MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.13 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh122-il-1000000-n5.txt Download as CSV file: xf-mh122-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2809 0.08333 0.08160 -0.0764 0.9779 0.0040
-8.750 -0.2742 0.07932 0.07760 -0.0793 0.9721 0.0042
-8.500 -0.2713 0.07500 0.07329 -0.0820 0.9634 0.0042
-6.000 -0.1092 0.01731 0.01324 -0.1374 0.8761 0.0026
-5.750 -0.0868 0.01473 0.01027 -0.1370 0.8718 0.0024
-5.500 -0.0624 0.01291 0.00815 -0.1366 0.8679 0.0023
-5.250 -0.0370 0.01155 0.00657 -0.1363 0.8646 0.0022
-5.000 -0.0114 0.01047 0.00533 -0.1360 0.8613 0.0021
-4.750 0.0148 0.00961 0.00432 -0.1358 0.8581 0.0021
-4.500 0.0417 0.00895 0.00353 -0.1358 0.8552 0.0021
-4.250 0.0692 0.00848 0.00291 -0.1359 0.8525 0.0021
-4.000 0.0968 0.00810 0.00244 -0.1359 0.8497 0.0021
-3.750 0.1247 0.00781 0.00208 -0.1360 0.8470 0.0022
-3.500 0.1527 0.00760 0.00180 -0.1362 0.8443 0.0023
-3.250 0.1808 0.00744 0.00158 -0.1363 0.8417 0.0026
-3.000 0.2090 0.00731 0.00142 -0.1364 0.8393 0.0047
-2.750 0.2368 0.00700 0.00125 -0.1367 0.8370 0.0453
-2.500 0.2645 0.00653 0.00111 -0.1371 0.8344 0.1466
-2.250 0.2918 0.00586 0.00097 -0.1377 0.8317 0.3206
-2.000 0.3197 0.00568 0.00093 -0.1379 0.8292 0.3788
-1.750 0.3479 0.00556 0.00091 -0.1382 0.8269 0.4245
-1.500 0.3761 0.00548 0.00090 -0.1384 0.8245 0.4593
-1.250 0.4041 0.00542 0.00090 -0.1385 0.8219 0.4857
-1.000 0.4320 0.00539 0.00091 -0.1386 0.8187 0.5038
-0.750 0.4600 0.00537 0.00090 -0.1387 0.8149 0.5161
-0.500 0.4878 0.00538 0.00090 -0.1388 0.8105 0.5252
-0.250 0.5153 0.00537 0.00090 -0.1387 0.8047 0.5337
0.000 0.5427 0.00538 0.00090 -0.1387 0.7987 0.5423
0.250 0.5699 0.00537 0.00092 -0.1386 0.7914 0.5507
0.500 0.5970 0.00539 0.00093 -0.1385 0.7835 0.5600
0.750 0.6237 0.00540 0.00096 -0.1383 0.7735 0.5691
1.000 0.6501 0.00542 0.00098 -0.1380 0.7609 0.5787
1.250 0.6756 0.00548 0.00101 -0.1375 0.7430 0.5892
1.500 0.6995 0.00559 0.00105 -0.1367 0.7123 0.5997
1.750 0.7213 0.00581 0.00113 -0.1354 0.6691 0.6107
2.000 0.7400 0.00622 0.00132 -0.1335 0.6044 0.6223
2.250 0.7574 0.00677 0.00158 -0.1315 0.5298 0.6342
2.500 0.7756 0.00734 0.00185 -0.1297 0.4538 0.6475
2.750 0.7943 0.00790 0.00214 -0.1281 0.3810 0.6615
3.000 0.8145 0.00838 0.00241 -0.1268 0.3197 0.6771
3.250 0.8349 0.00885 0.00270 -0.1255 0.2625 0.6943
3.500 0.8550 0.00936 0.00300 -0.1242 0.2052 0.7125
3.750 0.8772 0.00971 0.00327 -0.1233 0.1688 0.7328
4.000 0.8983 0.01013 0.00357 -0.1221 0.1280 0.7561
4.250 0.9209 0.01042 0.00385 -0.1213 0.1040 0.7830
