N-14 (n14-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 50,000 Max Cl/Cd: 27.52 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n14-il-50000-n5.txt Download as CSV file: xf-n14-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6653 0.09634 0.08838 -0.0327 1.0000 0.0743
-11.750 -0.7008 0.08527 0.07732 -0.0398 1.0000 0.0736
-11.500 -0.7410 0.07631 0.06829 -0.0449 1.0000 0.0727
-11.250 -0.7769 0.06996 0.06182 -0.0465 1.0000 0.0721
-11.000 -0.8069 0.06531 0.05702 -0.0455 1.0000 0.0719
-10.750 -0.8313 0.06170 0.05323 -0.0428 1.0000 0.0720
-10.500 -0.8507 0.05864 0.04998 -0.0390 1.0000 0.0723
-10.250 -0.8636 0.05555 0.04663 -0.0357 1.0000 0.0730
-10.000 -0.8716 0.05262 0.04338 -0.0323 1.0000 0.0739
-9.750 -0.8773 0.04985 0.04025 -0.0289 1.0000 0.0756
-9.500 -0.8801 0.04714 0.03710 -0.0255 1.0000 0.0775
-9.250 -0.8680 0.04560 0.03555 -0.0237 1.0000 0.0797
-9.000 -0.8584 0.04376 0.03352 -0.0214 1.0000 0.0820
-8.750 -0.8477 0.04168 0.03116 -0.0192 1.0000 0.0842
-8.500 -0.8350 0.03963 0.02876 -0.0171 1.0000 0.0867
-8.250 -0.8204 0.03792 0.02683 -0.0152 1.0000 0.0902
-8.000 -0.8048 0.03662 0.02545 -0.0135 1.0000 0.0944
-7.750 -0.7879 0.03514 0.02369 -0.0118 1.0000 0.0995
-7.500 -0.7677 0.03359 0.02203 -0.0106 1.0000 0.1042
-7.250 -0.7478 0.03221 0.02062 -0.0093 1.0000 0.1103
-7.000 -0.7277 0.03088 0.01916 -0.0080 1.0000 0.1186
-6.750 -0.7099 0.02970 0.01793 -0.0064 1.0000 0.1301
-6.500 -0.6935 0.02856 0.01687 -0.0046 1.0000 0.1433
-6.250 -0.6773 0.02755 0.01591 -0.0027 1.0000 0.1584
-6.000 -0.6620 0.02670 0.01512 -0.0007 1.0000 0.1760
-5.750 -0.6475 0.02594 0.01443 0.0014 1.0000 0.1957
-5.500 -0.6327 0.02525 0.01380 0.0035 1.0000 0.2203
-5.250 -0.6197 0.02457 0.01327 0.0058 1.0000 0.2508
-5.000 -0.6072 0.02386 0.01276 0.0083 1.0000 0.2862
-4.750 -0.5942 0.02310 0.01221 0.0107 1.0000 0.3241
-4.500 -0.5805 0.02236 0.01165 0.0132 1.0000 0.3649
-4.250 -0.5668 0.02170 0.01120 0.0157 1.0000 0.4102
-4.000 -0.5530 0.02110 0.01089 0.0183 1.0000 0.4637
-3.750 -0.5387 0.02064 0.01076 0.0212 1.0000 0.5281
-3.500 -0.5207 0.02039 0.01079 0.0238 1.0000 0.5998
-3.250 -0.4973 0.02040 0.01098 0.0255 1.0000 0.6655
-3.000 -0.4722 0.02056 0.01119 0.0269 1.0000 0.7211
-2.750 -0.4469 0.02081 0.01141 0.0283 1.0000 0.7704
-2.500 -0.4157 0.02119 0.01173 0.0286 1.0000 0.8121
-2.250 -0.3814 0.02161 0.01204 0.0282 1.0000 0.8474
-2.000 -0.3380 0.02215 0.01245 0.0261 1.0000 0.8778
-1.750 -0.2833 0.02275 0.01287 0.0217 1.0000 0.9042
-1.500 -0.2304 0.02314 0.01313 0.0172 1.0000 0.9257
-1.250 -0.1850 0.02336 0.01322 0.0135 1.0000 0.9449
-1.000 -0.1381 0.02347 0.01324 0.0093 1.0000 0.9611
-0.750 -0.0841 0.02352 0.01321 0.0035 1.0000 0.9777
-0.500 -0.0261 0.02348 0.01312 -0.0032 1.0000 0.9947
