MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 50,000 Max Cl/Cd: 33.03 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh24-il-50000-n5.txt Download as CSV file: xf-mh24-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4815 0.09954 0.09248 -0.0341 1.0000 0.0345
-9.250 -0.4836 0.09576 0.08877 -0.0351 1.0000 0.0339
-9.000 -0.4878 0.09182 0.08490 -0.0364 1.0000 0.0336
-8.750 -0.4936 0.08783 0.08099 -0.0378 1.0000 0.0328
-8.500 -0.5026 0.08392 0.07716 -0.0391 1.0000 0.0321
-8.250 -0.5163 0.08048 0.07379 -0.0388 1.0000 0.0320
-8.000 -0.5298 0.07738 0.07073 -0.0373 1.0000 0.0307
-7.750 -0.5415 0.07403 0.06738 -0.0359 1.0000 0.0304
-7.500 -0.5521 0.07072 0.06404 -0.0342 1.0000 0.0301
-7.250 -0.5617 0.06711 0.06033 -0.0322 1.0000 0.0288
-7.000 -0.5679 0.06394 0.05704 -0.0299 1.0000 0.0292
-6.750 -0.5725 0.06044 0.05336 -0.0275 1.0000 0.0286
-6.500 -0.5739 0.05721 0.04992 -0.0250 1.0000 0.0289
-6.250 -0.5729 0.05390 0.04635 -0.0225 1.0000 0.0286
-6.000 -0.5692 0.05072 0.04287 -0.0199 1.0000 0.0286
-5.750 -0.5630 0.04782 0.03966 -0.0175 1.0000 0.0296
-5.500 -0.5545 0.04487 0.03634 -0.0150 1.0000 0.0301
-5.250 -0.5434 0.04197 0.03303 -0.0126 1.0000 0.0301
-5.000 -0.5299 0.03917 0.02979 -0.0103 1.0000 0.0307
-4.750 -0.5136 0.03655 0.02670 -0.0082 1.0000 0.0308
-4.500 -0.4948 0.03408 0.02365 -0.0062 1.0000 0.0310
-4.250 -0.4736 0.03180 0.02094 -0.0045 1.0000 0.0319
-4.000 -0.4509 0.02986 0.01863 -0.0029 1.0000 0.0331
-3.750 -0.4268 0.02813 0.01655 -0.0015 1.0000 0.0352
-3.500 -0.4042 0.02664 0.01496 -0.0003 1.0000 0.0419
-3.250 -0.3801 0.02547 0.01351 0.0010 1.0000 0.0502
-3.000 -0.3566 0.02411 0.01213 0.0019 1.0000 0.0683
-2.750 -0.3350 0.02240 0.01076 0.0032 1.0000 0.1290
-2.500 -0.1351 0.02033 0.01089 -0.0253 1.0000 1.0000
-2.250 -0.1244 0.02020 0.01049 -0.0227 1.0000 1.0000
-2.000 -0.1133 0.02010 0.01016 -0.0201 1.0000 1.0000
-1.750 -0.1019 0.02003 0.00987 -0.0176 1.0000 1.0000
-1.500 -0.0901 0.01999 0.00963 -0.0152 1.0000 1.0000
-1.250 -0.0782 0.01998 0.00944 -0.0127 1.0000 1.0000
-1.000 -0.0660 0.01999 0.00924 -0.0103 1.0000 1.0000
-0.750 -0.0537 0.02003 0.00913 -0.0080 1.0000 1.0000
-0.500 -0.0412 0.02009 0.00907 -0.0057 1.0000 1.0000
-0.250 -0.0286 0.02018 0.00904 -0.0035 1.0000 1.0000
0.000 -0.0158 0.02030 0.00905 -0.0013 1.0000 1.0000
0.250 -0.0030 0.02045 0.00911 0.0008 1.0000 1.0000
0.500 0.0099 0.02063 0.00918 0.0029 1.0000 1.0000