4.500 0.9431 0.01070 0.00414 -0.1203 0.0841 0.8163
4.750 0.9642 0.01093 0.00445 -0.1190 0.0669 0.8600
5.000 0.9815 0.01097 0.00466 -0.1168 0.0566 1.0000
5.250 1.0047 0.01130 0.00495 -0.1160 0.0463 1.0000
5.500 1.0274 0.01167 0.00527 -0.1152 0.0353 1.0000
5.750 1.0496 0.01207 0.00561 -0.1143 0.0248 1.0000
6.000 1.0710 0.01253 0.00600 -0.1133 0.0143 1.0000
6.250 1.0926 0.01298 0.00640 -0.1123 0.0083 1.0000
6.500 1.1136 0.01346 0.00685 -0.1112 0.0038 1.0000
6.750 1.1346 0.01394 0.00733 -0.1101 0.0018 1.0000
7.000 1.1561 0.01435 0.00781 -0.1091 0.0014 1.0000
7.250 1.1766 0.01479 0.00830 -0.1078 0.0011 1.0000
7.500 1.1964 0.01528 0.00884 -0.1065 0.0009 1.0000
7.750 1.2153 0.01583 0.00946 -0.1049 0.0007 1.0000
8.000 1.2337 0.01646 0.01016 -0.1033 0.0006 1.0000
8.250 1.2530 0.01694 0.01069 -0.1020 0.0006 1.0000
8.500 1.2719 0.01747 0.01129 -0.1006 0.0005 1.0000
8.750 1.2903 0.01807 0.01195 -0.0991 0.0005 1.0000
9.000 1.3080 0.01873 0.01269 -0.0975 0.0004 1.0000
9.250 1.3250 0.01945 0.01350 -0.0958 0.0004 1.0000
9.500 1.3414 0.02025 0.01439 -0.0941 0.0003 1.0000
9.750 1.3573 0.02109 0.01537 -0.0923 0.0003 1.0000
10.000 1.3721 0.02203 0.01642 -0.0904 0.0003 1.0000
10.250 1.3863 0.02302 0.01753 -0.0884 0.0002 1.0000
10.500 1.3994 0.02411 0.01875 -0.0864 0.0002 1.0000
10.750 1.4115 0.02527 0.02004 -0.0842 0.0002 1.0000
11.000 1.4218 0.02660 0.02153 -0.0819 0.0002 1.0000
11.250 1.4313 0.02797 0.02306 -0.0795 0.0002 1.0000
11.500 1.4387 0.02954 0.02480 -0.0770 0.0002 1.0000
11.750 1.4451 0.03116 0.02659 -0.0745 0.0002 1.0000
12.000 1.4493 0.03299 0.02861 -0.0718 0.0002 1.0000
12.250 1.4509 0.03508 0.03089 -0.0691 0.0002 1.0000
12.500 1.4506 0.03735 0.03339 -0.0664 0.0002 1.0000
12.750 1.4466 0.04003 0.03628 -0.0636 0.0002 1.0000
13.000 1.4415 0.04286 0.03932 -0.0611 0.0002 1.0000
13.250 1.4345 0.04596 0.04263 -0.0588 0.0002 1.0000
13.500 1.4238 0.04960 0.04648 -0.0568 0.0002 1.0000
13.750 1.4105 0.05373 0.05083 -0.0552 0.0002 1.0000
14.000 1.3924 0.05873 0.05606 -0.0542 0.0002 1.0000
14.250 1.3745 0.06407 0.06161 -0.0542 0.0002 1.0000
14.500 1.3533 0.07047 0.06821 -0.0553 0.0002 1.0000
14.750 1.3301 0.07803 0.07597 -0.0579 0.0002 1.0000
15.000 1.3044 0.08723 0.08536 -0.0625 0.0002 1.0000
15.250 1.2770 0.09858 0.09690 -0.0694 0.0002 1.0000
15.500 1.2434 0.11434 0.11286 -0.0796 0.0002 1.0000
15.750 1.1968 0.13518 0.13384 -0.0911 0.0002 1.0000
16.000 1.1505 0.15441 0.15314 -0.1015 0.0002 1.0000
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Polar data table (+)
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