NACA 23015 (naca23015-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23015 (naca23015-il) Reynolds number: 50,000 Max Cl/Cd: 20.95 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23015-il-50000.txt Download as CSV file: xf-naca23015-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23015
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6857 0.08043 0.07310 -0.0302 0.9999 0.1960
-9.750 -0.6731 0.07581 0.06848 -0.0301 0.9999 0.1935
-9.500 -0.7549 0.06654 0.05860 -0.0296 0.9999 0.1797
-9.250 -0.7533 0.06214 0.05400 -0.0286 0.9999 0.1784
-9.000 -0.7509 0.05794 0.04956 -0.0274 0.9999 0.1773
-8.750 -0.7479 0.05400 0.04531 -0.0259 0.9999 0.1764
-8.500 -0.7431 0.05046 0.04137 -0.0243 0.9999 0.1766
-8.250 -0.7341 0.04731 0.03780 -0.0227 0.9999 0.1776
-8.000 -0.7216 0.04446 0.03452 -0.0211 0.9999 0.1784
-7.750 -0.7060 0.04181 0.03153 -0.0197 0.9999 0.1802
-7.500 -0.6854 0.03949 0.02924 -0.0187 0.9999 0.1841
-7.250 -0.6656 0.03749 0.02707 -0.0174 0.9999 0.1878
-7.000 -0.6457 0.03565 0.02496 -0.0161 0.9999 0.1916
-6.750 -0.6259 0.03404 0.02302 -0.0146 0.9999 0.1964
-6.500 -0.6028 0.03236 0.02148 -0.0137 0.9999 0.2024
-6.250 -0.5803 0.03103 0.02004 -0.0125 0.9999 0.2094
-6.000 -0.5572 0.02973 0.01882 -0.0114 0.9999 0.2181
-5.750 -0.5343 0.02866 0.01771 -0.0101 0.9999 0.2289
-5.500 -0.5117 0.02758 0.01682 -0.0089 0.9999 0.2429
-5.250 -0.4907 0.02658 0.01598 -0.0075 0.9999 0.2635
-5.000 -0.4725 0.02544 0.01525 -0.0058 0.9999 0.2962
-4.750 -0.4612 0.02383 0.01465 -0.0031 0.9999 0.3918
-4.500 -0.4619 0.02323 0.01533 0.0043 0.9999 0.6033
-4.250 -0.4538 0.02392 0.01622 0.0105 0.9999 0.6909
-4.000 -0.4397 0.02481 0.01716 0.0157 0.9999 0.7412
-3.750 -0.4235 0.02562 0.01793 0.0201 0.9999 0.7819
-3.500 -0.4024 0.02663 0.01888 0.0239 0.9999 0.8222
-3.250 -0.2024 0.03245 0.02407 0.0083 0.9999 0.9085
-3.000 -0.1513 0.03217 0.02362 0.0036 0.9999 0.9301
-2.750 -0.1045 0.03179 0.02311 -0.0011 0.9999 0.9508
-2.500 -0.0513 0.03137 0.02257 -0.0070 0.9999 0.9708
-2.250 0.0089 0.03088 0.02197 -0.0145 0.9999 0.9906
-2.000 0.0338 0.03057 0.02162 -0.0171 0.9999 1.0001
-1.750 0.0151 0.03056 0.02163 -0.0133 0.9999 1.0001
-1.500 -0.0074 0.03060 0.02169 -0.0092 0.9999 1.0001
-1.250 -0.0313 0.03065 0.02175 -0.0051 0.9999 1.0001
-1.000 -0.0544 0.03070 0.02181 -0.0010 0.9999 1.0001
-0.750 -0.0295 0.03082 0.02186 -0.0039 0.9896 1.0001
-0.500 0.0478 0.03083 0.02175 -0.0139 0.9651 1.0001
-0.250 0.1278 0.03051 0.02136 -0.0235 0.9396 1.0001
0.000 0.2030 0.02991 0.02071 -0.0316 0.9119 1.0001
0.250 0.2783 0.02892 0.01969 -0.0389 0.8856 1.0001
0.500 0.3275 0.02814 0.01888 -0.0416 0.8576 1.0001
0.750 0.3635 0.02751 0.01821 -0.0420 0.8288 1.0001
1.000 0.3899 0.02709 0.01772 -0.0407 0.8004 1.0001
1.250 0.4120 0.02677 0.01732 -0.0386 0.7726 1.0001
1.500 0.4314 0.02659 0.01704 -0.0362 0.7454 1.0001
1.750 0.4491 0.02654 0.01690 -0.0337 0.7175 1.0001
2.000 0.4686 0.02642 0.01664 -0.0311 0.6929 1.0001
2.250 0.4850 0.02668 0.01681 -0.0288 0.6657 1.0001
2.500 0.5032 0.02685 0.01686 -0.0265 0.6410 1.0001
2.750 0.5225 0.02706 0.01693 -0.0243 0.6186 1.0001
3.000 0.5422 0.02735 0.01707 -0.0223 0.5976 1.0001
3.250 0.5609 0.02788 0.01750 -0.0205 0.5768 1.0001
3.500 0.5803 0.02845 0.01798 -0.0189 0.5579 1.0001
3.750 0.6006 0.02903 0.01846 -0.0174 0.5410 1.0001
4.000 0.6192 0.02986 0.01927 -0.0160 0.5242 1.0001
4.250 0.6375 0.03084 0.02027 -0.0148 0.5089 1.0001
4.500 0.6566 0.03185 0.02128 -0.0136 0.4958 1.0001
4.750 0.6799 0.03245 0.02174 -0.0124 0.4846 1.0001
5.000 0.6956 0.03391 0.02336 -0.0113 0.4717 1.0001
5.250 0.7150 0.03511 0.02457 -0.0103 0.4615 1.0001
5.500 0.7338 0.03639 0.02590 -0.0094 0.4513 1.0001
5.750 0.7497 0.03804 0.02766 -0.0084 0.4419 1.0001
6.000 0.7680 0.03942 0.02910 -0.0074 0.4327 1.0001
6.250 0.7827 0.04134 0.03112 -0.0065 0.4247 1.0001
6.500 0.7918 0.04370 0.03365 -0.0054 0.4162 1.0001
6.750 0.8167 0.04463 0.03454 -0.0046 0.4088 1.0001
7.000 0.8023 0.04930 0.03955 -0.0032 0.4014 1.0001
7.250 0.8258 0.05032 0.04057 -0.0023 0.3941 1.0001
7.500 0.8076 0.05542 0.04588 -0.0009 0.3884 1.0001
7.750 0.7236 0.06697 0.05757 -0.0004 0.3877 1.0001
8.000 0.6194 0.08247 0.07299 -0.0053 0.3967 1.0001
8.250 0.6399 0.08449 0.07506 -0.0046 0.3903 1.0001
8.500 0.6261 0.09049 0.08108 -0.0063 0.3928 1.0001
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Polar data table (+)
Polar graphs
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