NACA 23018 (naca23018-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23018 (naca23018-il) Reynolds number: 50,000 Max Cl/Cd: 21.08 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23018-il-50000.txt Download as CSV file: xf-naca23018-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23018
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7369 0.07551 0.06719 -0.0469 1.0000 0.1785
-11.500 -0.7734 0.06990 0.06147 -0.0457 1.0000 0.1774
-11.250 -0.8107 0.06557 0.05703 -0.0422 1.0000 0.1764
-11.000 -0.8415 0.06179 0.05306 -0.0379 1.0000 0.1760
-10.750 -0.8654 0.05835 0.04940 -0.0335 1.0000 0.1761
-10.500 -0.8836 0.05525 0.04603 -0.0291 1.0000 0.1766
-10.250 -0.8971 0.05242 0.04288 -0.0246 1.0000 0.1776
-10.000 -0.9078 0.04985 0.03993 -0.0200 1.0000 0.1789
-9.750 -0.8911 0.04761 0.03780 -0.0187 1.0000 0.1829
-9.500 -0.8803 0.04573 0.03586 -0.0164 1.0000 0.1869
-9.250 -0.8761 0.04370 0.03360 -0.0132 1.0000 0.1906
-9.000 -0.8748 0.04176 0.03127 -0.0094 1.0000 0.1944
-8.750 -0.8538 0.04010 0.02981 -0.0084 1.0000 0.2007
-8.500 -0.8426 0.03855 0.02812 -0.0058 1.0000 0.2074
-8.250 -0.8267 0.03699 0.02657 -0.0039 1.0000 0.2148
-8.000 -0.8129 0.03571 0.02525 -0.0016 1.0000 0.2246
-7.750 -0.7954 0.03444 0.02414 0.0001 1.0000 0.2361
-7.500 -0.7807 0.03323 0.02302 0.0023 1.0000 0.2505
-7.250 -0.7672 0.03213 0.02209 0.0048 1.0000 0.2694
-7.000 -0.7564 0.03108 0.02124 0.0077 1.0000 0.2949
-6.750 -0.7478 0.03017 0.02071 0.0111 1.0000 0.3300
-6.500 -0.7426 0.02942 0.02038 0.0152 1.0000 0.3791
-6.250 -0.7386 0.02909 0.02038 0.0199 1.0000 0.4353
-6.000 -0.7274 0.02937 0.02100 0.0240 1.0000 0.4824
-5.750 -0.7163 0.02966 0.02139 0.0279 1.0000 0.5210
-5.500 -0.7009 0.03023 0.02210 0.0313 1.0000 0.5531
-5.250 -0.6886 0.03055 0.02246 0.0348 1.0000 0.5828
-5.000 -0.6707 0.03142 0.02345 0.0382 1.0000 0.6095
-4.750 -0.6550 0.03212 0.02421 0.0416 1.0000 0.6352
-4.500 -0.6404 0.03265 0.02478 0.0449 1.0000 0.6592
-4.250 -0.6259 0.03312 0.02525 0.0479 1.0000 0.6814
-4.000 -0.6115 0.03364 0.02578 0.0510 1.0000 0.7037
-3.750 -0.5982 0.03421 0.02636 0.0542 1.0000 0.7271
-3.500 -0.5856 0.03472 0.02686 0.0573 1.0000 0.7505
-3.250 -0.5687 0.03540 0.02755 0.0598 1.0000 0.7719
-3.000 -0.5476 0.03603 0.02815 0.0611 1.0000 0.7902
-2.750 -0.4894 0.03727 0.02927 0.0556 0.9904 0.8088
-2.500 -0.4061 0.03879 0.03064 0.0456 0.9736 0.8269
-2.250 -0.3179 0.04004 0.03173 0.0346 0.9564 0.8442
-2.000 -0.2261 0.04092 0.03246 0.0227 0.9389 0.8612
-1.750 -0.1298 0.04139 0.03280 0.0099 0.9208 0.8784
-1.500 -0.0381 0.04141 0.03271 -0.0021 0.9022 0.8957
-1.250 0.0845 0.04084 0.03205 -0.0189 0.8832 0.9099
-1.000 0.1917 0.03956 0.03072 -0.0330 0.8642 0.9256
-0.750 0.2788 0.03804 0.02915 -0.0433 0.8436 0.9414
-0.500 0.3525 0.03645 0.02753 -0.0510 0.8215 0.9573
-0.250 0.4169 0.03488 0.02590 -0.0570 0.7983 0.9731
0.000 0.4768 0.03329 0.02423 -0.0623 0.7743 0.9888
0.250 0.5224 0.03220 0.02308 -0.0656 0.7483 1.0000
0.500 0.5367 0.03188 0.02267 -0.0637 0.7264 1.0000
0.750 0.5512 0.03162 0.02233 -0.0617 0.7054 1.0000
1.000 0.5659 0.03141 0.02202 -0.0597 0.6848 1.0000
1.250 0.5812 0.03124 0.02174 -0.0578 0.6651 1.0000
1.500 0.5971 0.03113 0.02151 -0.0559 0.6462 1.0000
1.750 0.6114 0.03126 0.02157 -0.0541 0.6266 1.0000
2.000 0.6256 0.03148 0.02173 -0.0523 0.6076 1.0000
2.250 0.6397 0.03181 0.02202 -0.0505 0.5897 1.0000
2.500 0.6545 0.03218 0.02233 -0.0488 0.5732 1.0000
2.750 0.6721 0.03237 0.02240 -0.0471 0.5588 1.0000
3.000 0.6877 0.03276 0.02273 -0.0453 0.5440 1.0000
3.250 0.6984 0.03363 0.02364 -0.0434 0.5295 1.0000
3.500 0.7166 0.03399 0.02388 -0.0417 0.5180 1.0000
3.750 0.7262 0.03492 0.02487 -0.0395 0.5050 1.0000
4.000 0.7381 0.03583 0.02577 -0.0374 0.4943 1.0000
4.250 0.7499 0.03669 0.02663 -0.0353 0.4836 1.0000
4.500 0.7589 0.03782 0.02778 -0.0329 0.4741 1.0000
4.750 0.7653 0.03905 0.02906 -0.0302 0.4643 1.0000
5.000 0.7828 0.03976 0.02969 -0.0285 0.4564 1.0000
5.250 0.7672 0.04233 0.03246 -0.0239 0.4478 1.0000
5.500 0.7933 0.04252 0.03255 -0.0229 0.4399 1.0000
5.750 0.7741 0.04539 0.03556 -0.0179 0.4330 1.0000
6.000 0.7413 0.04897 0.03928 -0.0121 0.4267 1.0000
6.250 0.7983 0.04764 0.03777 -0.0136 0.4187 1.0000
6.500 0.7326 0.05335 0.04365 -0.0054 0.4144 1.0000
6.750 0.5659 0.06730 0.05753 0.0041 0.4146 1.0000
7.000 0.5039 0.07622 0.06638 0.0040 0.4135 1.0000
7.250 0.4796 0.08189 0.07203 0.0036 0.4131 1.0000
7.500 0.4653 0.08676 0.07689 0.0030 0.4130 1.0000
7.750 0.4602 0.09119 0.08132 0.0024 0.4144 1.0000
8.000 0.4637 0.09531 0.08546 0.0016 0.4161 1.0000
8.250 0.4776 0.09925 0.08945 0.0007 0.4177 1.0000
8.500 0.3584 0.11120 0.10144 -0.0059 0.5124 1.0000
8.750 0.3939 0.11523 0.10550 -0.0071 0.5010 1.0000
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Polar data table (+)
Polar graphs
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