MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 50,000 Max Cl/Cd: 14.62 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh93-il-50000.txt Download as CSV file: xf-mh93-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6131 0.10080 0.09437 -0.0108 1.0000 0.1254
-11.000 -0.5925 0.09740 0.09099 -0.0095 1.0000 0.1229
-10.750 -0.6879 0.08231 0.07578 -0.0214 1.0000 0.1129
-10.500 -0.7098 0.07706 0.07040 -0.0224 1.0000 0.1104
-10.250 -0.7223 0.07246 0.06573 -0.0223 1.0000 0.1087
-10.000 -0.7433 0.06826 0.06139 -0.0209 1.0000 0.1069
-9.750 -0.7652 0.06428 0.05718 -0.0187 1.0000 0.1050
-9.500 -0.7835 0.06019 0.05273 -0.0161 1.0000 0.1029
-9.250 -0.8005 0.05633 0.04830 -0.0129 1.0000 0.1007
-9.000 -0.8066 0.05333 0.04470 -0.0097 1.0000 0.0994
-8.750 -0.7943 0.04974 0.04091 -0.0085 1.0000 0.1002
-8.500 -0.7739 0.04682 0.03801 -0.0080 1.0000 0.1032
-8.250 -0.7589 0.04423 0.03520 -0.0067 1.0000 0.1058
-8.000 -0.7433 0.04171 0.03235 -0.0052 1.0000 0.1086
-7.750 -0.7264 0.03934 0.02954 -0.0035 1.0000 0.1115
-7.500 -0.6980 0.03679 0.02715 -0.0038 1.0000 0.1176
-7.250 -0.6800 0.03514 0.02522 -0.0022 1.0000 0.1255
-7.000 -0.6526 0.03313 0.02343 -0.0020 1.0000 0.1380
-6.750 -0.6339 0.03160 0.02204 -0.0005 1.0000 0.1542
-6.500 -0.6210 0.03016 0.02098 0.0017 1.0000 0.1769
-6.250 -0.6207 0.02897 0.02011 0.0056 1.0000 0.2073
-6.000 -0.6290 0.02775 0.01935 0.0106 1.0000 0.2520
-5.750 -0.6468 0.02634 0.01880 0.0170 1.0000 0.3260
-5.500 -0.6673 0.02527 0.01866 0.0247 1.0000 0.4363
-5.250 -0.6762 0.02518 0.01906 0.0314 1.0000 0.5281
-5.000 -0.6741 0.02577 0.01991 0.0371 1.0000 0.5963
-4.750 -0.6424 0.02796 0.02218 0.0398 0.9935 0.6647
-4.500 -0.5184 0.03499 0.02882 0.0344 0.9794 0.7339
-4.250 -0.3414 0.03923 0.03231 0.0166 0.9678 0.7719
-4.000 -0.2308 0.03971 0.03235 0.0035 0.9526 0.8026
-3.750 -0.1004 0.03918 0.03140 -0.0133 0.9379 0.8292
-3.500 -0.0260 0.03843 0.03039 -0.0220 0.9188 0.8538
-3.250 0.0444 0.03751 0.02924 -0.0296 0.8979 0.8748
-3.000 0.0955 0.03678 0.02833 -0.0338 0.8759 0.8944
-2.750 0.1340 0.03622 0.02763 -0.0361 0.8528 0.9133
-2.500 0.1711 0.03560 0.02687 -0.0382 0.8314 0.9321
-2.250 0.2069 0.03494 0.02609 -0.0401 0.8111 0.9505
-2.000 0.2427 0.03428 0.02529 -0.0423 0.7918 0.9692
-1.750 0.2873 0.03314 0.02402 -0.0461 0.7720 0.9872
-1.500 0.3243 0.03227 0.02303 -0.0488 0.7534 1.0000
-1.250 0.3381 0.03230 0.02300 -0.0478 0.7369 1.0000
-1.000 0.3523 0.03239 0.02302 -0.0469 0.7210 1.0000
-0.750 0.3669 0.03255 0.02312 -0.0460 0.7061 1.0000
-0.500 0.3808 0.03268 0.02318 -0.0446 0.6924 1.0000
-0.250 0.3942 0.03272 0.02311 -0.0427 0.6800 1.0000
0.000 0.4104 0.03310 0.02348 -0.0423 0.6651 1.0000
0.250 0.4260 0.03350 0.02384 -0.0414 0.6518 1.0000
0.500 0.4398 0.03348 0.02370 -0.0390 0.6420 1.0000
0.750 0.4563 0.03413 0.02436 -0.0388 0.6274 1.0000
1.000 0.4720 0.03477 0.02500 -0.0382 0.6151 1.0000
1.250 0.4872 0.03480 0.02493 -0.0359 0.6058 1.0000
1.500 0.5026 0.03583 0.02600 -0.0359 0.5922 1.0000
1.750 0.5178 0.03642 0.02657 -0.0346 0.5822 1.0000
2.000 0.5329 0.03705 0.02718 -0.0334 0.5715 1.0000
2.250 0.5458 0.03829 0.02847 -0.0328 0.5600 1.0000
2.500 0.5622 0.03846 0.02857 -0.0307 0.5518 1.0000
2.750 0.5707 0.04045 0.03065 -0.0307 0.5401 1.0000
3.000 0.5892 0.04031 0.03042 -0.0281 0.5329 1.0000
3.250 0.5897 0.04315 0.03342 -0.0281 0.5212 1.0000
3.500 0.6103 0.04288 0.03306 -0.0256 0.5148 1.0000
3.750 0.5970 0.04690 0.03723 -0.0252 0.5036 1.0000
4.000 0.6197 0.04656 0.03683 -0.0228 0.4974 1.0000
4.250 0.5819 0.05227 0.04265 -0.0214 0.4883 1.0000
4.500 0.5853 0.05375 0.04413 -0.0191 0.4816 1.0000
4.750 0.5728 0.05653 0.04689 -0.0166 0.4757 1.0000
5.000 0.4956 0.06259 0.05290 -0.0116 0.4731 1.0000
5.250 0.4472 0.06592 0.05614 -0.0062 0.4725 1.0000
5.500 0.4166 0.06890 0.05905 -0.0026 0.4726 1.0000
5.750 0.3965 0.07172 0.06180 -0.0001 0.4735 1.0000
6.000 0.3856 0.07449 0.06452 0.0016 0.4750 1.0000
6.250 0.3810 0.07747 0.06750 0.0024 0.4796 1.0000
6.500 0.2673 0.08579 0.07577 0.0006 0.5901 1.0000
6.750 0.2774 0.08833 0.07828 0.0010 0.5842 1.0000
7.000 0.2854 0.08984 0.07976 0.0020 0.5714 1.0000
7.250 0.2867 0.09169 0.08159 0.0030 0.5631 1.0000
7.500 0.3039 0.09408 0.08398 0.0030 0.5529 1.0000
7.750 0.3063 0.09617 0.08605 0.0037 0.5462 1.0000
8.000 0.3219 0.09844 0.08832 0.0038 0.5347 1.0000
8.250 0.3214 0.10024 0.09010 0.0046 0.5263 1.0000
8.500 0.3421 0.10308 0.09295 0.0043 0.5163 1.0000
8.750 0.3411 0.10504 0.09489 0.0048 0.5097 1.0000
9.000 0.3579 0.10760 0.09748 0.0047 0.4988 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 93 15.98% (mh93-il)