MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 500,000 Max Cl/Cd: 85.1 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh201-il-500000-n5.txt Download as CSV file: xf-mh201-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 201 13.08%
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5588 0.06106 0.05858 -0.0651 0.9994 0.0055
-10.750 -0.5727 0.05105 0.04833 -0.0772 0.9959 0.0053
-10.500 -0.5897 0.04347 0.04045 -0.0848 0.9902 0.0052
-10.250 -0.5957 0.03802 0.03461 -0.0897 0.9840 0.0054
-10.000 -0.6016 0.03400 0.03027 -0.0908 0.9732 0.0053
-9.750 -0.5945 0.03116 0.02711 -0.0910 0.9638 0.0054
-9.500 -0.5800 0.02815 0.02373 -0.0920 0.9583 0.0054
-9.250 -0.5665 0.02605 0.02137 -0.0915 0.9496 0.0054
-9.000 -0.5427 0.02385 0.01887 -0.0927 0.9460 0.0054
-8.750 -0.5210 0.02214 0.01691 -0.0929 0.9392 0.0054
-8.500 -0.4920 0.02057 0.01512 -0.0944 0.9350 0.0055
-8.250 -0.4601 0.01911 0.01345 -0.0962 0.9317 0.0055
-8.000 -0.4322 0.01802 0.01221 -0.0970 0.9256 0.0055
-7.750 -0.4012 0.01698 0.01104 -0.0984 0.9203 0.0056
-7.500 -0.3697 0.01601 0.00994 -0.0999 0.9149 0.0056
-7.250 -0.3418 0.01514 0.00897 -0.1005 0.9070 0.0057
-7.000 -0.3124 0.01430 0.00803 -0.1015 0.9004 0.0058
-6.750 -0.2867 0.01361 0.00726 -0.1016 0.8921 0.0060
-6.500 -0.2582 0.01308 0.00665 -0.1021 0.8851 0.0062
-6.250 -0.2325 0.01261 0.00611 -0.1021 0.8769 0.0066
-6.000 -0.2048 0.01220 0.00562 -0.1023 0.8702 0.0068
-5.750 -0.1790 0.01184 0.00518 -0.1021 0.8624 0.0073
-5.500 -0.1517 0.01148 0.00472 -0.1022 0.8557 0.0081
-5.250 -0.1257 0.01116 0.00436 -0.1021 0.8485 0.0089
-5.000 -0.0986 0.01087 0.00401 -0.1020 0.8418 0.0110
-4.750 -0.0720 0.01058 0.00371 -0.1020 0.8354 0.0157
-4.250 -0.0186 0.00990 0.00316 -0.1021 0.8230 0.0564
-4.000 0.0073 0.00943 0.00292 -0.1021 0.8167 0.1092
-3.750 0.0337 0.00893 0.00268 -0.1024 0.8108 0.1858
-3.500 0.0608 0.00854 0.00250 -0.1026 0.8053 0.2495
-3.250 0.0879 0.00814 0.00233 -0.1029 0.7993 0.3208
-3.000 0.1157 0.00769 0.00216 -0.1034 0.7938 0.4166
-2.750 0.1436 0.00740 0.00206 -0.1037 0.7880 0.4770
-2.500 0.1716 0.00717 0.00198 -0.1039 0.7818 0.5376
-2.250 0.1997 0.00703 0.00196 -0.1041 0.7760 0.5891
-2.000 0.2276 0.00698 0.00198 -0.1040 0.7695 0.6244
-1.750 0.2557 0.00699 0.00199 -0.1040 0.7632 0.6481
-1.500 0.2838 0.00702 0.00201 -0.1040 0.7568 0.6653
-1.250 0.3119 0.00706 0.00202 -0.1040 0.7497 0.6782
-1.000 0.3402 0.00710 0.00202 -0.1040 0.7430 0.6894
-0.750 0.3680 0.00715 0.00204 -0.1040 0.7354 0.6981
-0.500 0.3961 0.00720 0.00205 -0.1040 0.7280 0.7061
-0.250 0.4236 0.00726 0.00209 -0.1039 0.7194 0.7138
0.000 0.4514 0.00732 0.00211 -0.1038 0.7108 0.7219
0.250 0.4786 0.00739 0.00216 -0.1036 0.7012 0.7282
0.500 0.5062 0.00745 0.00218 -0.1035 0.6907 0.7338
0.750 0.5334 0.00751 0.00221 -0.1034 0.6794 0.7379
1.000 0.5601 0.00758 0.00225 -0.1031 0.6665 0.7416
1.250 0.5867 0.00767 0.00229 -0.1028 0.6518 0.7456
1.500 0.6131 0.00778 0.00233 -0.1025 0.6344 0.7497
1.750 0.6388 0.00790 0.00238 -0.1021 0.6144 0.7534
2.250 0.6882 0.00824 0.00257 -0.1008 0.5697 0.7611
2.500 0.7125 0.00847 0.00268 -0.1001 0.5447 0.7648
2.750 0.7369 0.00870 0.00280 -0.0995 0.5192 0.7679
3.000 0.7605 0.00894 0.00295 -0.0987 0.4937 0.7703
3.250 0.7838 0.00921 0.00313 -0.0979 0.4670 0.7730
3.500 0.8071 0.00949 0.00330 -0.0971 0.4397 0.7757
