MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Reynolds number: 100,000 Max Cl/Cd: 28.85 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske2-il-100000.txt Download as CSV file: xf-marske2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYB
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 -0.5250 0.09579 0.09089 -0.0056 1.0000 0.1244
-9.500 -0.5691 0.08946 0.08461 -0.0142 1.0000 0.1269
-9.250 -0.6086 0.08632 0.08143 -0.0144 1.0000 0.1275
-9.000 -0.5604 0.08128 0.07654 -0.0132 1.0000 0.1335
-8.750 -0.5675 0.07797 0.07324 -0.0129 1.0000 0.1377
-8.500 -0.5979 0.07484 0.07006 -0.0118 1.0000 0.1416
-8.250 -0.6586 0.07535 0.07002 -0.0079 1.0000 0.1448
-8.000 -0.6049 0.06775 0.06297 -0.0093 1.0000 0.1516
-7.750 -0.6492 0.06859 0.06320 -0.0048 1.0000 0.1615
-7.500 -0.6114 0.06166 0.05678 -0.0058 1.0000 0.1679
-7.250 -0.6224 0.05913 0.05407 -0.0031 1.0000 0.1809
-7.000 -0.6231 0.05712 0.05196 -0.0004 1.0000 0.1966
-5.500 -0.5596 0.03680 0.02959 0.0150 1.0000 0.1246
-5.250 -0.5427 0.03364 0.02592 0.0181 1.0000 0.1072
-5.000 -0.5290 0.03248 0.02401 0.0224 1.0000 0.0977
-4.750 -0.5128 0.03008 0.02156 0.0244 1.0000 0.0959
-4.500 -0.5006 0.02865 0.01997 0.0271 1.0000 0.0957
-4.250 -0.4902 0.02772 0.01885 0.0300 1.0000 0.0964
-4.000 -0.4776 0.02685 0.01779 0.0324 0.9998 0.0969
-3.750 -0.4194 0.02475 0.01549 0.0271 0.9873 0.0979
-3.500 -0.3639 0.02272 0.01358 0.0219 0.9751 0.1030
-3.250 -0.3077 0.02133 0.01220 0.0171 0.9614 0.1073
-3.000 -0.2518 0.01994 0.01090 0.0123 0.9468 0.1144
-2.750 -0.2020 0.01862 0.00978 0.0087 0.9289 0.1229
-2.500 -0.1592 0.01751 0.00876 0.0066 0.9066 0.1365
-2.250 -0.1250 0.01657 0.00788 0.0062 0.8787 0.1597
-2.000 0.0410 0.01772 0.01179 -0.0071 0.8457 0.9350
-1.750 0.2100 0.01715 0.01038 -0.0303 0.7383 1.0000
-1.500 0.2277 0.01711 0.00999 -0.0283 0.6794 1.0000
-1.250 0.2435 0.01706 0.00960 -0.0260 0.6103 1.0000
-1.000 0.2604 0.01713 0.00918 -0.0240 0.5413 1.0000
-0.750 0.2790 0.01730 0.00891 -0.0226 0.4911 1.0000
-0.500 0.2983 0.01748 0.00876 -0.0213 0.4576 1.0000
-0.250 0.3183 0.01767 0.00867 -0.0201 0.4342 1.0000
0.000 0.3388 0.01784 0.00864 -0.0191 0.4157 1.0000
0.250 0.3595 0.01804 0.00863 -0.0180 0.4012 1.0000
0.500 0.3805 0.01823 0.00867 -0.0170 0.3879 1.0000
0.750 0.4017 0.01843 0.00878 -0.0161 0.3761 1.0000
1.000 0.4231 0.01871 0.00888 -0.0151 0.3670 1.0000
1.250 0.4447 0.01895 0.00909 -0.0142 0.3578 1.0000
1.500 0.4665 0.01931 0.00928 -0.0133 0.3507 1.0000
1.750 0.4882 0.01956 0.00958 -0.0123 0.3429 1.0000
2.000 0.5100 0.01991 0.00979 -0.0114 0.3363 1.0000
2.250 0.5317 0.02028 0.01018 -0.0105 0.3297 1.0000
2.500 0.5534 0.02064 0.01054 -0.0096 0.3237 1.0000
2.750 0.5755 0.02109 0.01088 -0.0087 0.3188 1.0000
3.000 0.5972 0.02159 0.01146 -0.0078 0.3141 1.0000
3.250 0.6185 0.02204 0.01198 -0.0068 0.3089 1.0000
3.500 0.6400 0.02249 0.01241 -0.0058 0.3041 1.0000
3.750 0.6617 0.02317 0.01300 -0.0049 0.3000 1.0000
4.000 0.6816 0.02375 0.01380 -0.0038 0.2956 1.0000
4.250 0.7020 0.02440 0.01456 -0.0027 0.2916 1.0000
4.500 0.7224 0.02504 0.01523 -0.0016 0.2879 1.0000
4.750 0.7431 0.02580 0.01593 -0.0006 0.2845 1.0000
5.000 0.7609 0.02672 0.01707 0.0008 0.2807 1.0000
5.250 0.7782 0.02762 0.01818 0.0022 0.2767 1.0000
5.500 0.7962 0.02851 0.01918 0.0035 0.2733 1.0000
5.750 0.8154 0.02930 0.01999 0.0048 0.2700 1.0000
6.000 0.8349 0.03034 0.02096 0.0059 0.2669 1.0000
6.250 0.8462 0.03170 0.02267 0.0079 0.2634 1.0000
6.500 0.8576 0.03315 0.02439 0.0099 0.2600 1.0000
6.750 0.8708 0.03440 0.02581 0.0117 0.2566 1.0000
7.000 0.8880 0.03530 0.02672 0.0132 0.2534 1.0000
7.250 0.9079 0.03626 0.02758 0.0143 0.2505 1.0000
7.500 0.9108 0.03844 0.03010 0.0170 0.2476 1.0000
7.750 0.9076 0.04110 0.03313 0.0199 0.2448 1.0000
8.000 0.9043 0.04372 0.03603 0.0228 0.2418 1.0000
8.250 0.9069 0.04577 0.03822 0.0251 0.2388 1.0000
8.500 0.9300 0.04616 0.03855 0.0262 0.2357 1.0000
8.750 0.9575 0.04699 0.03922 0.0266 0.2330 1.0000
9.000 0.9156 0.05254 0.04525 0.0311 0.2314 1.0000
9.250 0.8365 0.06166 0.05467 0.0348 0.2314 1.0000
9.500 0.7568 0.07270 0.06575 0.0341 0.2337 1.0000
9.750 0.5798 0.10621 0.09919 0.0127 0.2845 1.0000
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Polar data table (+)
Polar graphs
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