MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.08 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh121-il-1000000.txt Download as CSV file: xf-mh121-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4302 0.11709 0.11544 -0.0307 1.0000 0.0034
-10.250 -0.4300 0.11409 0.11246 -0.0308 1.0000 0.0034
-10.000 -0.4314 0.11100 0.10940 -0.0307 1.0000 0.0035
-9.750 -0.4234 0.10676 0.10516 -0.0337 0.9994 0.0036
-9.500 -0.4133 0.10231 0.10071 -0.0374 0.9984 0.0038
-9.250 -0.4037 0.09751 0.09592 -0.0414 0.9972 0.0038
-9.000 -0.3933 0.09276 0.09118 -0.0458 0.9959 0.0040
-8.750 -0.3821 0.08793 0.08635 -0.0505 0.9947 0.0041
-8.500 -0.3713 0.08293 0.08135 -0.0556 0.9933 0.0042
-8.250 -0.3628 0.07795 0.07638 -0.0604 0.9902 0.0042
-8.000 -0.3517 0.07261 0.07105 -0.0665 0.9868 0.0044
-7.750 -0.3383 0.06634 0.06479 -0.0750 0.9836 0.0045
-7.500 -0.3231 0.05583 0.05425 -0.0930 0.9753 0.0043
-7.250 -0.3027 0.04783 0.04607 -0.1045 0.9709 0.0044
-7.000 -0.2859 0.04192 0.03997 -0.1101 0.9648 0.0046
-6.750 -0.2633 0.03687 0.03468 -0.1142 0.9603 0.0049
-6.500 -0.2295 0.03534 0.03305 -0.1158 0.9586 0.0060
-5.500 -0.1279 0.01419 0.00997 -0.1238 0.9376 0.0037
-5.250 -0.0979 0.01265 0.00816 -0.1245 0.9335 0.0043
-5.000 -0.0683 0.01174 0.00712 -0.1250 0.9295 0.0051
-4.750 -0.0415 0.01103 0.00631 -0.1249 0.9243 0.0056
-4.500 -0.0130 0.01021 0.00537 -0.1252 0.9201 0.0059
-4.250 0.0135 0.00910 0.00411 -0.1253 0.9156 0.0072
-4.000 0.0400 0.00839 0.00328 -0.1252 0.9109 0.0076
-3.750 0.0686 0.00791 0.00268 -0.1254 0.9071 0.0073
-3.500 0.0972 0.00750 0.00213 -0.1256 0.9036 0.0073
-3.250 0.1249 0.00701 0.00159 -0.1255 0.8995 0.0348
-3.000 0.1504 0.00558 0.00124 -0.1263 0.8957 0.3609
-2.750 0.1789 0.00534 0.00120 -0.1268 0.8926 0.4496
-2.500 0.2067 0.00528 0.00116 -0.1269 0.8893 0.4709
-2.250 0.2346 0.00524 0.00113 -0.1270 0.8858 0.4926
-2.000 0.2627 0.00521 0.00110 -0.1272 0.8827 0.5092
-1.750 0.2915 0.00519 0.00106 -0.1274 0.8798 0.5282
-1.500 0.3194 0.00517 0.00107 -0.1276 0.8767 0.5470
-1.250 0.3471 0.00514 0.00107 -0.1276 0.8733 0.5625
-1.000 0.3752 0.00513 0.00107 -0.1278 0.8699 0.5757
-0.750 0.4037 0.00513 0.00107 -0.1280 0.8664 0.5869
-0.500 0.4311 0.00512 0.00108 -0.1280 0.8620 0.5973
-0.250 0.4585 0.00510 0.00109 -0.1279 0.8569 0.6079
0.000 0.4867 0.00511 0.00110 -0.1280 0.8519 0.6189
0.250 0.5134 0.00508 0.00112 -0.1278 0.8459 0.6305
0.500 0.5412 0.00508 0.00113 -0.1278 0.8399 0.6429
0.750 0.5678 0.00505 0.00116 -0.1276 0.8328 0.6562
1.000 0.5950 0.00505 0.00119 -0.1275 0.8254 0.6704
1.250 0.6212 0.00502 0.00121 -0.1271 0.8160 0.6858
1.500 0.6474 0.00501 0.00124 -0.1267 0.8047 0.7023
1.750 0.6736 0.00500 0.00128 -0.1264 0.7931 0.7200
2.000 0.6982 0.00502 0.00130 -0.1256 0.7708 0.7397
2.250 0.7073 0.00566 0.00138 -0.1214 0.6253 0.7606
2.500 0.7245 0.00621 0.00168 -0.1193 0.5392 0.7846
2.750 0.7278 0.00785 0.00230 -0.1148 0.2968 0.8127
3.000 0.7428 0.00869 0.00269 -0.1125 0.1738 0.8482
3.250 0.7574 0.00931 0.00304 -0.1099 0.0828 0.8999
3.500 0.7744 0.00988 0.00338 -0.1078 0.0144 1.0000
3.750 0.7986 0.01027 0.00372 -0.1071 0.0028 1.0000
4.000 0.8238 0.01057 0.00412 -0.1065 0.0024 1.0000
4.250 0.8478 0.01099 0.00465 -0.1057 0.0024 1.0000
4.500 0.8709 0.01152 0.00527 -0.1047 0.0024 1.0000
4.750 0.8933 0.01214 0.00602 -0.1035 0.0025 1.0000
5.000 0.9153 0.01282 0.00679 -0.1022 0.0027 1.0000
5.250 0.9356 0.01374 0.00785 -0.1006 0.0031 1.0000
5.500 0.9518 0.01634 0.01073 -0.0975 0.0042 1.0000
7.250 1.0596 0.04387 0.04046 -0.0807 0.0059 1.0000
7.500 1.0641 0.04739 0.04425 -0.0774 0.0059 1.0000
7.750 1.0659 0.05098 0.04809 -0.0740 0.0059 1.0000
8.000 1.0653 0.05461 0.05195 -0.0705 0.0059 1.0000
8.250 1.0616 0.05828 0.05582 -0.0670 0.0059 1.0000
8.500 1.0549 0.06188 0.05960 -0.0635 0.0059 1.0000
8.750 1.0422 0.06498 0.06285 -0.0592 0.0058 1.0000
9.000 1.0262 0.06802 0.06602 -0.0551 0.0058 1.0000
9.250 1.0087 0.07151 0.06963 -0.0521 0.0058 1.0000
9.500 0.9902 0.07553 0.07377 -0.0503 0.0058 1.0000
9.750 0.9715 0.08011 0.07847 -0.0499 0.0058 1.0000
10.000 0.9518 0.08556 0.08401 -0.0510 0.0058 1.0000
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Polar data table (+)
Polar graphs
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