MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 50,000 Max Cl/Cd: 34.43 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh25-il-50000.txt Download as CSV file: xf-mh25-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 25 9.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4666 0.11289 0.10613 -0.0232 1.0000 0.2334
-9.250 -0.4768 0.11105 0.10437 -0.0227 1.0000 0.2438
-9.000 -0.4672 0.10716 0.10052 -0.0210 1.0000 0.2554
-8.750 -0.4649 0.10394 0.09735 -0.0196 1.0000 0.2658
-8.500 -0.4678 0.10101 0.09450 -0.0181 1.0000 0.2787
-8.250 -0.4716 0.09834 0.09192 -0.0165 1.0000 0.2911
-8.000 -0.4738 0.09556 0.08921 -0.0144 1.0000 0.3063
-7.750 -0.4779 0.09297 0.08669 -0.0122 1.0000 0.3216
-7.500 -0.5002 0.09144 0.08530 -0.0092 1.0000 0.3398
-5.500 -0.6012 0.05637 0.04931 -0.0121 1.0000 0.1437
-5.250 -0.5937 0.05147 0.04320 -0.0095 1.0000 0.1082
-5.000 -0.5787 0.04717 0.03889 -0.0078 1.0000 0.1008
-4.750 -0.5643 0.04366 0.03470 -0.0051 1.0000 0.0919
-4.500 -0.5481 0.04036 0.03096 -0.0029 1.0000 0.0875
-4.250 -0.5288 0.03742 0.02726 -0.0003 1.0000 0.0832
-4.000 -0.5080 0.03491 0.02444 0.0014 1.0000 0.0848
-3.750 -0.4862 0.03292 0.02201 0.0030 1.0000 0.0914
-3.500 -0.1782 0.02388 0.01565 -0.0353 1.0000 1.0000
-3.250 -0.1710 0.02349 0.01490 -0.0326 1.0000 1.0000
-3.000 -0.1626 0.02320 0.01428 -0.0300 1.0000 1.0000
-2.750 -0.1532 0.02296 0.01367 -0.0274 1.0000 1.0000
-2.500 -0.1432 0.02278 0.01322 -0.0249 1.0000 1.0000
-2.250 -0.1325 0.02264 0.01282 -0.0223 1.0000 1.0000
-2.000 -0.1216 0.02254 0.01249 -0.0199 1.0000 1.0000
-1.750 -0.1103 0.02247 0.01221 -0.0174 1.0000 1.0000
-1.500 -0.0988 0.02244 0.01199 -0.0150 1.0000 1.0000
-1.250 -0.0871 0.02243 0.01180 -0.0126 1.0000 1.0000
-1.000 -0.0753 0.02245 0.01166 -0.0102 1.0000 1.0000
-0.750 -0.0634 0.02250 0.01153 -0.0079 1.0000 1.0000
-0.500 -0.0515 0.02258 0.01148 -0.0056 1.0000 1.0000
-0.250 -0.0394 0.02269 0.01147 -0.0033 1.0000 1.0000
0.000 -0.0274 0.02283 0.01151 -0.0011 1.0000 1.0000
0.250 -0.0154 0.02300 0.01158 0.0010 1.0000 1.0000
0.500 -0.0033 0.02320 0.01168 0.0032 1.0000 1.0000
0.750 0.0088 0.02344 0.01185 0.0052 1.0000 1.0000
1.000 0.0208 0.02371 0.01207 0.0072 1.0000 1.0000
1.250 0.0328 0.02402 0.01234 0.0091 1.0000 1.0000
1.500 0.0448 0.02438 0.01267 0.0109 1.0000 1.0000
1.750 0.0567 0.02478 0.01305 0.0127 1.0000 1.0000
2.000 0.0684 0.02523 0.01349 0.0143 1.0000 1.0000
2.250 0.0799 0.02574 0.01400 0.0159 1.0000 1.0000
2.500 0.0913 0.02631 0.01457 0.0174 1.0000 1.0000
2.750 0.1025 0.02694 0.01522 0.0187 1.0000 1.0000
3.000 0.1136 0.02764 0.01595 0.0199 1.0000 1.0000
3.250 0.1244 0.02841 0.01677 0.0210 1.0000 1.0000
3.500 0.1919 0.03051 0.01908 0.0109 0.9752 1.0000
3.750 0.2564 0.03217 0.02095 0.0021 0.9468 1.0000
4.000 0.3164 0.03334 0.02236 -0.0052 0.9185 1.0000
4.250 0.3772 0.03405 0.02343 -0.0118 0.8899 1.0000
4.500 0.4266 0.03420 0.02387 -0.0158 0.8591 1.0000
4.750 0.4855 0.03382 0.02387 -0.0205 0.8275 1.0000
5.000 0.5555 0.03255 0.02316 -0.0257 0.7942 1.0000
5.250 0.6550 0.02915 0.02052 -0.0329 0.7554 1.0000
5.500 0.7578 0.02465 0.01682 -0.0384 0.6873 1.0000
5.750 0.8061 0.02341 0.01544 -0.0373 0.5848 1.0000
6.000 0.8233 0.02406 0.01558 -0.0331 0.4888 1.0000
6.250 0.8328 0.02531 0.01627 -0.0285 0.4035 1.0000
6.500 0.8406 0.02687 0.01732 -0.0243 0.3282 1.0000
6.750 0.8516 0.02871 0.01864 -0.0208 0.2636 1.0000
7.000 0.8630 0.03057 0.02021 -0.0176 0.2125 1.0000
7.250 0.8852 0.03311 0.02260 -0.0161 0.1736 1.0000
7.500 0.8999 0.03513 0.02470 -0.0137 0.1467 1.0000
7.750 0.9275 0.03845 0.02803 -0.0132 0.1299 1.0000
8.000 0.9416 0.04120 0.03129 -0.0102 0.1203 1.0000
8.250 0.9491 0.04380 0.03424 -0.0068 0.1106 1.0000
8.500 0.9637 0.04718 0.03768 -0.0048 0.1032 1.0000
8.750 0.9638 0.05052 0.04161 -0.0004 0.1017 1.0000
9.000 0.9606 0.05415 0.04574 0.0041 0.1009 1.0000
9.250 0.9543 0.05778 0.04977 0.0085 0.1008 1.0000
9.500 0.9452 0.06152 0.05385 0.0127 0.1013 1.0000
9.750 0.9336 0.06532 0.05793 0.0167 0.1019 1.0000
10.000 0.9184 0.06902 0.06185 0.0205 0.1022 1.0000
10.250 0.9016 0.07274 0.06574 0.0240 0.1026 1.0000
10.500 0.8867 0.07651 0.06961 0.0270 0.1032 1.0000
10.750 0.8706 0.08055 0.07373 0.0294 0.1036 1.0000
11.000 0.7116 0.07872 0.07243 0.0330 0.1146 1.0000
11.250 0.6355 0.09473 0.08825 0.0221 0.1406 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 25 9.98% (mh25-il)