MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) (marske3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) (marske3-il) Reynolds number: 100,000 Max Cl/Cd: 30.38 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske3-il-100000.txt Download as CSV file: xf-marske3-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5052 0.10215 0.09727 -0.0016 1.0000 0.1225
-9.750 -0.5218 0.09776 0.09296 -0.0062 1.0000 0.1276
-9.500 -0.5705 0.09233 0.08758 -0.0142 1.0000 0.1291
-9.250 -0.5259 0.08897 0.08428 -0.0086 1.0000 0.1346
-9.000 -0.5293 0.08517 0.08052 -0.0100 1.0000 0.1396
-8.750 -0.5630 0.08098 0.07634 -0.0124 1.0000 0.1429
-8.500 -0.6174 0.07929 0.07448 -0.0107 1.0000 0.1451
-8.250 -0.5805 0.07378 0.06919 -0.0101 1.0000 0.1507
-8.000 -0.5865 0.07102 0.06640 -0.0088 1.0000 0.1576
-7.750 -0.6082 0.06761 0.06287 -0.0070 1.0000 0.1642
-7.500 -0.5917 0.06477 0.06011 -0.0055 1.0000 0.1724
-7.250 -0.5971 0.06164 0.05694 -0.0034 1.0000 0.1827
-7.000 -0.6009 0.05920 0.05441 -0.0009 1.0000 0.1970
-6.750 -0.5998 0.05696 0.05213 0.0017 1.0000 0.2124
-6.250 -0.5824 0.05185 0.04717 0.0068 1.0000 0.2481
-5.500 -0.5520 0.03521 0.02777 0.0158 1.0000 0.0959
-5.250 -0.5377 0.03339 0.02513 0.0201 1.0000 0.0861
-5.000 -0.5212 0.03109 0.02268 0.0223 1.0000 0.0857
-4.750 -0.5054 0.02912 0.02057 0.0245 1.0000 0.0852
-4.500 -0.4921 0.02749 0.01883 0.0270 1.0000 0.0843
-4.250 -0.4824 0.02634 0.01755 0.0298 1.0000 0.0838
-4.000 -0.4396 0.02490 0.01584 0.0271 0.9910 0.0853
-3.750 -0.3813 0.02280 0.01369 0.0217 0.9777 0.0880
-3.500 -0.3239 0.02112 0.01212 0.0165 0.9626 0.0920
-3.250 -0.2673 0.01987 0.01089 0.0116 0.9454 0.0991
-3.000 -0.2175 0.01839 0.00961 0.0079 0.9244 0.1065
-2.750 -0.1760 0.01740 0.00868 0.0060 0.8958 0.1202
-2.500 -0.1406 0.01639 0.00781 0.0055 0.8644 0.1518
-2.250 0.1774 0.01756 0.01096 -0.0340 0.7802 1.0000
-2.000 0.1998 0.01756 0.01058 -0.0328 0.7302 1.0000
-1.750 0.2192 0.01758 0.01029 -0.0312 0.6863 1.0000
-1.500 0.2378 0.01755 0.01002 -0.0295 0.6411 1.0000
-1.250 0.2566 0.01752 0.00971 -0.0278 0.5978 1.0000
-1.000 0.2759 0.01753 0.00941 -0.0262 0.5573 1.0000
-0.750 0.2958 0.01760 0.00917 -0.0249 0.5229 1.0000
-0.500 0.3161 0.01773 0.00902 -0.0236 0.4946 1.0000
-0.250 0.3368 0.01787 0.00893 -0.0225 0.4716 1.0000
0.000 0.3578 0.01804 0.00887 -0.0214 0.4526 1.0000
0.250 0.3790 0.01822 0.00888 -0.0204 0.4360 1.0000
0.500 0.4006 0.01841 0.00895 -0.0194 0.4219 1.0000
0.750 0.4222 0.01863 0.00905 -0.0185 0.4094 1.0000
1.000 0.4439 0.01889 0.00913 -0.0175 0.3989 1.0000
1.250 0.4656 0.01910 0.00930 -0.0166 0.3881 1.0000
1.500 0.4873 0.01938 0.00950 -0.0157 0.3789 1.0000
1.750 0.5091 0.01964 0.00970 -0.0148 0.3704 1.0000
2.000 0.5310 0.01999 0.00999 -0.0139 0.3633 1.0000
2.250 0.5528 0.02029 0.01030 -0.0130 0.3558 1.0000
2.500 0.5748 0.02070 0.01055 -0.0121 0.3498 1.0000
2.750 0.5959 0.02103 0.01102 -0.0111 0.3425 1.0000
3.000 0.6176 0.02138 0.01131 -0.0102 0.3364 1.0000
3.250 0.6392 0.02188 0.01180 -0.0093 0.3315 1.0000
3.500 0.6601 0.02235 0.01241 -0.0083 0.3260 1.0000
3.750 0.6814 0.02281 0.01287 -0.0073 0.3212 1.0000
4.000 0.7031 0.02338 0.01333 -0.0064 0.3171 1.0000
4.250 0.7223 0.02396 0.01416 -0.0052 0.3118 1.0000
4.500 0.7422 0.02452 0.01480 -0.0041 0.3069 1.0000
4.750 0.7626 0.02510 0.01537 -0.0030 0.3031 1.0000
5.000 0.7824 0.02594 0.01622 -0.0019 0.2998 1.0000
5.250 0.7987 0.02681 0.01738 -0.0004 0.2954 1.0000
5.500 0.8164 0.02755 0.01825 0.0010 0.2910 1.0000
5.750 0.8356 0.02820 0.01889 0.0023 0.2872 1.0000
6.000 0.8550 0.02912 0.01975 0.0034 0.2840 1.0000
6.250 0.8656 0.03037 0.02139 0.0056 0.2797 1.0000
6.500 0.8793 0.03139 0.02260 0.0074 0.2753 1.0000
6.750 0.8974 0.03202 0.02322 0.0089 0.2714 1.0000
7.000 0.9172 0.03284 0.02394 0.0100 0.2681 1.0000
7.250 0.9201 0.03464 0.02617 0.0129 0.2639 1.0000
7.500 0.9267 0.03619 0.02796 0.0154 0.2597 1.0000
7.750 0.9408 0.03714 0.02897 0.0172 0.2561 1.0000
8.000 0.9634 0.03758 0.02930 0.0182 0.2528 1.0000
8.250 0.9616 0.03989 0.03192 0.0213 0.2491 1.0000
8.500 0.9510 0.04273 0.03511 0.0249 0.2449 1.0000
8.750 0.9529 0.04465 0.03718 0.0274 0.2412 1.0000
9.000 0.9771 0.04494 0.03741 0.0284 0.2381 1.0000
9.250 0.9955 0.04613 0.03857 0.0295 0.2350 1.0000
9.500 0.9244 0.05362 0.04658 0.0354 0.2324 1.0000
9.750 0.7058 0.08107 0.07406 0.0293 0.2350 1.0000
10.000 0.6822 0.08888 0.08186 0.0264 0.2353 1.0000
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Polar data table (+)
Polar graphs
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