MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Reynolds number: 100,000 Max Cl/Cd: 23.31 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske5-il-100000.txt Download as CSV file: xf-marske5-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5196 0.09702 0.09233 -0.0059 1.0000 0.1134
-9.500 -0.5636 0.09261 0.08789 -0.0111 1.0000 0.1142
-9.250 -0.6024 0.09065 0.08583 -0.0097 1.0000 0.1146
-9.000 -0.5185 0.08462 0.08007 -0.0077 1.0000 0.1218
-8.750 -0.5328 0.08087 0.07633 -0.0087 1.0000 0.1249
-8.500 -0.5635 0.07790 0.07332 -0.0078 1.0000 0.1281
-8.250 -0.6186 0.07810 0.07305 -0.0045 1.0000 0.1306
-8.000 -0.5749 0.07056 0.06596 -0.0055 1.0000 0.1352
-7.750 -0.5713 0.06793 0.06333 -0.0040 1.0000 0.1416
-7.500 -0.5934 0.06512 0.06026 -0.0015 1.0000 0.1492
-7.250 -0.5722 0.06202 0.05736 -0.0004 1.0000 0.1569
-7.000 -0.5780 0.05919 0.05442 0.0021 1.0000 0.1679
-6.750 -0.5836 0.05771 0.05273 0.0053 1.0000 0.1827
-6.500 -0.5633 0.05429 0.04956 0.0065 1.0000 0.1920
-6.250 -0.5585 0.05178 0.04705 0.0091 1.0000 0.2071
-6.000 -0.5532 0.04955 0.04485 0.0119 1.0000 0.2249
-4.750 -0.5196 0.03646 0.02943 0.0297 1.0000 0.1316
-4.500 -0.4648 0.03123 0.02350 0.0271 0.9875 0.0975
-4.250 -0.4112 0.02795 0.01986 0.0232 0.9709 0.0921
-4.000 -0.3578 0.02579 0.01744 0.0195 0.9501 0.0934
-3.750 -0.3031 0.02374 0.01514 0.0158 0.9242 0.0934
-3.500 -0.2494 0.02217 0.01340 0.0123 0.8872 0.0972
-3.250 -0.2045 0.02108 0.01205 0.0108 0.8381 0.0999
-3.000 -0.1692 0.01969 0.01066 0.0107 0.7837 0.1042
-2.750 -0.1443 0.01915 0.00995 0.0126 0.7261 0.1101
-2.500 -0.1234 0.01878 0.00934 0.0153 0.6510 0.1149
-2.250 -0.1075 0.01827 0.00850 0.0185 0.5475 0.1215
-2.000 -0.0888 0.01817 0.00793 0.0209 0.4751 0.1329
-1.750 0.2123 0.01954 0.01069 -0.0197 0.3678 1.0000
-1.500 0.2330 0.01968 0.01054 -0.0187 0.3580 1.0000
-1.250 0.2544 0.01976 0.01050 -0.0178 0.3485 1.0000
-1.000 0.2758 0.01996 0.01046 -0.0169 0.3413 1.0000
-0.750 0.2978 0.02014 0.01055 -0.0160 0.3347 1.0000
-0.500 0.3198 0.02034 0.01063 -0.0151 0.3285 1.0000
-0.250 0.3418 0.02065 0.01075 -0.0143 0.3234 1.0000
0.000 0.3640 0.02093 0.01098 -0.0134 0.3181 1.0000
0.250 0.3862 0.02118 0.01121 -0.0125 0.3127 1.0000
0.500 0.4084 0.02150 0.01142 -0.0116 0.3082 1.0000
0.750 0.4306 0.02205 0.01179 -0.0108 0.3040 1.0000
1.000 0.4530 0.02236 0.01220 -0.0099 0.3005 1.0000
1.250 0.4752 0.02277 0.01266 -0.0090 0.2971 1.0000
1.500 0.4975 0.02321 0.01311 -0.0082 0.2938 1.0000
1.750 0.5196 0.02370 0.01358 -0.0073 0.2908 1.0000
2.000 0.5417 0.02428 0.01410 -0.0064 0.2881 1.0000
2.250 0.5634 0.02506 0.01488 -0.0056 0.2854 1.0000
2.500 0.5846 0.02562 0.01563 -0.0046 0.2825 1.0000
2.750 0.6057 0.02628 0.01641 -0.0037 0.2795 1.0000
3.000 0.6266 0.02703 0.01727 -0.0028 0.2773 1.0000
3.250 0.6473 0.02781 0.01813 -0.0018 0.2751 1.0000
3.500 0.6677 0.02865 0.01901 -0.0008 0.2732 1.0000
3.750 0.6880 0.02954 0.01992 0.0001 0.2714 1.0000
4.000 0.7076 0.03065 0.02104 0.0012 0.2696 1.0000
4.250 0.7249 0.03204 0.02257 0.0023 0.2677 1.0000
4.500 0.7398 0.03337 0.02421 0.0036 0.2655 1.0000
4.750 0.7538 0.03501 0.02610 0.0050 0.2640 1.0000
5.000 0.7661 0.03688 0.02822 0.0064 0.2628 1.0000
5.250 0.7762 0.03895 0.03052 0.0079 0.2614 1.0000
5.500 0.7845 0.04106 0.03284 0.0095 0.2596 1.0000
5.750 0.7913 0.04323 0.03517 0.0112 0.2579 1.0000
6.000 0.7955 0.04563 0.03774 0.0130 0.2565 1.0000
6.250 0.7963 0.04832 0.04060 0.0150 0.2555 1.0000
6.500 0.7806 0.05260 0.04512 0.0172 0.2553 1.0000
6.750 0.7785 0.05525 0.04783 0.0193 0.2540 1.0000
7.000 0.7831 0.05737 0.04997 0.0213 0.2528 1.0000
7.250 0.7859 0.05998 0.05258 0.0232 0.2519 1.0000
7.500 0.7853 0.06329 0.05591 0.0249 0.2513 1.0000
7.750 0.4829 0.09549 0.08827 0.0115 0.2991 1.0000
8.000 0.4871 0.09753 0.09029 0.0121 0.2921 1.0000
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Polar data table (+)
Polar graphs
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