MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.62 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh62-il-1000000-n5.txt Download as CSV file: xf-mh62-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6534 0.06619 0.06475 -0.0049 0.9195 0.0019
-8.500 -0.6832 0.05452 0.05282 -0.0131 0.8766 0.0018
-8.250 -0.7091 0.04310 0.04097 -0.0159 0.8578 0.0018
-8.000 -0.7392 0.02856 0.02540 -0.0151 0.8438 0.0016
-7.750 -0.7304 0.02326 0.01944 -0.0138 0.8338 0.0016
-7.500 -0.7130 0.02014 0.01584 -0.0128 0.8249 0.0016
-7.250 -0.6918 0.01812 0.01348 -0.0120 0.8166 0.0016
-7.000 -0.6689 0.01652 0.01159 -0.0113 0.8082 0.0016
-6.750 -0.6449 0.01527 0.01011 -0.0107 0.8005 0.0016
-6.500 -0.6201 0.01423 0.00887 -0.0102 0.7924 0.0016
-6.250 -0.5949 0.01334 0.00780 -0.0097 0.7849 0.0017
-6.000 -0.5692 0.01260 0.00690 -0.0093 0.7773 0.0017
-5.750 -0.5430 0.01194 0.00612 -0.0089 0.7698 0.0018
-5.500 -0.5165 0.01140 0.00546 -0.0086 0.7623 0.0019
-5.250 -0.4897 0.01093 0.00490 -0.0084 0.7546 0.0020
-5.000 -0.4626 0.01056 0.00444 -0.0081 0.7473 0.0021
-4.750 -0.4351 0.01027 0.00408 -0.0080 0.7394 0.0022
-4.500 -0.4081 0.00980 0.00350 -0.0077 0.7320 0.0027
-4.250 -0.3806 0.00953 0.00318 -0.0076 0.7240 0.0030
-4.000 -0.3529 0.00929 0.00289 -0.0074 0.7162 0.0034
-3.750 -0.3251 0.00909 0.00262 -0.0073 0.7079 0.0039
-3.500 -0.2972 0.00888 0.00236 -0.0072 0.6995 0.0047
-3.250 -0.2695 0.00864 0.00211 -0.0071 0.6912 0.0091
-3.000 -0.2420 0.00835 0.00188 -0.0070 0.6822 0.0250
-2.750 -0.2144 0.00808 0.00168 -0.0069 0.6735 0.0493
-2.500 -0.1878 0.00761 0.00145 -0.0068 0.6646 0.1175
-2.250 -0.1604 0.00733 0.00131 -0.0067 0.6546 0.1617
-2.000 -0.1325 0.00719 0.00119 -0.0067 0.6448 0.1873
-1.750 -0.1047 0.00702 0.00109 -0.0066 0.6342 0.2221
-1.500 -0.0771 0.00684 0.00100 -0.0066 0.6228 0.2628
-1.250 -0.0495 0.00667 0.00093 -0.0066 0.6107 0.3068
-1.000 -0.0216 0.00655 0.00087 -0.0065 0.5978 0.3400
-0.750 0.0063 0.00646 0.00082 -0.0065 0.5842 0.3719
-0.500 0.0342 0.00639 0.00078 -0.0065 0.5696 0.4030
-0.250 0.0622 0.00633 0.00075 -0.0065 0.5541 0.4345
0.000 0.0900 0.00626 0.00073 -0.0064 0.5377 0.4679
0.250 0.1177 0.00621 0.00072 -0.0064 0.5202 0.5043
0.500 0.1453 0.00617 0.00073 -0.0064 0.5018 0.5420
0.750 0.1728 0.00612 0.00074 -0.0063 0.4832 0.5840
1.000 0.2000 0.00607 0.00076 -0.0061 0.4645 0.6315
1.250 0.2268 0.00600 0.00079 -0.0059 0.4460 0.6832
1.500 0.2531 0.00593 0.00084 -0.0056 0.4273 0.7409
1.750 0.2785 0.00583 0.00090 -0.0050 0.4090 0.8061
2.000 0.3031 0.00571 0.00096 -0.0041 0.3909 0.8797
2.250 0.3428 0.00572 0.00105 -0.0066 0.3693 0.9547
2.500 0.3893 0.00589 0.00113 -0.0108 0.3470 0.9813
2.750 0.4236 0.00605 0.00123 -0.0122 0.3279 0.9934
3.000 0.4586 0.00621 0.00131 -0.0139 0.3092 0.9997
3.250 0.4862 0.00639 0.00141 -0.0139 0.2914 1.0000
3.500 0.5130 0.00655 0.00152 -0.0137 0.2760 1.0000
3.750 0.5397 0.00673 0.00163 -0.0135 0.2584 1.0000
4.000 0.5664 0.00691 0.00175 -0.0133 0.2425 1.0000
