MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Reynolds number: 100,000 Max Cl/Cd: 31.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske5-il-100000-n5.txt Download as CSV file: xf-marske5-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4684 0.10176 0.09691 -0.0044 1.0000 0.0603
-10.000 -0.4211 0.08288 0.07833 -0.0173 1.0000 0.0423
-9.500 -0.5080 0.08104 0.07622 -0.0186 1.0000 0.0435
-9.000 -0.5669 0.06890 0.06375 -0.0181 1.0000 0.0362
-8.750 -0.5684 0.06599 0.06081 -0.0165 1.0000 0.0359
-8.500 -0.5720 0.06275 0.05747 -0.0146 1.0000 0.0356
-8.250 -0.5747 0.05944 0.05404 -0.0125 1.0000 0.0353
-8.000 -0.5761 0.05607 0.05051 -0.0101 1.0000 0.0350
-7.750 -0.5761 0.05270 0.04694 -0.0074 1.0000 0.0348
-7.500 -0.5742 0.04944 0.04344 -0.0045 1.0000 0.0347
-7.250 -0.5708 0.04628 0.04000 -0.0014 1.0000 0.0349
-7.000 -0.5670 0.04312 0.03648 0.0020 1.0000 0.0356
-6.750 -0.5644 0.03991 0.03270 0.0062 1.0000 0.0364
-6.500 -0.5502 0.03827 0.03110 0.0081 1.0000 0.0371
-6.250 -0.5381 0.03635 0.02900 0.0106 1.0000 0.0375
-6.000 -0.5258 0.03444 0.02690 0.0133 1.0000 0.0379
-5.750 -0.4916 0.03197 0.02409 0.0119 0.9763 0.0387
-5.500 -0.4531 0.02975 0.02142 0.0100 0.9424 0.0411
-5.250 -0.4097 0.02753 0.01872 0.0076 0.8977 0.0429
-5.000 -0.3635 0.02583 0.01680 0.0045 0.8470 0.0444
-4.750 -0.3284 0.02469 0.01536 0.0037 0.8057 0.0468
-4.500 -0.2981 0.02370 0.01396 0.0042 0.7711 0.0491
-4.250 -0.2696 0.02265 0.01280 0.0047 0.7399 0.0505
-4.000 -0.2431 0.02193 0.01196 0.0055 0.7103 0.0527
-3.750 -0.2172 0.02130 0.01118 0.0065 0.6792 0.0557
-3.500 -0.1917 0.02061 0.01036 0.0076 0.6426 0.0576
-3.250 -0.1683 0.01995 0.00965 0.0088 0.5959 0.0598
-3.000 -0.1461 0.01956 0.00903 0.0104 0.5324 0.0632
-2.750 -0.1246 0.01935 0.00843 0.0120 0.4616 0.0663
-2.500 -0.1043 0.01910 0.00791 0.0137 0.4052 0.0691
-2.250 -0.0826 0.01897 0.00753 0.0151 0.3710 0.0739
-2.000 -0.0603 0.01882 0.00719 0.0164 0.3496 0.0796
-1.750 -0.0373 0.01866 0.00690 0.0177 0.3339 0.0875
-1.500 -0.0142 0.01846 0.00664 0.0188 0.3217 0.1045
-1.250 0.0319 0.01644 0.00754 0.0172 0.3083 0.8393
-1.000 0.0847 0.01760 0.00844 0.0148 0.2963 0.8980
-0.750 0.2011 0.01934 0.00971 0.0006 0.2816 0.9554
-0.500 0.2338 0.01950 0.00966 -0.0003 0.2750 0.9629
-0.250 0.2664 0.01961 0.00954 -0.0013 0.2694 0.9662
0.000 0.2969 0.01968 0.00951 -0.0018 0.2638 0.9705
0.250 0.3283 0.01979 0.00948 -0.0026 0.2587 0.9750
0.500 0.3630 0.01992 0.00943 -0.0040 0.2544 0.9796
0.750 0.3941 0.02011 0.00949 -0.0048 0.2509 0.9843
1.000 0.4256 0.02020 0.00954 -0.0056 0.2470 0.9869
1.250 0.4552 0.02034 0.00961 -0.0061 0.2434 0.9895
1.500 0.4835 0.02052 0.00970 -0.0064 0.2401 0.9920
1.750 0.5110 0.02073 0.00980 -0.0065 0.2372 0.9942
2.000 0.5404 0.02098 0.00992 -0.0070 0.2344 0.9964
2.250 0.5695 0.02117 0.01016 -0.0075 0.2313 0.9987
2.500 0.5958 0.02143 0.01043 -0.0074 0.2284 1.0000
2.750 0.6176 0.02173 0.01073 -0.0064 0.2261 1.0000
3.000 0.6392 0.02205 0.01104 -0.0054 0.2240 1.0000
3.250 0.6608 0.02238 0.01134 -0.0043 0.2221 1.0000
3.500 0.6823 0.02274 0.01166 -0.0033 0.2203 1.0000
3.750 0.7038 0.02315 0.01201 -0.0023 0.2188 1.0000
4.000 0.7248 0.02362 0.01248 -0.0013 0.2171 1.0000
4.250 0.7452 0.02408 0.01308 -0.0001 0.2151 1.0000
4.500 0.7652 0.02456 0.01366 0.0011 0.2129 1.0000
4.750 0.7850 0.02506 0.01423 0.0023 0.2108 1.0000
5.000 0.8046 0.02556 0.01480 0.0036 0.2089 1.0000
5.250 0.8240 0.02608 0.01537 0.0048 0.2073 1.0000
5.500 0.8432 0.02662 0.01594 0.0061 0.2059 1.0000
5.750 0.8624 0.02718 0.01652 0.0074 0.2046 1.0000
6.000 0.8815 0.02776 0.01710 0.0087 0.2033 1.0000
6.250 0.9006 0.02842 0.01775 0.0100 0.2022 1.0000
6.500 0.9166 0.02924 0.01874 0.0116 0.2007 1.0000
6.750 0.9309 0.03014 0.01987 0.0134 0.1987 1.0000
7.000 0.9448 0.03105 0.02096 0.0153 0.1968 1.0000
7.250 0.9586 0.03198 0.02204 0.0171 0.1950 1.0000
7.500 0.9723 0.03287 0.02305 0.0190 0.1933 1.0000
7.750 0.9864 0.03366 0.02394 0.0208 0.1917 1.0000
8.000 1.0014 0.03431 0.02464 0.0225 0.1900 1.0000
8.250 1.0174 0.03489 0.02523 0.0241 0.1886 1.0000
8.500 1.0349 0.03544 0.02577 0.0255 0.1872 1.0000
8.750 1.0464 0.03650 0.02692 0.0275 0.1857 1.0000
9.000 1.0454 0.03831 0.02907 0.0306 0.1836 1.0000
9.250 1.0448 0.04007 0.03108 0.0335 0.1814 1.0000
9.500 1.0449 0.04172 0.03292 0.0362 0.1795 1.0000
9.750 1.0455 0.04328 0.03463 0.0388 0.1777 1.0000
10.000 1.0484 0.04460 0.03605 0.0411 0.1761 1.0000
10.250 1.0544 0.04567 0.03719 0.0431 0.1747 1.0000
10.500 1.0637 0.04654 0.03808 0.0449 0.1734 1.0000
10.750 1.0767 0.04724 0.03878 0.0464 0.1723 1.0000
11.000 1.0793 0.04861 0.04019 0.0485 0.1713 1.0000
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Polar data table (+)
Polar graphs
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