NACA 2415 (n2415-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 50,000 Max Cl/Cd: 26.26 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2415-il-50000.txt Download as CSV file: xf-n2415-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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3912 0.11156 0.10358 -0.0163 1.0000 0.3643
-9.250 -0.3530 0.10599 0.09794 -0.0159 1.0000 0.3742
-9.000 -0.5952 0.07639 0.06879 -0.0413 1.0000 0.2033
-8.750 -0.6146 0.07153 0.06390 -0.0401 1.0000 0.2014
-8.500 -0.6369 0.06677 0.05912 -0.0383 1.0000 0.2003
-8.250 -0.6614 0.06198 0.05419 -0.0360 1.0000 0.1997
-8.000 -0.6830 0.05732 0.04930 -0.0335 1.0000 0.1999
-7.750 -0.7001 0.05284 0.04442 -0.0308 1.0000 0.2013
-7.500 -0.6985 0.04978 0.04121 -0.0286 1.0000 0.2050
-7.250 -0.6861 0.04822 0.03967 -0.0266 1.0000 0.2109
-7.000 -0.6854 0.04513 0.03618 -0.0245 1.0000 0.2165
-6.750 -0.6780 0.04255 0.03332 -0.0226 1.0000 0.2225
-6.500 -0.6636 0.04113 0.03188 -0.0209 1.0000 0.2310
-6.250 -0.6530 0.03884 0.02923 -0.0193 1.0000 0.2395
-6.000 -0.6367 0.03761 0.02797 -0.0178 1.0000 0.2499
-5.750 -0.6209 0.03611 0.02635 -0.0165 1.0000 0.2607
-5.500 -0.6046 0.03465 0.02463 -0.0153 1.0000 0.2739
-5.250 -0.5864 0.03364 0.02359 -0.0141 1.0000 0.2880
-5.000 -0.5677 0.03270 0.02269 -0.0129 1.0000 0.3035
-4.750 -0.5484 0.03178 0.02175 -0.0119 1.0000 0.3206
-4.500 -0.5290 0.03097 0.02092 -0.0109 1.0000 0.3401
-4.250 -0.5094 0.03022 0.02014 -0.0100 1.0000 0.3617
-4.000 -0.4898 0.02954 0.01949 -0.0091 1.0000 0.3849
-3.750 -0.4707 0.02904 0.01915 -0.0079 1.0000 0.4090
-3.500 -0.4514 0.02858 0.01875 -0.0070 1.0000 0.4375
-3.250 -0.4326 0.02822 0.01857 -0.0058 1.0000 0.4662
-3.000 -0.4136 0.02793 0.01840 -0.0047 1.0000 0.4995
-2.750 -0.3956 0.02773 0.01834 -0.0034 1.0000 0.5356
-2.500 -0.3783 0.02761 0.01842 -0.0019 1.0000 0.5742
-2.250 -0.3618 0.02757 0.01860 0.0000 1.0000 0.6161
-2.000 -0.3462 0.02759 0.01885 0.0021 1.0000 0.6643
-1.750 -0.3328 0.02766 0.01919 0.0050 1.0000 0.7176
-1.500 -0.3223 0.02781 0.01960 0.0088 1.0000 0.7797
-1.250 -0.2881 0.02858 0.02060 0.0096 0.9914 0.8697
-1.000 -0.1290 0.03133 0.02303 -0.0137 0.9817 0.9823
-0.750 -0.0564 0.03155 0.02296 -0.0264 0.9661 1.0000
-0.500 -0.0295 0.03157 0.02278 -0.0297 0.9487 1.0000
-0.250 0.0013 0.03191 0.02291 -0.0326 0.9328 1.0000
0.000 0.0354 0.03239 0.02321 -0.0355 0.9176 1.0000
0.250 0.0742 0.03295 0.02361 -0.0389 0.9035 1.0000
0.500 0.1101 0.03348 0.02401 -0.0415 0.8888 1.0000
