NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M13 AIRFOIL (m13-il) Reynolds number: 50,000 Max Cl/Cd: 38.81 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m13-il-50000.txt Download as CSV file: xf-m13-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M13 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4758 0.12173 0.11501 0.0052 1.0000 0.1101
-8.750 -0.4798 0.12089 0.11427 0.0015 1.0000 0.1121
-8.500 -0.4735 0.11646 0.10990 0.0004 1.0000 0.1140
-8.250 -0.4592 0.11113 0.10455 0.0015 1.0000 0.1196
-8.000 -0.4573 0.10865 0.10213 -0.0007 1.0000 0.1242
-7.750 -0.4621 0.10787 0.10147 -0.0064 1.0000 0.1264
-7.500 -0.4489 0.10182 0.09541 -0.0042 1.0000 0.1302
-7.250 -0.4406 0.09826 0.09188 -0.0054 1.0000 0.1362
-7.000 -0.4377 0.09720 0.09085 -0.0139 1.0000 0.1407
-6.750 -0.4253 0.09123 0.08493 -0.0103 1.0000 0.1459
-6.500 -0.4166 0.08930 0.08300 -0.0169 1.0000 0.1544
-6.250 -0.4057 0.08422 0.07798 -0.0144 1.0000 0.1623
-5.750 -0.3810 0.07852 0.07225 -0.0234 1.0000 0.1834
-5.500 -0.3693 0.07414 0.06792 -0.0219 1.0000 0.1950
-5.250 -0.3567 0.07035 0.06416 -0.0224 1.0000 0.2069
-5.000 -0.3407 0.06780 0.06153 -0.0267 1.0000 0.2258
-4.750 -0.3300 0.06367 0.05745 -0.0251 1.0000 0.2422
-4.500 -0.3179 0.06072 0.05451 -0.0255 1.0000 0.2692
-4.250 -0.3114 0.05729 0.05121 -0.0225 1.0000 0.3008
-4.000 -0.3083 0.05438 0.04843 -0.0187 1.0000 0.3452
-3.750 -0.3108 0.05165 0.04587 -0.0131 1.0000 0.4006
-3.500 -0.3151 0.04914 0.04351 -0.0070 1.0000 0.4556
-3.250 -0.3196 0.04658 0.04112 0.0000 1.0000 0.5018
-3.000 -0.3231 0.04422 0.03889 0.0061 1.0000 0.5450
-2.750 -0.3220 0.04203 0.03676 0.0096 1.0000 0.5831
-2.500 -0.3185 0.03959 0.03436 0.0136 1.0000 0.6136
-2.250 -0.3064 0.03718 0.03197 0.0145 1.0000 0.6352
-2.000 -0.2834 0.03470 0.02943 0.0119 1.0000 0.6486
-1.750 -0.1284 0.03373 0.02656 -0.0307 1.0000 0.3918
-1.500 -0.0673 0.03335 0.02486 -0.0379 1.0000 0.2336
-1.250 -0.0349 0.03215 0.02302 -0.0389 1.0000 0.1926
-1.000 -0.0066 0.03096 0.02135 -0.0394 1.0000 0.1745
-0.750 0.0201 0.03036 0.02025 -0.0397 1.0000 0.1685
-0.500 0.0445 0.02965 0.01927 -0.0401 1.0000 0.1687
-0.250 0.0819 0.02867 0.01805 -0.0427 0.9954 0.1664
0.000 0.1366 0.02772 0.01673 -0.0479 0.9840 0.1660
0.250 0.1901 0.02702 0.01567 -0.0526 0.9721 0.1713
0.500 0.2400 0.02635 0.01491 -0.0569 0.9599 0.1862
0.750 0.2876 0.02549 0.01429 -0.0610 0.9477 0.2423
1.000 0.3366 0.02326 0.01347 -0.0644 0.9360 1.0000
