MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 500,000 Max Cl/Cd: 84.36 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh61-il-500000.txt Download as CSV file: xf-mh61-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5860 0.08618 0.08437 0.0061 1.0000 0.0164
-8.750 -0.5857 0.08000 0.07822 0.0013 1.0000 0.0167
-8.500 -0.5981 0.07130 0.06959 -0.0067 1.0000 0.0162
-8.250 -0.6257 0.06511 0.06320 -0.0112 0.9104 0.0154
-8.000 -0.6424 0.06063 0.05853 -0.0115 0.8909 0.0152
-7.750 -0.6494 0.05580 0.05346 -0.0120 0.8780 0.0155
-7.500 -0.6435 0.05238 0.04979 -0.0118 0.8679 0.0164
-7.250 -0.6325 0.05059 0.04769 -0.0110 0.8593 0.0171
-5.250 -0.5161 0.01915 0.01315 -0.0025 0.8079 0.0106
-5.000 -0.4879 0.01902 0.01292 -0.0021 0.8016 0.0098
-4.750 -0.4645 0.01630 0.00999 -0.0010 0.7962 0.0087
-4.500 -0.4401 0.01473 0.00825 0.0000 0.7908 0.0083
-4.250 -0.4153 0.01356 0.00693 0.0008 0.7848 0.0081
-4.000 -0.3907 0.01265 0.00587 0.0017 0.7798 0.0082
-3.750 -0.3645 0.01191 0.00501 0.0022 0.7735 0.0084
-3.500 -0.3382 0.01135 0.00428 0.0027 0.7680 0.0091
-3.250 -0.3115 0.01071 0.00347 0.0033 0.7623 0.0140
-3.000 -0.2897 0.00927 0.00282 0.0040 0.7564 0.1878
-2.750 -0.2665 0.00844 0.00262 0.0045 0.7511 0.3398
-2.500 -0.2407 0.00802 0.00249 0.0048 0.7446 0.4205
-2.250 -0.2145 0.00779 0.00235 0.0052 0.7393 0.4713
-2.000 -0.1881 0.00751 0.00223 0.0054 0.7327 0.5265
-1.750 -0.1619 0.00729 0.00211 0.0059 0.7269 0.5743
-1.500 -0.1357 0.00706 0.00203 0.0063 0.7205 0.6246
-1.250 -0.1101 0.00682 0.00194 0.0069 0.7142 0.6786
-1.000 -0.0850 0.00658 0.00188 0.0076 0.7079 0.7381
-0.750 -0.0601 0.00632 0.00182 0.0086 0.7013 0.8045
-0.500 -0.0321 0.00611 0.00180 0.0090 0.6949 0.8745
-0.250 0.0126 0.00606 0.00182 0.0057 0.6876 0.9300
0.000 0.0608 0.00612 0.00182 0.0015 0.6803 0.9564
0.250 0.1028 0.00618 0.00182 -0.0014 0.6727 0.9717
0.500 0.1424 0.00625 0.00183 -0.0038 0.6645 0.9839
0.750 0.1839 0.00631 0.00181 -0.0067 0.6565 0.9928
1.000 0.2279 0.00631 0.00178 -0.0102 0.6470 0.9993
1.250 0.2562 0.00631 0.00174 -0.0104 0.6381 1.0000
1.500 0.2822 0.00633 0.00171 -0.0100 0.6293 1.0000
1.750 0.3084 0.00634 0.00170 -0.0098 0.6191 1.0000
2.000 0.3348 0.00637 0.00170 -0.0095 0.6089 1.0000
2.250 0.3613 0.00641 0.00170 -0.0092 0.5984 1.0000
2.500 0.3878 0.00647 0.00172 -0.0090 0.5873 1.0000
2.750 0.4144 0.00653 0.00177 -0.0088 0.5754 1.0000
3.000 0.4412 0.00660 0.00182 -0.0086 0.5623 1.0000
3.250 0.4680 0.00669 0.00188 -0.0084 0.5481 1.0000
3.500 0.4948 0.00678 0.00195 -0.0082 0.5324 1.0000
3.750 0.5216 0.00689 0.00205 -0.0081 0.5153 1.0000
4.000 0.5485 0.00703 0.00215 -0.0080 0.4970 1.0000
4.250 0.5752 0.00719 0.00227 -0.0078 0.4776 1.0000
4.500 0.6020 0.00737 0.00241 -0.0077 0.4565 1.0000
4.750 0.6286 0.00757 0.00260 -0.0076 0.4344 1.0000
5.000 0.6552 0.00781 0.00278 -0.0075 0.4108 1.0000
5.250 0.6816 0.00808 0.00299 -0.0074 0.3842 1.0000
5.500 0.7077 0.00840 0.00323 -0.0074 0.3529 1.0000
5.750 0.7337 0.00873 0.00349 -0.0073 0.3242 1.0000
6.000 0.7592 0.00916 0.00380 -0.0072 0.2897 1.0000
6.250 0.7841 0.00968 0.00420 -0.0070 0.2449 1.0000
6.500 0.8080 0.01036 0.00465 -0.0069 0.1943 1.0000
6.750 0.8309 0.01116 0.00520 -0.0066 0.1403 1.0000
7.000 0.8523 0.01214 0.00586 -0.0063 0.0859 1.0000
7.250 0.8735 0.01305 0.00655 -0.0058 0.0484 1.0000
7.500 0.8949 0.01387 0.00724 -0.0052 0.0272 1.0000
7.750 0.9129 0.01520 0.00854 -0.0041 0.0113 1.0000
8.000 0.9326 0.01616 0.00957 -0.0031 0.0074 1.0000
8.250 0.9449 0.01794 0.01156 -0.0013 0.0062 1.0000
8.500 0.9575 0.01948 0.01326 0.0005 0.0059 1.0000
8.750 0.9719 0.02073 0.01462 0.0021 0.0058 1.0000
9.000 0.9838 0.02224 0.01632 0.0040 0.0056 1.0000
9.250 0.9951 0.02386 0.01808 0.0059 0.0056 1.0000
9.500 1.0055 0.02565 0.02003 0.0078 0.0056 1.0000
9.750 1.0144 0.02784 0.02241 0.0099 0.0056 1.0000
10.000 1.0210 0.03023 0.02500 0.0120 0.0057 1.0000
10.250 1.0224 0.03295 0.02796 0.0145 0.0058 1.0000
10.500 1.0176 0.03757 0.03287 0.0169 0.0061 1.0000
10.750 1.0205 0.03916 0.03459 0.0185 0.0062 1.0000
11.000 1.0221 0.04104 0.03661 0.0198 0.0063 1.0000
11.250 1.0242 0.04287 0.03857 0.0207 0.0064 1.0000
11.500 1.0234 0.04519 0.04106 0.0213 0.0066 1.0000
11.750 0.9781 0.05521 0.05182 0.0219 0.0090 1.0000
12.000 0.9584 0.06055 0.05737 0.0204 0.0093 1.0000
12.250 0.9364 0.06663 0.06363 0.0178 0.0097 1.0000
12.500 0.9169 0.07282 0.06998 0.0144 0.0098 1.0000
12.750 0.8941 0.08027 0.07758 0.0099 0.0101 1.0000
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Polar data table (+)
Polar graphs
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