MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Reynolds number: 200,000 Max Cl/Cd: 36.07 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske5-il-200000.txt Download as CSV file: xf-marske5-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE MONARCH AIRFOIL (NACA 43012A)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5072 0.09228 0.08883 -0.0054 1.0000 0.0525
-9.750 -0.5202 0.08599 0.08257 -0.0111 1.0000 0.0536
-9.500 -0.5507 0.07939 0.07591 -0.0165 1.0000 0.0545
-9.250 -0.5908 0.07563 0.07199 -0.0151 1.0000 0.0550
-9.000 -0.6305 0.07317 0.06918 -0.0109 1.0000 0.0554
-8.750 -0.6280 0.06792 0.06396 -0.0101 1.0000 0.0560
-8.500 -0.6083 0.06489 0.06111 -0.0099 1.0000 0.0569
-8.250 -0.6011 0.06249 0.05872 -0.0084 1.0000 0.0580
-8.000 -0.5974 0.06004 0.05622 -0.0065 1.0000 0.0600
-7.750 -0.6284 0.06010 0.05539 0.0010 1.0000 0.0643
-7.500 -0.6110 0.05360 0.04920 0.0003 1.0000 0.0655
-7.250 -0.5976 0.05099 0.04666 0.0016 1.0000 0.0667
-7.000 -0.5868 0.04883 0.04448 0.0035 1.0000 0.0686
-6.500 -0.5796 0.04409 0.03922 0.0106 1.0000 0.0765
-6.250 -0.5652 0.04189 0.03711 0.0122 1.0000 0.0784
-6.000 -0.5533 0.04033 0.03546 0.0148 1.0000 0.0825
-5.750 -0.5502 0.03831 0.03315 0.0189 1.0000 0.0888
-5.500 -0.5248 0.03610 0.03101 0.0184 0.9929 0.0927
-5.250 -0.4873 0.03360 0.02832 0.0157 0.9691 0.1050
-5.000 -0.4462 0.02716 0.02042 0.0176 0.9418 0.0655
-4.750 -0.3957 0.02331 0.01613 0.0146 0.9058 0.0575
-4.500 -0.3482 0.02155 0.01410 0.0115 0.8541 0.0585
-4.250 -0.3136 0.02011 0.01230 0.0113 0.8088 0.0583
-4.000 -0.2853 0.01919 0.01113 0.0121 0.7722 0.0592
-3.750 -0.2595 0.01860 0.01034 0.0133 0.7393 0.0615
-3.500 -0.2336 0.01801 0.00952 0.0145 0.7058 0.0631
-3.250 -0.2083 0.01748 0.00879 0.0158 0.6653 0.0642
-3.000 -0.1841 0.01653 0.00777 0.0170 0.6043 0.0665
-2.750 -0.1648 0.01633 0.00717 0.0191 0.4914 0.0693
-2.500 -0.1449 0.01631 0.00669 0.0209 0.4025 0.0719
-2.250 -0.1232 0.01620 0.00632 0.0224 0.3668 0.0742
-2.000 -0.1033 0.01581 0.00586 0.0242 0.3475 0.0784
-1.750 -0.0816 0.01566 0.00561 0.0256 0.3332 0.0839
-1.250 -0.0388 0.01526 0.00508 0.0288 0.3124 0.1046
-1.000 -0.0402 0.01343 0.00465 0.0340 0.3073 0.4480
-0.750 0.0942 0.01592 0.00835 0.0199 0.2883 0.9281
-0.500 0.1998 0.01722 0.00937 0.0066 0.2757 0.9578
-0.250 0.2775 0.01746 0.00932 -0.0026 0.2671 0.9755
0.000 0.3104 0.01746 0.00927 -0.0036 0.2622 0.9810
0.250 0.3435 0.01741 0.00913 -0.0048 0.2578 0.9845