1.250 0.3815 0.02384 0.01367 -0.0682 0.9211 1.0000
1.500 0.4252 0.02441 0.01403 -0.0718 0.9065 1.0000
1.750 0.4663 0.02498 0.01449 -0.0748 0.8919 1.0000
2.000 0.5030 0.02558 0.01502 -0.0769 0.8773 1.0000
2.250 0.5370 0.02622 0.01561 -0.0784 0.8629 1.0000
2.500 0.5687 0.02688 0.01627 -0.0795 0.8486 1.0000
2.750 0.5985 0.02759 0.01703 -0.0801 0.8345 1.0000
3.000 0.6267 0.02832 0.01780 -0.0804 0.8205 1.0000
3.250 0.6537 0.02909 0.01862 -0.0805 0.8068 1.0000
3.500 0.6799 0.02988 0.01949 -0.0803 0.7931 1.0000
3.750 0.7054 0.03070 0.02045 -0.0801 0.7795 1.0000
4.000 0.7304 0.03152 0.02139 -0.0796 0.7660 1.0000
4.250 0.7550 0.03236 0.02236 -0.0791 0.7525 1.0000
4.500 0.7794 0.03321 0.02335 -0.0784 0.7390 1.0000
4.750 0.8033 0.03406 0.02439 -0.0776 0.7254 1.0000
5.000 0.8268 0.03495 0.02552 -0.0767 0.7116 1.0000
5.250 0.8495 0.03589 0.02668 -0.0758 0.6976 1.0000
5.500 0.8707 0.03697 0.02799 -0.0747 0.6830 1.0000
5.750 0.8903 0.03819 0.02948 -0.0736 0.6678 1.0000
6.000 0.9091 0.03949 0.03107 -0.0725 0.6519 1.0000
6.250 0.9540 0.03146 0.02328 -0.0593 0.5943 1.0000
6.500 0.9733 0.02508 0.01667 -0.0469 0.5016 1.0000
6.750 0.9679 0.02521 0.01530 -0.0385 0.2284 1.0000
7.000 0.9689 0.02909 0.01800 -0.0359 0.1429 1.0000
7.250 0.9787 0.03166 0.02032 -0.0337 0.1200 1.0000
7.500 0.9944 0.03388 0.02247 -0.0314 0.1089 1.0000
7.750 1.0197 0.03600 0.02463 -0.0297 0.1006 1.0000
8.000 1.0497 0.03847 0.02718 -0.0286 0.0931 1.0000
8.250 1.0793 0.04134 0.03007 -0.0280 0.0872 1.0000
8.500 1.1092 0.04519 0.03409 -0.0275 0.0858 1.0000
8.750 1.1327 0.04887 0.03820 -0.0264 0.0860 1.0000
9.000 1.1491 0.05231 0.04235 -0.0246 0.0874 1.0000
9.250 1.1580 0.05640 0.04716 -0.0227 0.0890 1.0000
9.500 1.1621 0.06084 0.05225 -0.0210 0.0904 1.0000
9.750 1.1614 0.06549 0.05741 -0.0195 0.0918 1.0000
10.000 1.1549 0.07029 0.06263 -0.0181 0.0935 1.0000
10.250 1.1462 0.07520 0.06784 -0.0170 0.0951 1.0000
10.500 1.1387 0.08030 0.07315 -0.0164 0.0967 1.0000
10.750 1.1357 0.08555 0.07857 -0.0160 0.0991 1.0000
11.000 1.0623 0.09137 0.08470 -0.0190 0.1033 1.0000
11.250 1.0264 0.10015 0.09354 -0.0250 0.1071 1.0000
11.500 1.0207 0.10682 0.10022 -0.0270 0.1104 1.0000
11.750 0.9637 0.12361 0.11692 -0.0425 0.1186 1.0000
12.000 0.8292 0.11504 0.10864 -0.0227 0.1104 1.0000
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Polar data table (+)
Polar graphs
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