MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID) (marske4-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID) (marske4-il) Reynolds number: 100,000 Max Cl/Cd: 34.06 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske4-il-100000-n5.txt Download as CSV file: xf-marske4-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.83
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5425 0.09289 0.08810 -0.0104 1.0000 0.0548
-9.000 -0.5559 0.08933 0.08451 -0.0113 1.0000 0.0549
-8.750 -0.5678 0.08593 0.08103 -0.0114 1.0000 0.0550
-8.250 -0.5108 0.06243 0.05772 -0.0148 1.0000 0.0368
-7.750 -0.5623 0.06918 0.06414 -0.0099 1.0000 0.0560
-7.250 -0.5589 0.05528 0.04962 -0.0067 1.0000 0.0299
-7.000 -0.5512 0.05211 0.04631 -0.0051 1.0000 0.0296
-6.750 -0.5443 0.04855 0.04245 -0.0030 1.0000 0.0298
-6.500 -0.5371 0.04503 0.03849 -0.0003 1.0000 0.0301
-6.250 -0.5225 0.04323 0.03682 0.0007 1.0000 0.0313
-6.000 -0.5098 0.04063 0.03399 0.0028 1.0000 0.0316
-5.750 -0.4971 0.03756 0.03055 0.0054 1.0000 0.0313
-5.500 -0.4826 0.03490 0.02756 0.0078 1.0000 0.0312
-5.250 -0.4664 0.03264 0.02501 0.0100 1.0000 0.0314
-5.000 -0.4490 0.03066 0.02278 0.0121 1.0000 0.0317
-4.750 -0.4307 0.02905 0.02098 0.0140 1.0000 0.0328
-4.500 -0.4117 0.02756 0.01924 0.0159 1.0000 0.0346
-4.250 -0.3820 0.02575 0.01707 0.0160 0.9890 0.0359
-4.000 -0.3367 0.02369 0.01465 0.0132 0.9587 0.0370
-3.750 -0.2925 0.02214 0.01307 0.0101 0.9161 0.0396
-3.500 -0.2467 0.02090 0.01162 0.0073 0.8678 0.0434
-3.250 -0.2070 0.01968 0.01017 0.0059 0.8173 0.0457
-3.000 -0.1782 0.01893 0.00933 0.0062 0.7736 0.0499
-2.750 -0.1530 0.01837 0.00857 0.0075 0.7358 0.0535
-2.500 -0.1305 0.01775 0.00783 0.0091 0.7013 0.0570
-2.250 -0.1081 0.01734 0.00730 0.0106 0.6638 0.0630
-2.000 -0.0858 0.01694 0.00672 0.0123 0.6184 0.0685
-1.750 -0.0630 0.01666 0.00621 0.0137 0.5591 0.0781
-1.500 -0.0405 0.01645 0.00570 0.0152 0.4879 0.0928
-1.250 -0.0084 0.01396 0.00595 0.0156 0.4171 0.8288
-1.000 0.0601 0.01544 0.00684 0.0106 0.3616 0.9302
-0.750 0.1808 0.01646 0.00716 -0.0062 0.3214 0.9836
-0.500 0.2131 0.01654 0.00697 -0.0072 0.3088 0.9877
-0.250 0.2467 0.01658 0.00682 -0.0085 0.2976 0.9922
0.000 0.2820 0.01662 0.00666 -0.0101 0.2889 0.9972
0.250 0.3120 0.01670 0.00659 -0.0107 0.2814 1.0000
0.500 0.3340 0.01690 0.00659 -0.0097 0.2760 1.0000
0.750 0.3566 0.01702 0.00666 -0.0088 0.2701 1.0000
1.000 0.3790 0.01718 0.00673 -0.0078 0.2646 1.0000
1.250 0.4012 0.01741 0.00680 -0.0068 0.2600 1.0000
1.500 0.4237 0.01759 0.00693 -0.0059 0.2552 1.0000
1.750 0.4463 0.01778 0.00708 -0.0049 0.2506 1.0000
2.000 0.4687 0.01801 0.00723 -0.0040 0.2467 1.0000
2.250 0.4911 0.01828 0.00740 -0.0030 0.2436 1.0000
2.500 0.5135 0.01857 0.00764 -0.0020 0.2405 1.0000
2.750 0.5360 0.01884 0.00794 -0.0011 0.2373 1.0000
3.000 0.5583 0.01915 0.00825 -0.0001 0.2342 1.0000
3.250 0.5804 0.01946 0.00853 0.0009 0.2311 1.0000
3.500 0.6024 0.01978 0.00881 0.0019 0.2283 1.0000
3.750 0.6242 0.02018 0.00912 0.0029 0.2258 1.0000
4.000 0.6460 0.02054 0.00958 0.0040 0.2229 1.0000
4.250 0.6677 0.02096 0.01007 0.0050 0.2203 1.0000
4.500 0.6892 0.02140 0.01056 0.0061 0.2179 1.0000
4.750 0.7105 0.02184 0.01104 0.0072 0.2156 1.0000
5.000 0.7318 0.02230 0.01152 0.0083 0.2136 1.0000
5.250 0.7530 0.02275 0.01194 0.0094 0.2115 1.0000
5.500 0.7741 0.02328 0.01246 0.0105 0.2093 1.0000
5.750 0.7939 0.02385 0.01324 0.0117 0.2064 1.0000
6.000 0.8138 0.02439 0.01391 0.0130 0.2033 1.0000
6.250 0.8338 0.02485 0.01444 0.0142 0.2003 1.0000
6.500 0.8542 0.02525 0.01486 0.0154 0.1975 1.0000
6.750 0.8751 0.02569 0.01525 0.0165 0.1952 1.0000
7.000 0.8939 0.02640 0.01611 0.0178 0.1927 1.0000
7.250 0.9119 0.02720 0.01716 0.0191 0.1900 1.0000
7.500 0.9301 0.02796 0.01808 0.0204 0.1873 1.0000
7.750 0.9488 0.02860 0.01882 0.0217 0.1847 1.0000
8.000 0.9683 0.02916 0.01944 0.0229 0.1825 1.0000
8.250 0.9887 0.02966 0.01993 0.0240 0.1804 1.0000
8.500 1.0066 0.03049 0.02087 0.0252 0.1782 1.0000
8.750 1.0196 0.03173 0.02245 0.0269 0.1751 1.0000
9.000 1.0340 0.03286 0.02380 0.0284 0.1724 1.0000
9.250 1.0494 0.03383 0.02494 0.0298 0.1700 1.0000
9.500 1.0661 0.03463 0.02585 0.0310 0.1679 1.0000
9.750 1.0842 0.03533 0.02660 0.0322 0.1661 1.0000
10.000 1.1040 0.03603 0.02730 0.0331 0.1645 1.0000
10.250 1.1080 0.03804 0.02968 0.0351 0.1620 1.0000
10.500 1.1070 0.04035 0.03237 0.0373 0.1591 1.0000
10.750 1.1091 0.04226 0.03452 0.0392 0.1565 1.0000
11.000 1.1160 0.04362 0.03602 0.0408 0.1542 1.0000
11.250 1.1266 0.04466 0.03714 0.0421 0.1524 1.0000
11.500 1.1418 0.04536 0.03790 0.0433 0.1509 1.0000
11.750 1.1553 0.04628 0.03885 0.0444 0.1493 1.0000
12.000 1.0853 0.05293 0.04588 0.0477 0.1478 1.0000
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Polar data table (+)
Polar graphs
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