0.750 0.1351 0.03404 0.02445 -0.0421 0.8736 1.0000
1.000 0.1620 0.03465 0.02495 -0.0430 0.8587 1.0000
1.250 0.1927 0.03527 0.02549 -0.0443 0.8448 1.0000
1.500 0.2371 0.03576 0.02591 -0.0475 0.8323 1.0000
1.750 0.2630 0.03637 0.02647 -0.0478 0.8178 1.0000
2.000 0.2833 0.03711 0.02715 -0.0473 0.8031 1.0000
2.250 0.3095 0.03780 0.02781 -0.0476 0.7893 1.0000
2.500 0.3567 0.03805 0.02804 -0.0505 0.7775 1.0000
2.750 0.3788 0.03875 0.02873 -0.0500 0.7630 1.0000
3.000 0.3950 0.03968 0.02964 -0.0488 0.7482 1.0000
3.250 0.4198 0.04041 0.03037 -0.0486 0.7344 1.0000
3.500 0.4827 0.03981 0.02983 -0.0525 0.7240 1.0000
3.750 0.4894 0.04106 0.03107 -0.0501 0.7082 1.0000
4.000 0.5023 0.04219 0.03220 -0.0484 0.6930 1.0000
4.250 0.5249 0.04297 0.03300 -0.0477 0.6788 1.0000
4.500 0.5958 0.04128 0.03142 -0.0509 0.6690 1.0000
4.750 0.6050 0.04258 0.03273 -0.0487 0.6528 1.0000
5.000 0.6167 0.04379 0.03398 -0.0468 0.6370 1.0000
5.250 0.6344 0.04469 0.03492 -0.0453 0.6218 1.0000
5.500 0.6721 0.04436 0.03466 -0.0451 0.6082 1.0000
5.750 0.7356 0.04215 0.03255 -0.0463 0.5963 1.0000
6.000 0.7501 0.04308 0.03354 -0.0442 0.5796 1.0000
6.250 0.7676 0.04383 0.03435 -0.0423 0.5632 1.0000
6.500 0.7910 0.04414 0.03473 -0.0407 0.5468 1.0000
6.750 0.8212 0.04391 0.03455 -0.0395 0.5303 1.0000
7.000 0.8559 0.04330 0.03402 -0.0384 0.5134 1.0000
7.250 0.8911 0.04262 0.03338 -0.0374 0.4955 1.0000
7.500 0.9251 0.04200 0.03280 -0.0363 0.4767 1.0000
7.750 0.9584 0.04143 0.03223 -0.0351 0.4570 1.0000
8.000 0.9929 0.04079 0.03156 -0.0341 0.4365 1.0000
8.250 1.0337 0.03979 0.03044 -0.0337 0.4149 1.0000
8.500 1.0527 0.04024 0.03088 -0.0317 0.3943 1.0000
8.750 1.0665 0.04101 0.03168 -0.0292 0.3742 1.0000
9.000 1.0831 0.04167 0.03235 -0.0270 0.3541 1.0000
9.250 1.1021 0.04222 0.03285 -0.0250 0.3341 1.0000
9.500 1.1230 0.04277 0.03331 -0.0233 0.3146 1.0000
9.750 1.1421 0.04359 0.03405 -0.0216 0.2964 1.0000
10.000 1.1540 0.04495 0.03542 -0.0194 0.2804 1.0000
10.250 1.1604 0.04674 0.03729 -0.0168 0.2664 1.0000
10.500 1.1701 0.04850 0.03908 -0.0146 0.2534 1.0000
10.750 1.1862 0.05002 0.04055 -0.0131 0.2404 1.0000
11.000 1.2115 0.05133 0.04170 -0.0125 0.2272 1.0000
11.250 1.1836 0.05499 0.04581 -0.0075 0.2227 1.0000
11.500 0.9228 0.08297 0.07459 -0.0066 0.2505 1.0000
11.750 0.8865 0.09334 0.08496 -0.0102 0.2456 1.0000
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Polar data table (+)
Polar graphs
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