4.250 0.5929 0.00713 0.00190 -0.0131 0.2249 1.0000
4.500 0.6195 0.00734 0.00206 -0.0129 0.2089 1.0000
4.750 0.6460 0.00755 0.00222 -0.0127 0.1939 1.0000
5.000 0.6724 0.00779 0.00239 -0.0126 0.1768 1.0000
5.250 0.6987 0.00804 0.00258 -0.0124 0.1610 1.0000
5.500 0.7250 0.00831 0.00279 -0.0122 0.1454 1.0000
5.750 0.7511 0.00858 0.00303 -0.0120 0.1311 1.0000
6.000 0.7772 0.00887 0.00326 -0.0117 0.1172 1.0000
6.250 0.8031 0.00917 0.00351 -0.0115 0.1039 1.0000
6.500 0.8287 0.00953 0.00380 -0.0113 0.0873 1.0000
6.750 0.8543 0.00988 0.00410 -0.0111 0.0738 1.0000
7.000 0.8797 0.01025 0.00441 -0.0108 0.0617 1.0000
7.250 0.9047 0.01068 0.00480 -0.0106 0.0474 1.0000
7.500 0.9289 0.01124 0.00525 -0.0102 0.0311 1.0000
7.750 0.9532 0.01175 0.00570 -0.0099 0.0204 1.0000
8.000 0.9773 0.01227 0.00617 -0.0095 0.0128 1.0000
8.250 1.0014 0.01276 0.00665 -0.0092 0.0086 1.0000
8.500 1.0259 0.01317 0.00708 -0.0088 0.0069 1.0000
8.750 1.0499 0.01365 0.00757 -0.0085 0.0051 1.0000
9.000 1.0738 0.01410 0.00807 -0.0081 0.0038 1.0000
9.250 1.0969 0.01464 0.00863 -0.0076 0.0025 1.0000
9.500 1.1197 0.01520 0.00923 -0.0071 0.0017 1.0000
9.750 1.1424 0.01574 0.00982 -0.0066 0.0013 1.0000
10.000 1.1645 0.01632 0.01046 -0.0060 0.0010 1.0000
10.250 1.1859 0.01695 0.01115 -0.0054 0.0008 1.0000
10.500 1.2066 0.01764 0.01191 -0.0047 0.0007 1.0000
10.750 1.2260 0.01842 0.01278 -0.0039 0.0006 1.0000
11.000 1.2450 0.01919 0.01365 -0.0030 0.0005 1.0000
11.250 1.2632 0.01997 0.01452 -0.0021 0.0005 1.0000
11.500 1.2806 0.02076 0.01539 -0.0011 0.0005 1.0000
11.750 1.2960 0.02165 0.01638 0.0001 0.0004 1.0000
12.000 1.3093 0.02264 0.01747 0.0014 0.0004 1.0000
12.250 1.3197 0.02365 0.01858 0.0031 0.0004 1.0000
12.500 1.3247 0.02469 0.01971 0.0055 0.0004 1.0000
12.750 1.3266 0.02615 0.02129 0.0075 0.0003 1.0000
13.000 1.3306 0.02767 0.02292 0.0088 0.0003 1.0000
13.250 1.3347 0.02935 0.02470 0.0098 0.0003 1.0000
13.500 1.3320 0.03184 0.02735 0.0105 0.0003 1.0000
13.750 1.3343 0.03402 0.02963 0.0107 0.0003 1.0000
14.000 1.3316 0.03691 0.03266 0.0105 0.0003 1.0000
14.250 1.3292 0.03995 0.03584 0.0099 0.0003 1.0000
14.500 1.3222 0.04379 0.03982 0.0088 0.0003 1.0000
14.750 1.3107 0.04849 0.04468 0.0070 0.0003 1.0000
15.000 1.3028 0.05296 0.04928 0.0050 0.0003 1.0000
15.250 1.2910 0.05826 0.05471 0.0025 0.0003 1.0000
15.500 1.2773 0.06409 0.06068 -0.0004 0.0003 1.0000
15.750 1.2554 0.07159 0.06834 -0.0043 0.0003 1.0000
16.000 1.2362 0.07893 0.07582 -0.0082 0.0003 1.0000
16.250 1.2183 0.08621 0.08322 -0.0119 0.0003 1.0000
16.500 1.1933 0.09509 0.09223 -0.0165 0.0003 1.0000
16.750 1.1663 0.10463 0.10190 -0.0214 0.0003 1.0000
17.000 1.1486 0.11256 0.10993 -0.0255 0.0003 1.0000
17.250 1.1248 0.12196 0.11944 -0.0304 0.0003 1.0000
17.500 1.0950 0.13319 0.13078 -0.0364 0.0003 1.0000
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Polar data table (+)
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