09723 -0.0333 0.0010 1.0000
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Polar data table (+)
Polar graphs
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