MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Reynolds number: 50,000 Max Cl/Cd: 18.94 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske2-il-50000.txt Download as CSV file: xf-marske2-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5412 0.14660 0.13931 0.0173 1.0000 0.2111
-12.000 -0.5129 0.14062 0.13331 0.0190 1.0000 0.2214
-11.750 -0.5412 0.14056 0.13338 0.0156 1.0000 0.2282
-11.500 -0.5117 0.13496 0.12776 0.0175 1.0000 0.2428
-11.250 -0.4972 0.13077 0.12359 0.0180 1.0000 0.2547
-11.000 -0.4956 0.12751 0.12039 0.0176 1.0000 0.2667
-10.750 -0.5185 0.12689 0.11987 0.0159 1.0000 0.2786
-10.500 -0.4999 0.12257 0.11557 0.0170 1.0000 0.2948
-10.250 -0.4848 0.11862 0.11165 0.0179 1.0000 0.3107
-10.000 -0.4782 0.11540 0.10847 0.0185 1.0000 0.3278
-9.750 -0.4809 0.11302 0.10616 0.0190 1.0000 0.3462
-9.500 -0.4514 0.10838 0.10152 0.0208 1.0000 0.3707
-9.250 -0.4496 0.10614 0.09934 0.0220 1.0000 0.3956
-9.000 -0.4334 0.10251 0.09575 0.0232 1.0000 0.4196
-8.750 -0.4300 0.10040 0.09370 0.0249 1.0000 0.4472
-8.500 -0.4061 0.09633 0.08964 0.0259 1.0000 0.4721
-8.250 -0.4015 0.09401 0.08739 0.0278 1.0000 0.5026
-8.000 -0.3859 0.09126 0.08468 0.0292 1.0000 0.5331
-6.750 -0.5582 0.06450 0.05854 0.0111 1.0000 0.3498
-6.500 -0.6012 0.05373 0.04667 0.0033 1.0000 0.2235
-6.250 -0.5951 0.04909 0.04136 0.0048 1.0000 0.1892
-6.000 -0.5842 0.04573 0.03747 0.0072 1.0000 0.1729
-5.750 -0.5742 0.04293 0.03408 0.0101 1.0000 0.1638
-5.500 -0.5587 0.04083 0.03156 0.0126 1.0000 0.1599
-5.250 -0.5409 0.03824 0.02880 0.0145 1.0000 0.1571
-5.000 -0.5224 0.03598 0.02628 0.0165 1.0000 0.1539
-4.750 -0.5037 0.03411 0.02416 0.0185 1.0000 0.1537
-4.500 -0.4846 0.03248 0.02231 0.0204 1.0000 0.1552
-4.250 -0.4644 0.03097 0.02059 0.0221 1.0000 0.1560
-4.000 -0.4432 0.02963 0.01908 0.0237 1.0000 0.1570
-3.750 -0.4236 0.02864 0.01789 0.0254 1.0000 0.1604
-3.500 -0.3977 0.02727 0.01659 0.0259 1.0000 0.1652
-3.250 -0.3692 0.02627 0.01566 0.0261 1.0000 0.1705
-3.000 0.0269 0.02271 0.01465 -0.0200 1.0000 1.0000
-2.750 0.0415 0.02237 0.01424 -0.0190 1.0000 1.0000
-2.500 0.0546 0.02215 0.01398 -0.0177 1.0000 1.0000
-2.250 0.0638 0.02208 0.01394 -0.0160 1.0000 1.0000
-2.000 0.0628 0.02239 0.01434 -0.0132 1.0000 1.0000
-1.750 0.0570 0.02314 0.01515 -0.0110 0.9922 1.0000
-1.500 0.2072 0.02169 0.01341 -0.0329 0.8963 1.0000
-1.250 0.2532 0.02153 0.01271 -0.0341 0.7919 1.0000
-1.000 0.2678 0.02197 0.01265 -0.0302 0.7169 1.0000
-0.750 0.2834 0.02238 0.01266 -0.0271 0.6582 1.0000
-0.500 0.3012 0.02266 0.01264 -0.0249 0.6131 1.0000
-0.250 0.3204 0.02290 0.01260 -0.0231 0.5791 1.0000
0.000 0.3404 0.02318 0.01265 -0.0216 0.5519 1.0000
0.250 0.3608 0.02353 0.01280 -0.0202 0.5299 1.0000
0.500 0.3820 0.02392 0.01302 -0.0191 0.5110 1.0000
0.750 0.4035 0.02436 0.01333 -0.0181 0.4940 1.0000
1.000 0.4251 0.02488 0.01375 -0.0172 0.4797 1.0000
1.250 0.4466 0.02543 0.01420 -0.0162 0.4678 1.0000
1.500 0.4679 0.02601 0.01469 -0.0152 0.4564 1.0000
1.750 0.4887 0.02672 0.01544 -0.0143 0.4454 1.0000
2.000 0.5098 0.02735 0.01590 -0.0132 0.4367 1.0000
2.250 0.5297 0.02830 0.01702 -0.0125 0.4277 1.0000
2.500 0.5505 0.02907 0.01771 -0.0114 0.4210 1.0000
2.750 0.5690 0.03026 0.01908 -0.0106 0.4135 1.0000
3.000 0.5883 0.03119 0.02002 -0.0095 0.4065 1.0000
3.250 0.6067 0.03231 0.02116 -0.0084 0.4004 1.0000
3.500 0.6223 0.03389 0.02298 -0.0076 0.3945 1.0000
3.750 0.6392 0.03525 0.02442 -0.0065 0.3898 1.0000
4.000 0.6587 0.03631 0.02537 -0.0051 0.3855 1.0000
4.250 0.6659 0.03884 0.02829 -0.0042 0.3808 1.0000
4.500 0.6750 0.04102 0.03066 -0.0030 0.3761 1.0000
4.750 0.6862 0.04295 0.03269 -0.0017 0.3724 1.0000
5.000 0.6988 0.04484 0.03461 -0.0003 0.3698 1.0000
5.250 0.7020 0.04778 0.03770 0.0010 0.3677 1.0000
5.500 0.6892 0.05216 0.04232 0.0021 0.3666 1.0000
5.750 0.6706 0.05695 0.04724 0.0032 0.3666 1.0000
6.000 0.6570 0.06139 0.05173 0.0042 0.3677 1.0000
6.250 0.3683 0.08552 0.07570 -0.0084 0.5705 1.0000
6.500 0.3873 0.08819 0.07835 -0.0083 0.5596 1.0000
6.750 0.3847 0.08968 0.07980 -0.0066 0.5464 1.0000
7.000 0.3934 0.09207 0.08216 -0.0058 0.5351 1.0000
7.250 0.4246 0.09579 0.08590 -0.0064 0.5240 1.0000
7.500 0.4137 0.09662 0.08667 -0.0044 0.5109 1.0000
7.750 0.4232 0.09941 0.08945 -0.0041 0.5027 1.0000
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Polar data table (+)
Polar graphs
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