NACA 2414 (n2414-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 2414 (n2414-il) Reynolds number: 100,000 Max Cl/Cd: 47.77 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2414-il-100000.txt Download as CSV file: xf-n2414-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2414
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4901 0.12030 0.11467 -0.0300 1.0000 0.1630
-11.000 -0.6812 0.07017 0.06439 -0.0629 1.0000 0.0947
-10.750 -0.7034 0.06566 0.05983 -0.0620 1.0000 0.0942
-10.500 -0.7291 0.06152 0.05560 -0.0597 1.0000 0.0937
-10.250 -0.7536 0.05737 0.05128 -0.0569 1.0000 0.0933
-10.000 -0.7749 0.05335 0.04700 -0.0536 1.0000 0.0932
-9.750 -0.7925 0.04955 0.04286 -0.0499 1.0000 0.0935
-9.500 -0.8061 0.04613 0.03898 -0.0460 1.0000 0.0943
-9.250 -0.8067 0.04314 0.03575 -0.0432 1.0000 0.0959
-9.000 -0.7905 0.04194 0.03469 -0.0417 1.0000 0.0984
-8.750 -0.7832 0.04001 0.03258 -0.0393 1.0000 0.1006
-8.500 -0.7777 0.03778 0.03001 -0.0366 1.0000 0.1031
-8.250 -0.7722 0.03563 0.02733 -0.0338 1.0000 0.1060
-8.000 -0.7587 0.03373 0.02537 -0.0321 1.0000 0.1092
-7.750 -0.7426 0.03259 0.02420 -0.0305 1.0000 0.1128
-7.500 -0.7282 0.03122 0.02253 -0.0286 1.0000 0.1173
-7.250 -0.7122 0.02969 0.02081 -0.0271 1.0000 0.1218
-7.000 -0.6940 0.02877 0.01990 -0.0257 1.0000 0.1268
-6.750 -0.6766 0.02780 0.01859 -0.0242 1.0000 0.1330
-6.500 -0.6569 0.02672 0.01766 -0.0232 1.0000 0.1390
-6.250 -0.6377 0.02597 0.01669 -0.0220 1.0000 0.1467
-6.000 -0.6172 0.02510 0.01594 -0.0211 1.0000 0.1544
-5.750 -0.5967 0.02444 0.01508 -0.0201 1.0000 0.1641
-5.500 -0.5761 0.02384 0.01462 -0.0193 1.0000 0.1740
-5.250 -0.5555 0.02324 0.01404 -0.0185 1.0000 0.1853
-5.000 -0.5348 0.02274 0.01352 -0.0177 1.0000 0.1984
-4.750 -0.5143 0.02234 0.01313 -0.0169 1.0000 0.2132
-4.500 -0.4938 0.02199 0.01282 -0.0162 1.0000 0.2294
-4.250 -0.4732 0.02165 0.01259 -0.0155 1.0000 0.2473
-4.000 -0.4270 0.02139 0.01249 -0.0197 0.9933 0.2767
-3.750 -0.3839 0.02109 0.01236 -0.0232 0.9853 0.3091
-3.500 -0.3413 0.02081 0.01225 -0.0265 0.9771 0.3459
-3.250 -0.2957 0.02055 0.01218 -0.0304 0.9699 0.3893
-3.000 -0.2584 0.02020 0.01210 -0.0325 0.9598 0.4321
-2.750 -0.2188 0.01992 0.01209 -0.0350 0.9507 0.4836
-2.500 -0.1778 0.01962 0.01210 -0.0374 0.9420 0.5430
-2.250 -0.1446 0.01937 0.01213 -0.0382 0.9309 0.6051
-2.000 -0.1015 0.01910 0.01218 -0.0403 0.9241 0.6767
-1.750 -0.0741 0.01897 0.01228 -0.0393 0.9116 0.7389
-1.500 -0.0405 0.01892 0.01241 -0.0390 0.9021 0.7998
-1.250 -0.0007 0.01893 0.01250 -0.0396 0.8936 0.8553
-1.000 0.0465 0.01902 0.01258 -0.0417 0.8858 0.9023
-0.750 0.1088 0.01909 0.01258 -0.0470 0.8785 0.9357
-0.500 0.1914 0.01891 0.01229 -0.0564 0.8748 0.9566
-0.250 0.2703 0.01864 0.01193 -0.0658 0.8670 0.9741
0.000 0.3473 0.01809 0.01131 -0.0748 0.8588 0.9906
0.250 0.3990 0.01762 0.01078 -0.0796 0.8453 1.0000
0.500 0.4204 0.01731 0.01040 -0.0786 0.8297 1.0000
0.750 0.4425 0.01705 0.01007 -0.0774 0.8147 1.0000
1.000 0.4656 0.01681 0.00974 -0.0763 0.8006 1.0000
1.250 0.4873 0.01666 0.00950 -0.0750 0.7856 1.0000
1.500 0.5073 0.01663 0.00941 -0.0734 0.7697 1.0000