3.750 0.8304 0.00979 0.00349 -0.0964 0.4129 0.7785
4.000 0.8538 0.01010 0.00369 -0.0957 0.3875 0.7814
4.250 0.8768 0.01042 0.00391 -0.0949 0.3622 0.7839
4.500 0.8996 0.01072 0.00413 -0.0941 0.3382 0.7862
4.750 0.9221 0.01105 0.00438 -0.0932 0.3154 0.7887
5.000 0.9449 0.01137 0.00463 -0.0925 0.2936 0.7914
5.250 0.9677 0.01170 0.00489 -0.0917 0.2736 0.7941
5.750 1.0124 0.01239 0.00545 -0.0900 0.2362 0.7996
6.000 1.0341 0.01273 0.00574 -0.0891 0.2190 0.8021
6.250 1.0557 0.01308 0.00605 -0.0881 0.2030 0.8046
6.500 1.0772 0.01343 0.00637 -0.0871 0.1890 0.8076
6.750 1.0984 0.01380 0.00671 -0.0861 0.1749 0.8109
7.000 1.1188 0.01419 0.00705 -0.0850 0.1614 0.8139
7.250 1.1376 0.01457 0.00741 -0.0835 0.1491 0.8166
7.500 1.1560 0.01495 0.00779 -0.0820 0.1376 0.8196
7.750 1.1750 0.01532 0.00817 -0.0806 0.1281 0.8232
8.000 1.1934 0.01576 0.00859 -0.0791 0.1184 0.8270
8.250 1.2110 0.01623 0.00904 -0.0776 0.1092 0.8306
8.500 1.2291 0.01664 0.00949 -0.0761 0.1014 0.8342
8.750 1.2462 0.01713 0.00999 -0.0745 0.0937 0.8383
9.000 1.2631 0.01763 0.01050 -0.0729 0.0865 0.8427
9.250 1.2799 0.01812 0.01103 -0.0714 0.0809 0.8473
9.500 1.2958 0.01865 0.01160 -0.0697 0.0749 0.8527
9.750 1.3116 0.01922 0.01220 -0.0680 0.0698 0.8586
10.000 1.3267 0.01978 0.01281 -0.0663 0.0649 0.8645
10.250 1.3405 0.02044 0.01350 -0.0645 0.0600 0.8717
10.500 1.3547 0.02104 0.01417 -0.0627 0.0555 0.8795
10.750 1.3667 0.02179 0.01496 -0.0607 0.0511 0.8896
11.000 1.3791 0.02243 0.01569 -0.0587 0.0478 0.9032
11.250 1.3885 0.02312 0.01647 -0.0563 0.0444 0.9276
11.500 1.3990 0.02391 0.01733 -0.0543 0.0413 1.0000
11.750 1.4128 0.02479 0.01826 -0.0531 0.0384 1.0000
12.000 1.4246 0.02583 0.01933 -0.0517 0.0353 1.0000
12.250 1.4363 0.02689 0.02045 -0.0503 0.0329 1.0000
12.500 1.4476 0.02800 0.02161 -0.0490 0.0304 1.0000
12.750 1.4567 0.02930 0.02295 -0.0476 0.0280 1.0000
13.000 1.4671 0.03054 0.02425 -0.0464 0.0261 1.0000
13.250 1.4757 0.03193 0.02570 -0.0452 0.0238 1.0000
13.500 1.4828 0.03351 0.02732 -0.0440 0.0218 1.0000
13.750 1.4908 0.03504 0.02892 -0.0429 0.0199 1.0000
14.000 1.4956 0.03689 0.03080 -0.0418 0.0177 1.0000
14.250 1.5020 0.03864 0.03265 -0.0409 0.0161 1.0000
14.500 1.5061 0.04068 0.03475 -0.0400 0.0145 1.0000
14.750 1.5098 0.04281 0.03696 -0.0392 0.0132 1.0000
15.000 1.5127 0.04510 0.03932 -0.0386 0.0117 1.0000
15.250 1.5139 0.04766 0.04196 -0.0381 0.0108 1.0000
15.500 1.5162 0.05020 0.04460 -0.0378 0.0100 1.0000
15.750 1.5170 0.05300 0.04751 -0.0377 0.0094 1.0000
16.000 1.5159 0.05613 0.05074 -0.0378 0.0087 1.0000
16.250 1.5138 0.05953 0.05424 -0.0381 0.0082 1.0000
16.500 1.5120 0.06303 0.05786 -0.0387 0.0077 1.0000
16.750 1.5088 0.06685 0.06182 -0.0395 0.0073 1.0000
17.000 1.5038 0.07107 0.06616 -0.0406 0.0069 1.0000
17.250 1.4975 0.07565 0.07087 -0.0421 0.0066 1.0000
17.500 1.4894 0.08071 0.07605 -0.0439 0.0063 1.0000
17.750 1.4808 0.08598 0.08146 -0.0459 0.0060 1.0000
18.000 1.4712 0.09158 0.08721 -0.0483 0.0058 1.0000
18.250 1.4601 0.09762 0.09340 -0.0511 0.0056 1.0000
18.500 1.4476 0.10407 0.09999 -0.0542 0.0053 1.0000
18.750 1.4340 0.11085 0.10692 -0.0577 0.0052 1.0000
19.000 1.4193 0.11797 0.11419 -0.0614 0.0051 1.0000
19.250 1.4039 0.12540 0.12177 -0.0656 0.0050 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 201 13.08% (mh201-il)