N-12 (n12-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 50,000 Max Cl/Cd: 28.91 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n12-il-50000.txt Download as CSV file: xf-n12-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: N-12
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 -0.6140 0.09376 0.08635 -0.0132 1.0000 0.1884
-9.250 -0.6665 0.08121 0.07395 -0.0240 1.0000 0.1583
-9.000 -0.7332 0.07390 0.06657 -0.0252 1.0000 0.1482
-8.750 -0.7359 0.06900 0.06162 -0.0245 1.0000 0.1432
-8.500 -0.7871 0.06315 0.05516 -0.0213 1.0000 0.1347
-8.250 -0.7789 0.05876 0.05068 -0.0200 1.0000 0.1326
-8.000 -0.7783 0.05470 0.04636 -0.0178 1.0000 0.1302
-7.750 -0.7782 0.05079 0.04208 -0.0152 1.0000 0.1281
-7.500 -0.7745 0.04724 0.03812 -0.0125 1.0000 0.1271
-7.250 -0.7665 0.04426 0.03475 -0.0099 1.0000 0.1284
-7.000 -0.7558 0.04149 0.03156 -0.0075 1.0000 0.1302
-6.750 -0.7420 0.03880 0.02844 -0.0051 1.0000 0.1317
-6.500 -0.7248 0.03630 0.02549 -0.0031 1.0000 0.1330
-6.250 -0.7053 0.03411 0.02279 -0.0012 1.0000 0.1351
-6.000 -0.6810 0.03187 0.02064 -0.0006 1.0000 0.1410
-5.750 -0.6581 0.03020 0.01869 0.0008 1.0000 0.1490
-5.500 -0.6306 0.02828 0.01687 0.0013 1.0000 0.1584
-5.250 -0.6022 0.02650 0.01514 0.0018 1.0000 0.1724
-5.000 -0.5768 0.02463 0.01347 0.0028 1.0000 0.2008
-4.750 -0.5653 0.02215 0.01204 0.0057 1.0000 0.2941
-4.500 -0.5636 0.02054 0.01140 0.0110 1.0000 0.4502
-4.250 -0.5552 0.01979 0.01133 0.0161 1.0000 0.5634
-4.000 -0.5408 0.01965 0.01147 0.0206 1.0000 0.6499
-3.750 -0.5190 0.01979 0.01169 0.0240 1.0000 0.7177
-3.500 -0.4861 0.02057 0.01246 0.0265 1.0000 0.7847
-3.250 -0.4282 0.02209 0.01368 0.0253 1.0000 0.8462
-3.000 -0.2859 0.02453 0.01533 0.0097 1.0000 0.9084
-2.750 -0.1488 0.02459 0.01476 -0.0097 1.0000 0.9645
-2.500 -0.0589 0.02311 0.01294 -0.0240 1.0000 0.9979
-2.250 -0.0466 0.02226 0.01202 -0.0237 1.0000 1.0000
-2.000 -0.0394 0.02161 0.01132 -0.0221 1.0000 1.0000
-1.750 -0.0316 0.02108 0.01076 -0.0202 1.0000 1.0000
-1.500 -0.0236 0.02066 0.01032 -0.0180 1.0000 1.0000
-1.250 -0.0159 0.02032 0.00997 -0.0157 1.0000 1.0000
-1.000 -0.0089 0.02006 0.00970 -0.0132 1.0000 1.0000
-0.750 -0.0029 0.01986 0.00951 -0.0103 1.0000 1.0000
-0.500 0.0016 0.01974 0.00940 -0.0072 1.0000 1.0000
-0.250 0.0045 0.01968 0.00935 -0.0038 1.0000 1.0000
0.000 0.0061 0.01969 0.00936 -0.0002 1.0000 1.0000
0.250 0.0071 0.01976 0.00943 0.0035 1.0000 1.0000
0.500 0.0084 0.01989 0.00956 0.0070 1.0000 1.0000
0.750 0.0107 0.02009 0.00974 0.0104 1.0000 1.0000
1.000 0.0141 0.02035 0.01000 0.0134 1.0000 1.0000
1.250 0.0186 0.02069 0.01033 0.0161 1.0000 1.0000
1.500 0.0240 0.02111 0.01074 0.0185 1.0000 1.0000
1.750 0.0300 0.02162 0.01125 0.0207 1.0000 1.0000
2.000 0.0365 0.02220 0.01186 0.0225 1.0000 1.0000
2.250 0.1125 0.02330 0.01318 0.0112 0.9751 1.0000
2.500 0.1999 0.02395 0.01414 -0.0011 0.9425 1.0000
2.750 0.2896 0.02404 0.01461 -0.0128 0.9065 1.0000
3.000 0.4051 0.02316 0.01431 -0.0272 0.8641 1.0000
3.250 0.4940 0.02181 0.01337 -0.0349 0.8099 1.0000
3.500 0.5334 0.02140 0.01307 -0.0345 0.7562 1.0000
3.750 0.5622 0.02127 0.01297 -0.0325 0.7066 1.0000
4.000 0.5854 0.02128 0.01291 -0.0296 0.6587 1.0000
4.250 0.6027 0.02125 0.01269 -0.0256 0.6063 1.0000
4.500 0.6132 0.02128 0.01245 -0.0206 0.5471 1.0000
4.750 0.6227 0.02154 0.01251 -0.0161 0.4886 1.0000
5.000 0.6304 0.02200 0.01272 -0.0114 0.4202 1.0000
5.250 0.6315 0.02344 0.01338 -0.0058 0.3058 1.0000
5.500 0.6422 0.02555 0.01476 -0.0022 0.2203 1.0000
5.750 0.6608 0.02692 0.01595 -0.0002 0.1872 1.0000
6.000 0.6839 0.02838 0.01733 0.0012 0.1700 1.0000
6.250 0.7087 0.03007 0.01907 0.0023 0.1589 1.0000
6.500 0.7314 0.03181 0.02082 0.0035 0.1492 1.0000
6.750 0.7537 0.03376 0.02290 0.0047 0.1421 1.0000
7.000 0.7757 0.03632 0.02560 0.0059 0.1384 1.0000
7.250 0.7905 0.03894 0.02874 0.0082 0.1358 1.0000
7.500 0.8023 0.04160 0.03185 0.0107 0.1324 1.0000
7.750 0.8130 0.04445 0.03503 0.0130 0.1299 1.0000
8.000 0.8173 0.04801 0.03906 0.0159 0.1303 1.0000
8.250 0.8156 0.05204 0.04357 0.0189 0.1319 1.0000
8.500 0.8096 0.05627 0.04819 0.0218 0.1338 1.0000
8.750 0.8012 0.06064 0.05285 0.0242 0.1356 1.0000
9.000 0.7919 0.06503 0.05743 0.0263 0.1370 1.0000
9.250 0.7874 0.06939 0.06189 0.0277 0.1385 1.0000
9.500 0.7150 0.07712 0.06984 0.0285 0.1493 1.0000
9.750 0.7156 0.08191 0.07463 0.0287 0.1522 1.0000
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Polar data table (+)
Polar graphs
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