-0.250 -0.0050 0.02343 0.01304 -0.0035 1.0000 1.0000
0.000 -0.0041 0.02343 0.01303 -0.0001 1.0000 1.0000
0.250 0.0039 0.02344 0.01304 0.0021 0.9983 1.0000
0.500 0.0690 0.02344 0.01306 -0.0060 0.9796 1.0000
0.750 0.1240 0.02333 0.01300 -0.0119 0.9620 1.0000
1.000 0.1674 0.02323 0.01296 -0.0156 0.9474 1.0000
1.250 0.2086 0.02310 0.01291 -0.0187 0.9325 1.0000
1.500 0.2500 0.02293 0.01285 -0.0217 0.9171 1.0000
1.750 0.2937 0.02269 0.01273 -0.0249 0.9011 1.0000
2.000 0.3391 0.02240 0.01259 -0.0281 0.8842 1.0000
2.250 0.3741 0.02214 0.01247 -0.0293 0.8625 1.0000
2.500 0.4135 0.02179 0.01226 -0.0309 0.8395 1.0000
2.750 0.4487 0.02138 0.01198 -0.0314 0.8078 1.0000
3.000 0.4768 0.02102 0.01168 -0.0303 0.7652 1.0000
3.250 0.5007 0.02074 0.01142 -0.0285 0.7146 1.0000
3.500 0.5244 0.02056 0.01117 -0.0266 0.6588 1.0000
3.750 0.5475 0.02055 0.01098 -0.0247 0.6007 1.0000
4.000 0.5660 0.02077 0.01099 -0.0223 0.5442 1.0000
4.250 0.5826 0.02117 0.01115 -0.0198 0.4908 1.0000
4.500 0.5971 0.02171 0.01141 -0.0172 0.4414 1.0000
4.750 0.6097 0.02234 0.01177 -0.0144 0.3939 1.0000
5.000 0.6215 0.02302 0.01221 -0.0116 0.3495 1.0000
5.250 0.6337 0.02368 0.01273 -0.0089 0.3093 1.0000
5.500 0.6464 0.02433 0.01329 -0.0064 0.2729 1.0000
5.750 0.6594 0.02501 0.01388 -0.0039 0.2394 1.0000
6.000 0.6716 0.02576 0.01449 -0.0014 0.2075 1.0000
6.250 0.6847 0.02664 0.01525 0.0010 0.1809 1.0000
6.500 0.6982 0.02768 0.01610 0.0032 0.1617 1.0000
6.750 0.7139 0.02875 0.01712 0.0052 0.1457 1.0000
7.000 0.7299 0.02982 0.01817 0.0070 0.1330 1.0000
7.250 0.7487 0.03095 0.01940 0.0086 0.1231 1.0000
7.500 0.7671 0.03221 0.02059 0.0101 0.1167 1.0000
7.750 0.7867 0.03345 0.02209 0.0115 0.1098 1.0000
8.000 0.8035 0.03465 0.02331 0.0131 0.1038 1.0000
8.250 0.8220 0.03615 0.02495 0.0146 0.0993 1.0000
8.500 0.8395 0.03781 0.02688 0.0161 0.0953 1.0000
8.750 0.8545 0.03930 0.02852 0.0179 0.0913 1.0000
9.000 0.8690 0.04087 0.03010 0.0196 0.0877 1.0000
9.250 0.8780 0.04292 0.03258 0.0221 0.0844 1.0000
9.500 0.8864 0.04503 0.03499 0.0245 0.0817 1.0000
9.750 0.8948 0.04683 0.03693 0.0268 0.0788 1.0000
10.000 0.9053 0.04854 0.03860 0.0286 0.0761 1.0000
10.250 0.8987 0.05135 0.04189 0.0323 0.0742 1.0000
10.500 0.8908 0.05428 0.04517 0.0357 0.0729 1.0000
10.750 0.8784 0.05721 0.04839 0.0392 0.0718 1.0000
11.000 0.8608 0.06009 0.05148 0.0429 0.0709 1.0000
11.250 0.8402 0.06337 0.05495 0.0458 0.0702 1.0000
11.500 0.8147 0.06749 0.05926 0.0472 0.0700 1.0000
11.750 0.7809 0.07323 0.06518 0.0464 0.0706 1.0000
12.000 0.7397 0.08149 0.07356 0.0424 0.0719 1.0000
12.250 0.6995 0.09223 0.08434 0.0356 0.0732 1.0000
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Polar data table (+)
Polar graphs
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