NACA 2415 (naca2415-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 2415 (naca2415-il) Reynolds number: 50,000 Max Cl/Cd: 27.36 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2415-il-50000.txt Download as CSV file: xf-naca2415-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2415
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3609 0.10637 0.09836 -0.0166 1.0000 0.3628
-9.000 -0.5860 0.07654 0.06889 -0.0420 1.0000 0.1974
-8.750 -0.6048 0.07186 0.06423 -0.0407 1.0000 0.1962
-8.500 -0.6294 0.06702 0.05936 -0.0390 1.0000 0.1949
-8.250 -0.6550 0.06216 0.05438 -0.0367 1.0000 0.1939
-8.000 -0.6766 0.05749 0.04949 -0.0342 1.0000 0.1938
-7.750 -0.6920 0.05310 0.04477 -0.0316 1.0000 0.1948
-7.500 -0.7028 0.04894 0.04011 -0.0290 1.0000 0.1971
-7.250 -0.6893 0.04724 0.03851 -0.0271 1.0000 0.2028
-7.000 -0.6822 0.04498 0.03606 -0.0251 1.0000 0.2090
-6.750 -0.6796 0.04185 0.03238 -0.0231 1.0000 0.2155
-6.500 -0.6623 0.04082 0.03153 -0.0214 1.0000 0.2243
-6.250 -0.6519 0.03855 0.02887 -0.0198 1.0000 0.2339
-6.000 -0.6358 0.03738 0.02767 -0.0182 1.0000 0.2454
-5.750 -0.6195 0.03606 0.02633 -0.0168 1.0000 0.2573
-5.500 -0.6031 0.03470 0.02481 -0.0155 1.0000 0.2714
-5.250 -0.5857 0.03355 0.02352 -0.0143 1.0000 0.2871
-5.000 -0.5672 0.03256 0.02245 -0.0132 1.0000 0.3042
-4.750 -0.5480 0.03171 0.02158 -0.0122 1.0000 0.3225
-4.500 -0.5286 0.03094 0.02086 -0.0112 1.0000 0.3419
-4.250 -0.5091 0.03025 0.02024 -0.0101 1.0000 0.3626
-4.000 -0.4897 0.02964 0.01973 -0.0091 1.0000 0.3853
-3.750 -0.4700 0.02906 0.01915 -0.0082 1.0000 0.4113
-3.500 -0.4507 0.02858 0.01881 -0.0071 1.0000 0.4376
-3.250 -0.4314 0.02820 0.01850 -0.0061 1.0000 0.4687
-3.000 -0.4128 0.02794 0.01846 -0.0048 1.0000 0.4994
-2.750 -0.3949 0.02776 0.01843 -0.0035 1.0000 0.5341
-2.500 -0.3774 0.02765 0.01850 -0.0020 1.0000 0.5721
-2.250 -0.3604 0.02760 0.01862 -0.0003 1.0000 0.6147
-2.000 -0.3444 0.02759 0.01883 0.0017 1.0000 0.6616
-1.750 -0.3304 0.02764 0.01912 0.0043 1.0000 0.7157
-1.500 -0.3199 0.02778 0.01956 0.0083 1.0000 0.7754
-1.250 -0.2914 0.02846 0.02047 0.0099 0.9934 0.8635
-1.000 -0.1424 0.03109 0.02284 -0.0113 0.9825 0.9781
-0.750 -0.0571 0.03151 0.02294 -0.0262 0.9673 1.0000
-0.500 -0.0301 0.03152 0.02274 -0.0295 0.9494 1.0000
-0.250 0.0017 0.03183 0.02286 -0.0326 0.9329 1.0000
0.000 0.0358 0.03230 0.02314 -0.0355 0.9173 1.0000
0.250 0.0725 0.03282 0.02350 -0.0385 0.9023 1.0000
0.500 0.1165 0.03338 0.02391 -0.0424 0.8885 1.0000
0.750 0.1449 0.03389 0.02431 -0.0436 0.8729 1.0000
