NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7301 AIRFOIL (nlr7301-il) Reynolds number: 50,000 Max Cl/Cd: 20.98 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlr7301-il-50000.txt Download as CSV file: xf-nlr7301-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7301 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5529 0.08882 0.08060 -0.0504 1.0000 0.1912
-10.000 -0.5397 0.08655 0.07838 -0.0488 1.0000 0.1930
-9.750 -0.7665 0.07216 0.06377 -0.0470 1.0000 0.1743
-9.500 -0.7876 0.06882 0.06037 -0.0440 1.0000 0.1736
-9.250 -0.8089 0.06547 0.05688 -0.0410 1.0000 0.1729
-9.000 -0.8269 0.06208 0.05329 -0.0382 1.0000 0.1724
-8.750 -0.8401 0.05873 0.04967 -0.0358 1.0000 0.1723
-8.500 -0.8476 0.05552 0.04613 -0.0337 1.0000 0.1730
-8.250 -0.8505 0.05250 0.04266 -0.0320 1.0000 0.1743
-8.000 -0.8386 0.04988 0.04005 -0.0308 1.0000 0.1771
-7.750 -0.8250 0.04779 0.03792 -0.0295 1.0000 0.1803
-7.500 -0.8125 0.04557 0.03548 -0.0283 1.0000 0.1837
-7.250 -0.7992 0.04337 0.03292 -0.0275 1.0000 0.1881
-7.000 -0.7825 0.04126 0.03062 -0.0267 1.0000 0.1929
-6.750 -0.7629 0.03971 0.02912 -0.0256 1.0000 0.1989
-6.500 -0.7436 0.03811 0.02723 -0.0249 1.0000 0.2063
-6.250 -0.7225 0.03665 0.02591 -0.0238 1.0000 0.2144
-6.000 -0.7013 0.03537 0.02445 -0.0231 1.0000 0.2248
-5.750 -0.6803 0.03422 0.02357 -0.0216 1.0000 0.2363
-5.500 -0.6594 0.03313 0.02260 -0.0202 1.0000 0.2508
-5.250 -0.6393 0.03212 0.02174 -0.0186 1.0000 0.2691
-5.000 -0.6201 0.03106 0.02097 -0.0170 1.0000 0.2936
-4.750 -0.6019 0.02979 0.02015 -0.0155 1.0000 0.3303
-4.500 -0.5867 0.02849 0.01992 -0.0131 1.0000 0.4057
-4.250 -0.5810 0.03086 0.02335 -0.0039 1.0000 0.5223
-4.000 -0.5714 0.03453 0.02702 0.0051 1.0000 0.5873
-3.750 -0.5602 0.03739 0.02979 0.0126 1.0000 0.6261
-3.500 -0.5478 0.03995 0.03228 0.0204 1.0000 0.6521
-3.250 -0.5338 0.04179 0.03404 0.0268 1.0000 0.6781
-3.000 -0.5188 0.04303 0.03519 0.0322 1.0000 0.7040
-2.750 -0.5043 0.04377 0.03584 0.0368 1.0000 0.7297
-2.500 -0.4917 0.04407 0.03605 0.0408 1.0000 0.7551
-2.250 -0.4726 0.04437 0.03628 0.0447 1.0000 0.7790
-2.000 -0.4430 0.04466 0.03648 0.0471 1.0000 0.8052
-1.750 -0.4293 0.04441 0.03616 0.0501 1.0000 0.8326
-1.500 -0.2923 0.04531 0.03686 0.0363 1.0000 0.8875
-1.250 -0.2494 0.04469 0.03616 0.0328 1.0000 0.9085
-1.000 -0.2189 0.04403 0.03545 0.0308 1.0000 0.9226
-0.750 -0.1921 0.04343 0.03481 0.0292 1.0000 0.9337
-0.500 -0.1786 0.04292 0.03427 0.0297 1.0000 0.9424
-0.250 -0.1497 0.04249 0.03383 0.0274 1.0000 0.9508
0.000 -0.1316 0.04212 0.03346 0.0270 1.0000 0.9574
0.250 -0.1097 0.04186 0.03320 0.0258 1.0000 0.9636
0.500 -0.0946 0.04165 0.03301 0.0257 1.0000 0.9690
0.750 -0.0710 0.04156 0.03295 0.0240 1.0000 0.9740
1.000 -0.0553 0.04154 0.03297 0.0237 1.0000 0.9788
1.250 -0.0346 0.04162 0.03310 0.0224 1.0000 0.9832
1.500 -0.0150 0.04181 0.03335 0.0212 1.0000 0.9874
1.750 0.0016 0.04209 0.03370 0.0204 1.0000 0.9918
2.000 0.0212 0.04250 0.03420 0.0188 1.0000 0.9958
2.250 0.4038 0.04045 0.03270 -0.0376 0.8687 1.0000
2.500 0.5755 0.03097 0.02381 -0.0487 0.7560 1.0000
2.750 0.5958 0.02932 0.01940 -0.0385 0.3604 1.0000
3.000 0.6070 0.03069 0.02009 -0.0360 0.3114 1.0000
3.250 0.6273 0.03155 0.02069 -0.0349 0.2803 1.0000
3.500 0.6534 0.03231 0.02124 -0.0348 0.2579 1.0000
3.750 0.6808 0.03310 0.02185 -0.0348 0.2409 1.0000
4.000 0.7096 0.03405 0.02252 -0.0352 0.2278 1.0000
4.250 0.7309 0.03485 0.02344 -0.0343 0.2177 1.0000
4.500 0.7568 0.03608 0.02445 -0.0344 0.2097 1.0000
4.750 0.7742 0.03702 0.02566 -0.0329 0.2034 1.0000
5.000 0.7933 0.03810 0.02678 -0.0319 0.1975 1.0000
5.250 0.8144 0.03961 0.02820 -0.0314 0.1930 1.0000
5.500 0.8287 0.04107 0.02992 -0.0296 0.1905 1.0000
5.750 0.8403 0.04254 0.03170 -0.0274 0.1882 1.0000
6.000 0.8498 0.04409 0.03352 -0.0251 0.1859 1.0000
6.250 0.8573 0.04568 0.03533 -0.0225 0.1837 1.0000
6.500 0.8633 0.04730 0.03715 -0.0199 0.1818 1.0000
6.750 0.8676 0.04900 0.03902 -0.0170 0.1804 1.0000
7.000 0.8683 0.05083 0.04106 -0.0137 0.1797 1.0000
7.250 0.8620 0.05282 0.04334 -0.0096 0.1801 1.0000
7.500 0.8493 0.05489 0.04571 -0.0049 0.1810 1.0000
7.750 0.8313 0.05697 0.04808 0.0003 0.1823 1.0000
8.000 0.8090 0.05906 0.05042 0.0057 0.1839 1.0000
8.250 0.7885 0.06175 0.05338 0.0098 0.1859 1.0000
8.500 0.7766 0.06540 0.05727 0.0116 0.1882 1.0000
8.750 0.7746 0.06956 0.06158 0.0117 0.1905 1.0000
9.000 0.7910 0.07403 0.06607 0.0104 0.1923 1.0000
9.250 0.6638 0.08692 0.07969 0.0076 0.2117 1.0000
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Polar data table (+)
Polar graphs
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