NACA 0015 (naca0015-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0015 (naca0015-il) Reynolds number: 50,000 Max Cl/Cd: 26.89 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0015-il-50000-n5.txt Download as CSV file: xf-naca0015-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8517 0.08278 0.07391 -0.0340 1.0000 0.0978
-13.000 -0.8995 0.07280 0.06365 -0.0392 1.0000 0.0979
-12.750 -0.9197 0.06746 0.05812 -0.0408 1.0000 0.0991
-12.500 -0.9361 0.06298 0.05343 -0.0414 1.0000 0.1006
-12.250 -0.9504 0.05904 0.04925 -0.0411 1.0000 0.1023
-12.000 -0.9630 0.05549 0.04541 -0.0402 1.0000 0.1043
-11.750 -0.9743 0.05228 0.04184 -0.0384 1.0000 0.1063
-11.500 -0.9598 0.05075 0.04042 -0.0375 1.0000 0.1092
-11.250 -0.9543 0.04894 0.03854 -0.0360 1.0000 0.1124
-11.000 -0.9528 0.04690 0.03628 -0.0340 1.0000 0.1161
-10.750 -0.9490 0.04495 0.03413 -0.0319 1.0000 0.1201
-10.500 -0.9372 0.04365 0.03290 -0.0304 1.0000 0.1244
-10.250 -0.9292 0.04205 0.03114 -0.0285 1.0000 0.1299
-10.000 -0.9182 0.04059 0.02963 -0.0268 1.0000 0.1356
-9.750 -0.9067 0.03932 0.02831 -0.0251 1.0000 0.1420
-9.500 -0.8953 0.03797 0.02687 -0.0233 1.0000 0.1494
-9.250 -0.8831 0.03683 0.02573 -0.0215 1.0000 0.1574
-9.000 -0.8704 0.03567 0.02456 -0.0196 1.0000 0.1661
-8.750 -0.8582 0.03456 0.02331 -0.0177 1.0000 0.1765
-8.500 -0.8450 0.03360 0.02247 -0.0158 1.0000 0.1864
-8.250 -0.8318 0.03263 0.02150 -0.0138 1.0000 0.1979
-8.000 -0.8185 0.03170 0.02054 -0.0118 1.0000 0.2108
-7.750 -0.8051 0.03084 0.01966 -0.0097 1.0000 0.2244
-7.500 -0.7915 0.03005 0.01896 -0.0076 1.0000 0.2384
-7.250 -0.7775 0.02930 0.01826 -0.0055 1.0000 0.2533
-7.000 -0.7633 0.02859 0.01760 -0.0034 1.0000 0.2693
-6.750 -0.7487 0.02792 0.01697 -0.0013 1.0000 0.2860
-6.500 -0.7338 0.02730 0.01639 0.0008 1.0000 0.3037
-6.250 -0.7187 0.02672 0.01586 0.0029 1.0000 0.3221
-6.000 -0.7033 0.02619 0.01536 0.0049 1.0000 0.3413
-5.750 -0.6876 0.02569 0.01489 0.0069 1.0000 0.3612
-5.500 -0.6716 0.02524 0.01450 0.0089 1.0000 0.3812
-5.250 -0.6552 0.02483 0.01418 0.0109 1.0000 0.4014
-5.000 -0.6385 0.02446 0.01387 0.0129 1.0000 0.4221
-4.750 -0.6217 0.02413 0.01360 0.0148 1.0000 0.4436
-4.500 -0.6046 0.02382 0.01333 0.0166 1.0000 0.4655
-4.250 -0.5874 0.02354 0.01310 0.0184 1.0000 0.4877
-4.000 -0.5693 0.02332 0.01296 0.0202 1.0000 0.5091
-3.750 -0.5512 0.02313 0.01284 0.0219 1.0000 0.5309
-3.500 -0.5332 0.02297 0.01274 0.0236 1.0000 0.5535
-3.250 -0.5151 0.02283 0.01263 0.0252 1.0000 0.5766
-3.000 -0.4965 0.02277 0.01266 0.0268 1.0000 0.5988
-2.750 -0.4780 0.02274 0.01272 0.0284 0.9999 0.6214
-2.500 -0.4368 0.02280 0.01280 0.0256 0.9893 0.6497
-2.250 -0.3952 0.02294 0.01302 0.0231 0.9785 0.6753
-2.000 -0.3535 0.02305 0.01317 0.0206 0.9675 0.7018
-1.750 -0.3127 0.02318 0.01335 0.0184 0.9556 0.7263
-1.500 -0.2722 0.02333 0.01354 0.0164 0.9430 0.7494
-1.250 -0.2305 0.02348 0.01371 0.0142 0.9305 0.7721
-1.000 -0.1841 0.02361 0.01385 0.0112 0.9194 0.7942