1.750 0.5279 0.01664 0.00936 -0.0719 0.7541 1.0000
2.000 0.5492 0.01667 0.00932 -0.0705 0.7389 1.0000
2.250 0.5712 0.01672 0.00930 -0.0691 0.7243 1.0000
2.500 0.5944 0.01676 0.00927 -0.0679 0.7102 1.0000
2.750 0.6189 0.01679 0.00920 -0.0668 0.6965 1.0000
3.000 0.6397 0.01697 0.00933 -0.0653 0.6810 1.0000
3.250 0.6611 0.01715 0.00948 -0.0639 0.6658 1.0000
3.500 0.6833 0.01734 0.00963 -0.0625 0.6509 1.0000
3.750 0.7061 0.01752 0.00975 -0.0613 0.6363 1.0000
4.000 0.7295 0.01770 0.00987 -0.0601 0.6217 1.0000
4.250 0.7536 0.01787 0.00995 -0.0590 0.6071 1.0000
4.500 0.7758 0.01808 0.01012 -0.0576 0.5913 1.0000
4.750 0.7973 0.01832 0.01034 -0.0561 0.5751 1.0000
5.000 0.8191 0.01856 0.01056 -0.0547 0.5587 1.0000
5.250 0.8411 0.01881 0.01077 -0.0533 0.5421 1.0000
5.500 0.8631 0.01906 0.01099 -0.0519 0.5251 1.0000
5.750 0.8849 0.01931 0.01121 -0.0505 0.5076 1.0000
6.000 0.9066 0.01957 0.01142 -0.0491 0.4897 1.0000
6.250 0.9279 0.01983 0.01164 -0.0476 0.4712 1.0000
6.500 0.9490 0.02010 0.01186 -0.0461 0.4523 1.0000
6.750 0.9697 0.02039 0.01208 -0.0446 0.4329 1.0000
7.000 0.9881 0.02072 0.01243 -0.0428 0.4120 1.0000
7.250 1.0060 0.02106 0.01277 -0.0408 0.3901 1.0000
7.500 1.0237 0.02143 0.01307 -0.0389 0.3681 1.0000
7.750 1.0405 0.02189 0.01343 -0.0369 0.3455 1.0000
8.000 1.0554 0.02242 0.01395 -0.0347 0.3211 1.0000
8.250 1.0702 0.02307 0.01443 -0.0325 0.2981 1.0000
8.500 1.0830 0.02382 0.01515 -0.0301 0.2736 1.0000
8.750 1.0955 0.02468 0.01586 -0.0278 0.2513 1.0000
9.000 1.1077 0.02567 0.01673 -0.0255 0.2303 1.0000
9.250 1.1191 0.02670 0.01770 -0.0231 0.2109 1.0000
9.500 1.1307 0.02781 0.01873 -0.0209 0.1939 1.0000
9.750 1.1427 0.02898 0.01982 -0.0187 0.1791 1.0000
10.000 1.1552 0.03021 0.02099 -0.0168 0.1664 1.0000
10.250 1.1695 0.03151 0.02214 -0.0151 0.1552 1.0000
10.500 1.1802 0.03269 0.02338 -0.0129 0.1455 1.0000
10.750 1.1939 0.03413 0.02486 -0.0112 0.1367 1.0000
11.000 1.2165 0.03570 0.02620 -0.0110 0.1283 1.0000
11.250 1.2223 0.03705 0.02784 -0.0082 0.1222 1.0000
11.500 1.2487 0.03878 0.02933 -0.0086 0.1152 1.0000
11.750 1.2519 0.04031 0.03119 -0.0057 0.1108 1.0000
12.000 1.2658 0.04180 0.03270 -0.0044 0.1058 1.0000
12.250 1.2838 0.04390 0.03483 -0.0037 0.1014 1.0000
12.500 1.2864 0.04577 0.03698 -0.0012 0.0980 1.0000
12.750 1.2956 0.04750 0.03878 0.0003 0.0946 1.0000
13.000 1.3158 0.04989 0.04113 0.0005 0.0910 1.0000
13.250 1.3064 0.05229 0.04390 0.0036 0.0893 1.0000
13.500 1.2995 0.05490 0.04680 0.0060 0.0875 1.0000
13.750 1.2977 0.05739 0.04946 0.0076 0.0854 1.0000
14.000 1.3022 0.05963 0.05177 0.0087 0.0832 1.0000
14.250 1.3153 0.06265 0.05477 0.0091 0.0810 1.0000
14.500 1.2925 0.06640 0.05887 0.0109 0.0806 1.0000
14.750 1.2677 0.07080 0.06359 0.0119 0.0802 1.0000
15.000 1.2403 0.07593 0.06902 0.0118 0.0801 1.0000
15.250 1.2099 0.08192 0.07529 0.0107 0.0800 1.0000
15.500 1.1761 0.08894 0.08259 0.0084 0.0802 1.0000
15.750 1.1390 0.09719 0.09108 0.0049 0.0806 1.0000
16.000 1.0996 0.10683 0.10091 0.0000 0.0810 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 2414 (n2414-il)