NACA 2415 (naca2415-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2415 (naca2415-il) Reynolds number: 100,000 Max Cl/Cd: 46.68 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2415-il-100000.txt Download as CSV file: xf-naca2415-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6054 0.08336 0.07758 -0.0565 1.0000 0.1095
-11.250 -0.6180 0.07674 0.07095 -0.0592 1.0000 0.1082
-11.000 -0.6583 0.06811 0.06226 -0.0634 1.0000 0.1064
-10.750 -0.7137 0.06170 0.05575 -0.0628 1.0000 0.1047
-10.500 -0.7608 0.05720 0.05108 -0.0583 1.0000 0.1036
-10.250 -0.7944 0.05295 0.04657 -0.0539 1.0000 0.1030
-10.000 -0.8149 0.04936 0.04269 -0.0498 1.0000 0.1030
-9.750 -0.8258 0.04633 0.03937 -0.0460 1.0000 0.1035
-9.500 -0.8307 0.04371 0.03645 -0.0425 1.0000 0.1048
-9.250 -0.8326 0.04124 0.03362 -0.0392 1.0000 0.1064
-9.000 -0.8321 0.03894 0.03087 -0.0359 1.0000 0.1082
-8.750 -0.8259 0.03670 0.02832 -0.0333 1.0000 0.1100
-8.500 -0.8113 0.03517 0.02682 -0.0316 1.0000 0.1123
-8.250 -0.7973 0.03387 0.02543 -0.0298 1.0000 0.1151
-8.000 -0.7840 0.03255 0.02390 -0.0278 1.0000 0.1187
-7.750 -0.7713 0.03114 0.02209 -0.0257 1.0000 0.1226
-7.500 -0.7532 0.03000 0.02111 -0.0245 1.0000 0.1269
-7.250 -0.7364 0.02903 0.02001 -0.0230 1.0000 0.1321
-7.000 -0.7190 0.02786 0.01865 -0.0216 1.0000 0.1380
-6.750 -0.7002 0.02716 0.01804 -0.0204 1.0000 0.1448
-6.500 -0.6814 0.02626 0.01700 -0.0192 1.0000 0.1529
-6.250 -0.6622 0.02569 0.01649 -0.0182 1.0000 0.1619
-6.000 -0.6428 0.02500 0.01582 -0.0172 1.0000 0.1716
-5.750 -0.6236 0.02449 0.01521 -0.0161 1.0000 0.1834
-5.500 -0.6043 0.02410 0.01490 -0.0152 1.0000 0.1954
-5.250 -0.5849 0.02369 0.01459 -0.0143 1.0000 0.2080
-5.000 -0.5654 0.02336 0.01429 -0.0135 1.0000 0.2218
-4.750 -0.5289 0.02312 0.01411 -0.0159 0.9954 0.2413
-4.500 -0.4853 0.02291 0.01389 -0.0194 0.9880 0.2654
-4.250 -0.4400 0.02266 0.01381 -0.0233 0.9814 0.2909
-4.000 -0.4003 0.02238 0.01360 -0.0261 0.9723 0.3189
-3.750 -0.3602 0.02207 0.01347 -0.0289 0.9638 0.3483
-3.250 -0.2814 0.02146 0.01318 -0.0339 0.9457 0.4170
-3.000 -0.2362 0.02115 0.01311 -0.0373 0.9388 0.4579
-2.750 -0.2040 0.02086 0.01303 -0.0381 0.9273 0.4970
-2.500 -0.1676 0.02061 0.01298 -0.0396 0.9177 0.5441
-2.250 -0.1286 0.02029 0.01292 -0.0413 0.9088 0.5958
-2.000 -0.0978 0.02007 0.01294 -0.0413 0.8978 0.6470
-1.750 -0.0556 0.01975 0.01285 -0.0428 0.8908 0.7051
-1.500 -0.0277 0.01966 0.01293 -0.0418 0.8792 0.7555
-1.250 0.0147 0.01945 0.01284 -0.0427 0.8731 0.8058
-1.000 0.0426 0.01951 0.01296 -0.0412 0.8612 0.8479
-0.750 0.0909 0.01938 0.01281 -0.0431 0.8554 0.8852
-0.500 0.1387 0.01949 0.01289 -0.0455 0.8449 0.9135
-0.250 0.2036 0.01928 0.01260 -0.0512 0.8386 0.9358
0.000 0.2682 0.01916 0.01240 -0.0575 0.8286 0.9533
0.250 0.3396 0.01873 0.01188 -0.0650 0.8200 0.9672
0.500 0.4024 0.01844 0.01153 -0.0716 0.8068 0.9824
0.750 0.4668 0.01797 0.01099 -0.0785 0.7940 0.9966
1.000 0.4986 0.01762 0.01054 -0.0794 0.7810 1.0000
1.250 0.5165 0.01751 0.01036 -0.0780 0.7653 1.0000
1.500 0.5347 0.01747 0.01027 -0.0765 0.7499 1.0000