0.750 0.0507 0.02107 0.00955 -0.0007 0.9908 1.0000
1.000 0.0935 0.02157 0.01000 -0.0046 0.9810 1.0000
1.250 0.1346 0.02198 0.01041 -0.0080 0.9701 1.0000
1.500 0.1748 0.02234 0.01079 -0.0112 0.9583 1.0000
1.750 0.2151 0.02265 0.01115 -0.0142 0.9457 1.0000
2.000 0.2552 0.02290 0.01149 -0.0171 0.9323 1.0000
2.500 0.3362 0.02317 0.01203 -0.0225 0.9032 1.0000
2.750 0.3694 0.02316 0.01216 -0.0236 0.8852 1.0000
3.000 0.4047 0.02306 0.01224 -0.0249 0.8664 1.0000
3.250 0.4404 0.02286 0.01223 -0.0260 0.8466 1.0000
3.500 0.4754 0.02254 0.01223 -0.0267 0.8246 1.0000
3.750 0.5069 0.02214 0.01207 -0.0265 0.7997 1.0000
4.000 0.5404 0.02165 0.01182 -0.0264 0.7719 1.0000
4.250 0.5741 0.02118 0.01166 -0.0262 0.7375 1.0000
4.500 0.6123 0.02069 0.01137 -0.0265 0.6928 1.0000
4.750 0.6499 0.02039 0.01112 -0.0267 0.6336 1.0000
5.000 0.6773 0.02055 0.01116 -0.0253 0.5640 1.0000
5.250 0.6960 0.02107 0.01147 -0.0228 0.4938 1.0000
5.500 0.7098 0.02179 0.01195 -0.0198 0.4269 1.0000
5.750 0.7210 0.02266 0.01256 -0.0167 0.3634 1.0000
6.000 0.7316 0.02363 0.01344 -0.0137 0.3031 1.0000
6.250 0.7419 0.02473 0.01431 -0.0108 0.2462 1.0000
6.500 0.7532 0.02596 0.01532 -0.0083 0.1959 1.0000
6.750 0.7654 0.02733 0.01649 -0.0060 0.1527 1.0000
7.000 0.7789 0.02887 0.01788 -0.0039 0.1221 1.0000
7.250 0.7936 0.03040 0.01937 -0.0019 0.0970 1.0000
7.500 0.8098 0.03208 0.02112 -0.0001 0.0802 1.0000
7.750 0.8285 0.03409 0.02317 0.0014 0.0696 1.0000
8.000 0.8442 0.03578 0.02505 0.0032 0.0589 1.0000
8.250 0.8637 0.03809 0.02773 0.0046 0.0513 1.0000
8.500 0.8814 0.04062 0.03045 0.0061 0.0471 1.0000
8.750 0.8975 0.04407 0.03424 0.0077 0.0444 1.0000
9.000 0.9050 0.04726 0.03802 0.0105 0.0416 1.0000
9.250 0.9077 0.04960 0.04069 0.0133 0.0373 1.0000
9.500 0.9095 0.05204 0.04315 0.0155 0.0342 1.0000
9.750 0.9046 0.05566 0.04730 0.0187 0.0334 1.0000
10.000 0.8959 0.05896 0.05097 0.0219 0.0331 1.0000
10.250 0.8813 0.06222 0.05453 0.0253 0.0329 1.0000
10.500 0.8638 0.06574 0.05829 0.0280 0.0326 1.0000
10.750 0.8482 0.06933 0.06208 0.0294 0.0328 1.0000
11.000 0.8285 0.07364 0.06657 0.0297 0.0328 1.0000
11.250 0.8112 0.07825 0.07130 0.0287 0.0330 1.0000
11.500 0.7930 0.08370 0.07670 0.0264 0.0332 1.0000
11.750 0.7782 0.08944 0.08250 0.0233 0.0335 1.0000
12.000 0.7622 0.09634 0.08943 0.0190 0.0337 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 24 9.01% (mh24-il)