NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 50,000 Max Cl/Cd: 21.48 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20414-il-50000-n5.txt Download as CSV file: xf-sc20414-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0414 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6899 0.09937 0.09043 -0.0402 1.0000 0.0841
-12.250 -0.7360 0.08764 0.07857 -0.0473 1.0000 0.0837
-12.000 -0.7770 0.07897 0.06972 -0.0517 1.0000 0.0834
-11.750 -0.8111 0.07248 0.06303 -0.0539 1.0000 0.0834
-11.500 -0.8398 0.06739 0.05771 -0.0545 1.0000 0.0837
-11.250 -0.8651 0.06331 0.05338 -0.0536 1.0000 0.0841
-11.000 -0.8859 0.05969 0.04947 -0.0525 1.0000 0.0847
-10.750 -0.8750 0.05780 0.04761 -0.0517 1.0000 0.0864
-10.500 -0.8702 0.05565 0.04537 -0.0508 1.0000 0.0882
-10.250 -0.8672 0.05329 0.04284 -0.0497 1.0000 0.0900
-10.000 -0.8638 0.05078 0.04008 -0.0484 1.0000 0.0918
-9.750 -0.8589 0.04827 0.03722 -0.0472 1.0000 0.0939
-9.500 -0.8496 0.04610 0.03481 -0.0459 1.0000 0.0964
-9.250 -0.8334 0.04466 0.03340 -0.0449 1.0000 0.0991
-9.000 -0.8186 0.04307 0.03170 -0.0437 1.0000 0.1022
-8.750 -0.8035 0.04138 0.02976 -0.0425 1.0000 0.1057
-8.500 -0.7863 0.03990 0.02817 -0.0413 1.0000 0.1093
-8.250 -0.7679 0.03877 0.02708 -0.0401 1.0000 0.1132
-8.000 -0.7492 0.03759 0.02579 -0.0388 1.0000 0.1177
-7.750 -0.7298 0.03648 0.02461 -0.0373 1.0000 0.1225
-7.500 -0.7107 0.03559 0.02380 -0.0358 1.0000 0.1278
-7.250 -0.6909 0.03474 0.02279 -0.0342 1.0000 0.1342
-7.000 -0.6720 0.03396 0.02213 -0.0324 1.0000 0.1405
-6.750 -0.6543 0.03322 0.02137 -0.0307 1.0000 0.1483
-6.500 -0.6380 0.03246 0.02071 -0.0288 1.0000 0.1560
-6.250 -0.6222 0.03174 0.01995 -0.0269 1.0000 0.1663
-6.000 -0.6082 0.03090 0.01929 -0.0251 1.0000 0.1769
-5.750 -0.5942 0.03005 0.01857 -0.0235 1.0000 0.1906
-5.500 -0.5802 0.02911 0.01781 -0.0221 1.0000 0.2082
-5.250 -0.5656 0.02809 0.01698 -0.0210 1.0000 0.2332
-5.000 -0.5506 0.02683 0.01613 -0.0205 1.0000 0.2712
-4.750 -0.5346 0.02553 0.01550 -0.0200 1.0000 0.3421
-4.500 -0.5247 0.02585 0.01672 -0.0148 1.0000 0.4370
-4.250 -0.5132 0.02736 0.01857 -0.0085 1.0000 0.5098
-4.000 -0.4934 0.02787 0.01896 -0.0070 1.0000 0.5640
-3.750 -0.4731 0.02838 0.01934 -0.0058 1.0000 0.5995
-3.500 -0.4522 0.02884 0.01965 -0.0047 1.0000 0.6278
-3.250 -0.4353 0.02958 0.02031 -0.0019 1.0000 0.6473
-3.000 -0.4187 0.03026 0.02091 0.0009 1.0000 0.6657
-2.750 -0.4024 0.03085 0.02144 0.0037 1.0000 0.6833
-2.500 -0.3869 0.03144 0.02197 0.0067 1.0000 0.7011
-2.250 -0.3730 0.03201 0.02250 0.0101 1.0000 0.7188
-2.000 -0.3615 0.03252 0.02301 0.0145 1.0000 0.7337
-1.750 -0.3450 0.03282 0.02327 0.0173 0.9988 0.7484
-1.500 -0.3151 0.03296 0.02334 0.0168 0.9936 0.7610
-1.250 -0.2839 0.03290 0.02319 0.0154 0.9880 0.7698
-1.000 -0.2514 0.03284 0.02306 0.0139 0.9825 0.7769