1.750 0.5537 0.01746 0.01019 -0.0750 0.7351 1.0000
2.000 0.5740 0.01743 0.01007 -0.0735 0.7206 1.0000
2.250 0.5955 0.01736 0.00990 -0.0721 0.7061 1.0000
2.500 0.6171 0.01734 0.00977 -0.0706 0.6914 1.0000
2.750 0.6362 0.01746 0.00985 -0.0690 0.6758 1.0000
3.000 0.6560 0.01763 0.00998 -0.0674 0.6615 1.0000
3.250 0.6775 0.01778 0.01006 -0.0660 0.6480 1.0000
3.500 0.7016 0.01789 0.01006 -0.0650 0.6356 1.0000
3.750 0.7215 0.01812 0.01028 -0.0634 0.6213 1.0000
4.000 0.7416 0.01839 0.01052 -0.0619 0.6073 1.0000
4.250 0.7637 0.01863 0.01070 -0.0606 0.5942 1.0000
4.500 0.7884 0.01880 0.01077 -0.0597 0.5815 1.0000
4.750 0.8084 0.01907 0.01104 -0.0581 0.5668 1.0000
5.000 0.8285 0.01933 0.01128 -0.0564 0.5517 1.0000
5.250 0.8494 0.01957 0.01148 -0.0549 0.5364 1.0000
5.500 0.8710 0.01980 0.01166 -0.0534 0.5212 1.0000
5.750 0.8933 0.02004 0.01183 -0.0521 0.5064 1.0000
6.000 0.9164 0.02028 0.01198 -0.0509 0.4915 1.0000
6.250 0.9363 0.02057 0.01227 -0.0493 0.4754 1.0000
6.500 0.9560 0.02087 0.01257 -0.0476 0.4590 1.0000
6.750 0.9758 0.02118 0.01286 -0.0460 0.4422 1.0000
7.000 0.9954 0.02149 0.01314 -0.0443 0.4248 1.0000
7.250 1.0144 0.02180 0.01341 -0.0426 0.4069 1.0000
7.500 1.0328 0.02213 0.01370 -0.0407 0.3885 1.0000
7.750 1.0504 0.02250 0.01399 -0.0388 0.3697 1.0000
8.000 1.0672 0.02292 0.01433 -0.0369 0.3507 1.0000
8.250 1.0813 0.02340 0.01482 -0.0345 0.3306 1.0000
8.500 1.0947 0.02393 0.01534 -0.0321 0.3104 1.0000
8.750 1.1072 0.02452 0.01588 -0.0296 0.2903 1.0000
9.000 1.1188 0.02518 0.01647 -0.0271 0.2708 1.0000
9.250 1.1294 0.02595 0.01713 -0.0245 0.2521 1.0000
9.500 1.1398 0.02687 0.01791 -0.0220 0.2343 1.0000
9.750 1.1492 0.02792 0.01884 -0.0194 0.2172 1.0000
10.000 1.1582 0.02903 0.01984 -0.0169 0.2017 1.0000
10.250 1.1647 0.03013 0.02096 -0.0140 0.1878 1.0000
10.500 1.1724 0.03135 0.02217 -0.0114 0.1751 1.0000
10.750 1.1818 0.03266 0.02348 -0.0092 0.1639 1.0000
11.000 1.1941 0.03400 0.02470 -0.0075 0.1542 1.0000
11.250 1.2036 0.03530 0.02603 -0.0055 0.1455 1.0000
11.500 1.2165 0.03683 0.02757 -0.0041 0.1380 1.0000
11.750 1.2312 0.03821 0.02892 -0.0028 0.1314 1.0000
12.000 1.2482 0.03993 0.03067 -0.0019 0.1258 1.0000
12.250 1.2586 0.04151 0.03239 -0.0003 0.1209 1.0000
12.500 1.2904 0.04323 0.03387 -0.0012 0.1155 1.0000
12.750 1.2915 0.04510 0.03605 0.0013 0.1128 1.0000
13.000 1.2975 0.04709 0.03826 0.0031 0.1099 1.0000
13.250 1.3079 0.04895 0.04022 0.0043 0.1071 1.0000
13.500 1.3426 0.05114 0.04221 0.0032 0.1033 1.0000
13.750 1.3316 0.05351 0.04495 0.0061 0.1021 1.0000
14.000 1.3212 0.05625 0.04800 0.0085 0.1008 1.0000
14.250 1.3106 0.05930 0.05133 0.0104 0.0996 1.0000
14.500 1.2988 0.06268 0.05497 0.0118 0.0985 1.0000
14.750 1.2847 0.06642 0.05896 0.0128 0.0977 1.0000
15.000 1.2674 0.07063 0.06341 0.0132 0.0969 1.0000
15.250 1.2433 0.07571 0.06876 0.0130 0.0965 1.0000
15.500 1.1975 0.08354 0.07694 0.0111 0.0970 1.0000
15.750 1.1065 0.09902 0.09289 0.0036 0.0994 1.0000
16.000 0.9747 0.12816 0.12233 -0.0133 0.1032 1.0000
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