N-14 (n14-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 50,000 Max Cl/Cd: 29.13 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n14-il-50000.txt Download as CSV file: xf-n14-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: N-14
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5056 0.11004 0.10206 -0.0024 1.0000 0.3447
-9.750 -0.6924 0.07822 0.07062 -0.0341 1.0000 0.1646
-9.500 -0.7167 0.07322 0.06564 -0.0330 1.0000 0.1608
-9.250 -0.8022 0.06685 0.05891 -0.0278 1.0000 0.1524
-9.000 -0.8053 0.06272 0.05466 -0.0256 1.0000 0.1512
-8.750 -0.8124 0.05879 0.05053 -0.0227 1.0000 0.1501
-8.500 -0.8196 0.05504 0.04650 -0.0194 1.0000 0.1494
-8.250 -0.8257 0.05158 0.04268 -0.0158 1.0000 0.1499
-8.000 -0.8295 0.04842 0.03908 -0.0120 1.0000 0.1512
-7.750 -0.8296 0.04548 0.03567 -0.0082 1.0000 0.1529
-7.500 -0.8128 0.04283 0.03303 -0.0068 1.0000 0.1568
-7.250 -0.8014 0.04033 0.03026 -0.0043 1.0000 0.1600
-7.000 -0.7908 0.03796 0.02749 -0.0015 1.0000 0.1646
-6.750 -0.7756 0.03588 0.02527 0.0006 1.0000 0.1719
-6.500 -0.7603 0.03400 0.02308 0.0029 1.0000 0.1809
-6.250 -0.7397 0.03208 0.02115 0.0044 1.0000 0.1919
-6.000 -0.7217 0.03042 0.01942 0.0063 1.0000 0.2091
-5.750 -0.7033 0.02882 0.01797 0.0083 1.0000 0.2339
-5.500 -0.6864 0.02738 0.01667 0.0105 1.0000 0.2665
-5.250 -0.6708 0.02621 0.01560 0.0129 1.0000 0.3022
-5.000 -0.6551 0.02514 0.01469 0.0152 1.0000 0.3398
-4.750 -0.6425 0.02420 0.01403 0.0181 1.0000 0.3857
-4.500 -0.6271 0.02307 0.01341 0.0209 1.0000 0.4439
-4.250 -0.6101 0.02181 0.01282 0.0239 1.0000 0.5306
-4.000 -0.5898 0.02136 0.01314 0.0280 1.0000 0.6465
-3.750 -0.5561 0.02227 0.01426 0.0310 1.0000 0.7476
-3.500 -0.5024 0.02388 0.01562 0.0305 1.0000 0.8163
-3.250 -0.3855 0.02634 0.01747 0.0193 1.0000 0.8691
-3.000 -0.2477 0.02777 0.01829 0.0026 1.0000 0.9234
-2.750 -0.1251 0.02721 0.01726 -0.0150 1.0000 0.9708
-2.500 -0.0346 0.02560 0.01535 -0.0290 1.0000 1.0000
-2.250 -0.0287 0.02505 0.01476 -0.0271 1.0000 1.0000
-2.000 -0.0231 0.02459 0.01428 -0.0249 1.0000 1.0000
-1.750 -0.0183 0.02423 0.01390 -0.0224 1.0000 1.0000
-1.500 -0.0144 0.02395 0.01361 -0.0197 1.0000 1.0000
-1.250 -0.0115 0.02374 0.01339 -0.0168 1.0000 1.0000
-1.000 -0.0095 0.02359 0.01323 -0.0136 1.0000 1.0000
-0.750 -0.0082 0.02348 0.01312 -0.0103 1.0000 1.0000
-0.500 -0.0072 0.02342 0.01304 -0.0068 1.0000 1.0000
-0.250 -0.0062 0.02339 0.01300 -0.0034 1.0000 1.0000
0.000 -0.0053 0.02338 0.01299 0.0000 1.0000 1.0000
0.250 -0.0041 0.02341 0.01301 0.0034 1.0000 1.0000
0.500 -0.0026 0.02346 0.01306 0.0068 1.0000 1.0000
0.750 -0.0007 0.02356 0.01315 0.0101 1.0000 1.0000
1.000 0.0018 0.02369 0.01328 0.0132 1.0000 1.0000
1.250 0.0050 0.02388 0.01347 0.0162 1.0000 1.0000
1.500 0.0092 0.02413 0.01372 0.0190 1.0000 1.0000
1.750 0.0142 0.02445 0.01404 0.0215 1.0000 1.0000
2.000 0.0198 0.02485 0.01445 0.0238 1.0000 1.0000
2.250 0.0259 0.02534 0.01496 0.0259 1.0000 1.0000
2.500 0.0684 0.02639 0.01615 0.0207 0.9877 1.0000
2.750 0.1606 0.02779 0.01784 0.0069 0.9565 1.0000
3.000 0.2427 0.02839 0.01874 -0.0040 0.9202 1.0000
3.250 0.3594 0.02800 0.01886 -0.0189 0.8786 1.0000
3.500 0.4930 0.02544 0.01691 -0.0330 0.8222 1.0000
3.750 0.5683 0.02345 0.01523 -0.0370 0.7655 1.0000
4.000 0.6044 0.02248 0.01427 -0.0351 0.7038 1.0000
4.250 0.6284 0.02207 0.01369 -0.0317 0.6383 1.0000
4.500 0.6458 0.02217 0.01344 -0.0278 0.5689 1.0000
4.750 0.6587 0.02264 0.01345 -0.0236 0.5002 1.0000
5.000 0.6707 0.02347 0.01384 -0.0199 0.4367 1.0000
5.250 0.6840 0.02464 0.01463 -0.0167 0.3768 1.0000
5.500 0.6982 0.02603 0.01562 -0.0139 0.3215 1.0000
5.750 0.7126 0.02748 0.01676 -0.0111 0.2745 1.0000
6.000 0.7281 0.02886 0.01804 -0.0085 0.2407 1.0000
6.250 0.7459 0.03023 0.01937 -0.0065 0.2177 1.0000
6.500 0.7660 0.03185 0.02102 -0.0048 0.2023 1.0000
6.750 0.7838 0.03351 0.02280 -0.0029 0.1897 1.0000
7.000 0.8022 0.03541 0.02477 -0.0012 0.1805 1.0000
7.250 0.8177 0.03745 0.02708 0.0010 0.1733 1.0000
7.500 0.8326 0.03965 0.02939 0.0030 0.1666 1.0000
7.750 0.8394 0.04208 0.03229 0.0062 0.1616 1.0000
8.000 0.8489 0.04466 0.03514 0.0089 0.1580 1.0000
8.250 0.8641 0.04738 0.03781 0.0105 0.1533 1.0000
8.500 0.8598 0.05045 0.04139 0.0146 0.1517 1.0000
8.750 0.8521 0.05381 0.04518 0.0185 0.1503 1.0000
9.000 0.8427 0.05752 0.04921 0.0222 0.1503 1.0000
9.250 0.8299 0.06147 0.05342 0.0256 0.1509 1.0000
9.500 0.8151 0.06555 0.05769 0.0287 0.1517 1.0000
9.750 0.8005 0.06977 0.06203 0.0312 0.1526 1.0000
10.000 0.7870 0.07414 0.06647 0.0332 0.1534 1.0000
10.250 0.6379 0.09027 0.08256 0.0260 0.1790 1.0000
10.500 0.5969 0.10311 0.09526 0.0172 0.2112 1.0000
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Polar data table (+)
Polar graphs
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