0.500 0.3777 0.01741 0.00900 -0.0062 0.2541 0.9878
0.750 0.4094 0.01766 0.00913 -0.0071 0.2504 0.9913
1.000 0.4426 0.01762 0.00910 -0.0083 0.2474 0.9947
1.250 0.4771 0.01758 0.00905 -0.0097 0.2442 0.9978
1.500 0.5083 0.01764 0.00906 -0.0106 0.2411 1.0000
1.750 0.5306 0.01782 0.00918 -0.0096 0.2384 1.0000
2.000 0.5529 0.01809 0.00937 -0.0088 0.2360 1.0000
2.250 0.5751 0.01861 0.00984 -0.0079 0.2336 1.0000
2.500 0.5974 0.01880 0.01009 -0.0069 0.2318 1.0000
2.750 0.6197 0.01906 0.01040 -0.0060 0.2299 1.0000
3.000 0.6419 0.01936 0.01074 -0.0051 0.2281 1.0000
3.250 0.6640 0.01968 0.01109 -0.0041 0.2261 1.0000
3.500 0.6860 0.02001 0.01145 -0.0032 0.2243 1.0000
3.750 0.7080 0.02036 0.01181 -0.0022 0.2226 1.0000
4.000 0.7300 0.02073 0.01217 -0.0013 0.2210 1.0000
4.250 0.7518 0.02120 0.01261 -0.0004 0.2193 1.0000
4.500 0.7731 0.02204 0.01346 0.0004 0.2173 1.0000
4.750 0.7940 0.02242 0.01397 0.0016 0.2160 1.0000
5.000 0.8146 0.02292 0.01460 0.0027 0.2145 1.0000
5.250 0.8348 0.02350 0.01531 0.0038 0.2130 1.0000
5.500 0.8547 0.02410 0.01602 0.0050 0.2114 1.0000
5.750 0.8744 0.02464 0.01664 0.0062 0.2095 1.0000
6.000 0.8944 0.02505 0.01708 0.0073 0.2076 1.0000
6.250 0.9142 0.02547 0.01753 0.0085 0.2058 1.0000
6.500 0.9341 0.02590 0.01794 0.0097 0.2040 1.0000
6.750 0.9531 0.02685 0.01885 0.0108 0.2023 1.0000
7.000 0.9684 0.02774 0.01994 0.0125 0.2006 1.0000
7.250 0.9826 0.02855 0.02098 0.0144 0.1987 1.0000
7.500 0.9966 0.02947 0.02209 0.0162 0.1967 1.0000
7.750 1.0106 0.03039 0.02314 0.0180 0.1948 1.0000
8.000 1.0252 0.03118 0.02403 0.0198 0.1931 1.0000
8.250 1.0412 0.03180 0.02470 0.0215 0.1916 1.0000
8.500 1.0581 0.03229 0.02520 0.0230 0.1901 1.0000
8.750 1.0762 0.03275 0.02562 0.0245 0.1886 1.0000
9.000 1.0911 0.03402 0.02688 0.0259 0.1870 1.0000
9.250 1.0911 0.03557 0.02876 0.0293 0.1851 1.0000
9.500 1.0871 0.03745 0.03096 0.0330 0.1828 1.0000
9.750 1.0844 0.03929 0.03302 0.0363 0.1807 1.0000
10.000 1.0860 0.04075 0.03462 0.0392 0.1788 1.0000
10.250 1.0954 0.04161 0.03554 0.0413 0.1772 1.0000
10.500 1.1133 0.04192 0.03583 0.0427 0.1759 1.0000
10.750 1.1288 0.04241 0.03632 0.0442 0.1746 1.0000
11.000 1.1487 0.04299 0.03685 0.0452 0.1734 1.0000
11.250 1.1344 0.04592 0.03996 0.0487 0.1718 1.0000
11.500 0.5793 0.12400 0.11876 0.0162 0.1767 1.0000
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Polar data table (+)
Polar graphs
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