-0.750 -0.2211 0.03277 0.02293 0.0129 0.9765 0.7840
-0.500 -0.1859 0.03270 0.02281 0.0103 0.9702 0.7912
-0.250 -0.1554 0.03259 0.02268 0.0093 0.9634 0.7959
0.000 -0.1211 0.03251 0.02257 0.0072 0.9564 0.8005
0.250 -0.0867 0.03245 0.02249 0.0047 0.9493 0.8053
0.500 -0.0522 0.03237 0.02242 0.0026 0.9415 0.8092
0.750 -0.0210 0.03229 0.02237 0.0014 0.9332 0.8131
1.000 0.0154 0.03223 0.02235 -0.0009 0.9247 0.8171
1.250 0.0495 0.03215 0.02231 -0.0030 0.9137 0.8207
1.500 0.0935 0.03205 0.02225 -0.0067 0.9031 0.8235
1.750 0.1290 0.03181 0.02210 -0.0082 0.8900 0.8262
2.000 0.1628 0.03156 0.02195 -0.0093 0.8755 0.8292
2.250 0.2033 0.03115 0.02163 -0.0112 0.8587 0.8319
2.500 0.2497 0.03046 0.02106 -0.0136 0.8384 0.8341
2.750 0.2977 0.02951 0.02022 -0.0157 0.8158 0.8364
3.000 0.3330 0.02879 0.01961 -0.0160 0.7899 0.8394
3.250 0.3671 0.02794 0.01887 -0.0156 0.7607 0.8421
3.500 0.3949 0.02722 0.01824 -0.0142 0.7247 0.8449
3.750 0.4204 0.02664 0.01774 -0.0127 0.6767 0.8479
4.000 0.4506 0.02608 0.01711 -0.0117 0.6051 0.8509
4.250 0.4856 0.02589 0.01621 -0.0111 0.4753 0.8537
4.500 0.5040 0.02682 0.01637 -0.0096 0.3671 0.8568
4.750 0.5191 0.02771 0.01681 -0.0079 0.3011 0.8595
5.000 0.5372 0.02860 0.01736 -0.0068 0.2574 0.8621
5.250 0.5584 0.02941 0.01798 -0.0063 0.2269 0.8652
5.500 0.5816 0.03027 0.01863 -0.0062 0.2051 0.8685
5.750 0.6082 0.03111 0.01939 -0.0066 0.1871 0.8717
6.000 0.6337 0.03184 0.02006 -0.0065 0.1732 0.8747
6.250 0.6614 0.03255 0.02083 -0.0067 0.1609 0.8776
6.500 0.6909 0.03340 0.02169 -0.0073 0.1510 0.8804
6.750 0.7202 0.03432 0.02255 -0.0079 0.1422 0.8833
7.000 0.7512 0.03537 0.02374 -0.0088 0.1342 0.8865
7.250 0.7785 0.03634 0.02469 -0.0090 0.1277 0.8898
7.500 0.8052 0.03750 0.02598 -0.0091 0.1219 0.8934
7.750 0.8315 0.03871 0.02735 -0.0093 0.1164 0.8971
8.000 0.8590 0.04001 0.02852 -0.0099 0.1120 0.9007
8.250 0.8821 0.04163 0.03058 -0.0097 0.1074 0.9040
8.500 0.9040 0.04312 0.03227 -0.0094 0.1035 0.9075
8.750 0.9272 0.04449 0.03364 -0.0094 0.1002 0.9114
9.000 0.9452 0.04663 0.03617 -0.0089 0.0969 0.9156
9.250 0.9599 0.04882 0.03875 -0.0080 0.0942 0.9199
9.500 0.9750 0.05075 0.04091 -0.0071 0.0915 0.9248
9.750 0.9930 0.05246 0.04271 -0.0069 0.0892 0.9297
10.000 1.0012 0.05497 0.04552 -0.0056 0.0872 0.9347
10.250 0.9987 0.05833 0.04941 -0.0037 0.0857 0.9404
10.500 0.9929 0.06184 0.05336 -0.0020 0.0845 0.9464
10.750 0.9809 0.06537 0.05727 0.0000 0.0836 0.9536
11.000 0.9633 0.06930 0.06154 0.0015 0.0829 0.9625
11.250 0.9384 0.07417 0.06674 0.0017 0.0825 0.9762
11.500 0.9011 0.08113 0.07404 -0.0006 0.0827 1.0000
11.750 0.8471 0.09279 0.08601 -0.0079 0.0835 1.0000
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Polar data table (+)
Polar graphs
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