-0.750 -0.1395 0.02372 0.01397 0.0085 0.9065 0.8144
-0.500 -0.0960 0.02383 0.01409 0.0062 0.8924 0.8328
-0.250 -0.0504 0.02389 0.01416 0.0035 0.8785 0.8500
0.000 0.0000 0.02393 0.01420 0.0000 0.8647 0.8647
0.250 0.0504 0.02389 0.01416 -0.0035 0.8500 0.8785
0.500 0.0960 0.02383 0.01409 -0.0062 0.8328 0.8924
0.750 0.1395 0.02372 0.01397 -0.0085 0.8145 0.9065
1.000 0.1841 0.02361 0.01385 -0.0112 0.7942 0.9194
1.250 0.2305 0.02348 0.01371 -0.0142 0.7721 0.9306
1.500 0.2722 0.02333 0.01354 -0.0164 0.7494 0.9430
1.750 0.3127 0.02318 0.01335 -0.0184 0.7263 0.9556
2.000 0.3534 0.02305 0.01317 -0.0206 0.7018 0.9676
2.250 0.3952 0.02293 0.01302 -0.0231 0.6753 0.9786
2.500 0.4368 0.02280 0.01279 -0.0256 0.6498 0.9893
2.750 0.4780 0.02274 0.01272 -0.0284 0.6214 0.9999
3.000 0.4964 0.02276 0.01266 -0.0267 0.5988 1.0000
3.250 0.5150 0.02283 0.01263 -0.0252 0.5767 1.0000
3.500 0.5331 0.02296 0.01273 -0.0236 0.5535 1.0000
3.750 0.5511 0.02313 0.01284 -0.0219 0.5310 1.0000
4.000 0.5692 0.02332 0.01295 -0.0202 0.5091 1.0000
4.250 0.5873 0.02354 0.01309 -0.0184 0.4878 1.0000
4.500 0.6045 0.02382 0.01332 -0.0166 0.4655 1.0000
4.750 0.6216 0.02413 0.01359 -0.0148 0.4436 1.0000
5.000 0.6384 0.02446 0.01387 -0.0129 0.4221 1.0000
5.250 0.6551 0.02483 0.01418 -0.0109 0.4014 1.0000
5.500 0.6715 0.02523 0.01450 -0.0089 0.3812 1.0000
5.750 0.6876 0.02569 0.01488 -0.0069 0.3612 1.0000
6.000 0.7032 0.02618 0.01536 -0.0049 0.3413 1.0000
6.250 0.7186 0.02672 0.01586 -0.0029 0.3221 1.0000
6.500 0.7338 0.02730 0.01639 -0.0008 0.3037 1.0000
6.750 0.7487 0.02792 0.01697 0.0013 0.2860 1.0000
7.000 0.7633 0.02859 0.01760 0.0034 0.2693 1.0000
7.250 0.7775 0.02930 0.01826 0.0055 0.2533 1.0000
7.500 0.7915 0.03005 0.01895 0.0076 0.2384 1.0000
7.750 0.8051 0.03084 0.01966 0.0097 0.2244 1.0000
8.000 0.8186 0.03169 0.02054 0.0118 0.2107 1.0000
8.250 0.8318 0.03262 0.02149 0.0138 0.1978 1.0000
8.500 0.8451 0.03360 0.02246 0.0158 0.1864 1.0000
8.750 0.8583 0.03456 0.02331 0.0177 0.1764 1.0000
9.000 0.8706 0.03567 0.02455 0.0196 0.1660 1.0000
9.250 0.8833 0.03683 0.02572 0.0214 0.1574 1.0000
9.500 0.8955 0.03796 0.02686 0.0232 0.1494 1.0000
9.750 0.9069 0.03932 0.02831 0.0250 0.1420 1.0000
10.000 0.9185 0.04059 0.02962 0.0268 0.1356 1.0000
10.250 0.9295 0.04205 0.03114 0.0284 0.1299 1.0000
10.500 0.9376 0.04365 0.03289 0.0303 0.1244 1.0000
10.750 0.9496 0.04495 0.03413 0.0318 0.1201 1.0000
11.000 0.9532 0.04691 0.03629 0.0339 0.1161 1.0000
11.250 0.9549 0.04894 0.03854 0.0359 0.1123 1.0000
11.500 0.9606 0.05075 0.04041 0.0374 0.1091 1.0000
11.750 0.9748 0.05230 0.04186 0.0383 0.1063 1.0000
12.000 0.9636 0.05551 0.04544 0.0401 0.1042 1.0000
12.250 0.9511 0.05905 0.04927 0.0410 0.1023 1.0000
12.500 0.9371 0.06298 0.05343 0.0412 0.1005 1.0000
12.750 0.9211 0.06742 0.05808 0.0406 0.0990 1.0000
13.000 0.9015 0.07269 0.06353 0.0391 0.0978 1.0000
13.250 0.8598 0.08171 0.07281 0.0346 0.0975 1.0000
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