1.000 0.1703 0.03447 0.02480 -0.0442 0.8577 1.0000
1.250 0.1971 0.03509 0.02533 -0.0449 0.8430 1.0000
1.500 0.2278 0.03572 0.02589 -0.0461 0.8292 1.0000
1.750 0.2781 0.03609 0.02621 -0.0500 0.8176 1.0000
2.000 0.2956 0.03684 0.02691 -0.0490 0.8024 1.0000
2.250 0.3140 0.03769 0.02771 -0.0483 0.7880 1.0000
2.500 0.3408 0.03840 0.02840 -0.0486 0.7744 1.0000
2.750 0.3954 0.03841 0.02842 -0.0523 0.7636 1.0000
3.000 0.4065 0.03941 0.02940 -0.0504 0.7481 1.0000
3.250 0.4242 0.04031 0.03028 -0.0493 0.7331 1.0000
3.500 0.4503 0.04093 0.03091 -0.0491 0.7188 1.0000
3.750 0.5061 0.04037 0.03040 -0.0518 0.7073 1.0000
4.000 0.5302 0.04092 0.03097 -0.0511 0.6928 1.0000
4.250 0.5402 0.04216 0.03222 -0.0490 0.6774 1.0000
4.500 0.5571 0.04317 0.03326 -0.0477 0.6631 1.0000
4.750 0.6063 0.04248 0.03263 -0.0489 0.6516 1.0000
5.000 0.6394 0.04249 0.03271 -0.0486 0.6384 1.0000
5.250 0.6503 0.04379 0.03404 -0.0466 0.6227 1.0000
5.500 0.6643 0.04496 0.03526 -0.0449 0.6074 1.0000
5.750 0.6919 0.04523 0.03560 -0.0440 0.5931 1.0000
6.000 0.7732 0.04174 0.03222 -0.0462 0.5824 1.0000
6.250 0.7915 0.04234 0.03287 -0.0442 0.5655 1.0000
6.500 0.8143 0.04261 0.03320 -0.0425 0.5486 1.0000
6.750 0.8428 0.04242 0.03308 -0.0411 0.5313 1.0000
7.000 0.8748 0.04199 0.03269 -0.0399 0.5137 1.0000
7.250 0.9081 0.04146 0.03220 -0.0388 0.4957 1.0000
7.500 0.9418 0.04092 0.03168 -0.0377 0.4771 1.0000
7.750 0.9800 0.04009 0.03081 -0.0371 0.4575 1.0000
8.000 1.0079 0.03996 0.03065 -0.0357 0.4373 1.0000
8.250 1.0226 0.04064 0.03139 -0.0332 0.4172 1.0000
8.500 1.0408 0.04105 0.03181 -0.0310 0.3962 1.0000
8.750 1.0660 0.04096 0.03166 -0.0293 0.3740 1.0000
9.000 1.1027 0.04030 0.03072 -0.0288 0.3504 1.0000
9.250 1.1118 0.04137 0.03185 -0.0259 0.3304 1.0000
9.500 1.1233 0.04238 0.03286 -0.0233 0.3108 1.0000
9.750 1.1361 0.04338 0.03385 -0.0210 0.2919 1.0000
10.000 1.1490 0.04451 0.03494 -0.0187 0.2745 1.0000
10.250 1.1609 0.04585 0.03626 -0.0165 0.2586 1.0000
10.500 1.1731 0.04735 0.03773 -0.0145 0.2442 1.0000
10.750 1.1890 0.04891 0.03922 -0.0129 0.2309 1.0000
11.000 1.2135 0.05038 0.04049 -0.0124 0.2176 1.0000
11.250 1.1898 0.05379 0.04437 -0.0076 0.2126 1.0000
11.500 1.2207 0.05537 0.04575 -0.0077 0.2013 1.0000
11.750 1.1894 0.05909 0.04988 -0.0027 0.1990 1.0000
12.000 1.1535 0.06350 0.05460 0.0014 0.1974 1.0000
12.250 1.1064 0.06963 0.06102 0.0039 0.1975 1.0000
12.500 1.0421 0.07918 0.07080 0.0032 0.1996 1.0000
12.750 0.9696 0.09312 0.08485 -0.0018 0.2018 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 2415 (naca2415-il)