Joukovsky f=0% t=18% (joukowsk0018-jf) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Joukovsky f=0% t=18% (joukowsk0018-jf) Reynolds number: 500,000 Max Cl/Cd: 70.6 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0018-jf-500000.txt Download as CSV file: xf-joukowsk0018-jf-500000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=18%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -1.2766 0.08850 0.08372 -0.0080 1.0000 0.0613
-18.500 -1.2782 0.08464 0.07975 -0.0099 1.0000 0.0623
-18.250 -1.2799 0.08101 0.07609 -0.0115 1.0000 0.0635
-18.000 -1.2815 0.07740 0.07247 -0.0132 1.0000 0.0646
-17.750 -1.2833 0.07372 0.06874 -0.0148 1.0000 0.0658
-17.500 -1.2846 0.07016 0.06511 -0.0164 1.0000 0.0670
-17.250 -1.2844 0.06687 0.06173 -0.0177 1.0000 0.0682
-17.000 -1.2858 0.06348 0.05828 -0.0190 1.0000 0.0694
-16.750 -1.2891 0.05999 0.05477 -0.0203 1.0000 0.0707
-16.500 -1.2902 0.05675 0.05150 -0.0215 1.0000 0.0721
-16.250 -1.2894 0.05379 0.04846 -0.0225 1.0000 0.0736
-16.000 -1.2872 0.05105 0.04563 -0.0233 1.0000 0.0750
-15.750 -1.2890 0.04805 0.04259 -0.0241 1.0000 0.0765
-15.500 -1.2914 0.04507 0.03959 -0.0248 1.0000 0.0779
-15.250 -1.2903 0.04250 0.03698 -0.0252 1.0000 0.0795
-15.000 -1.2863 0.04026 0.03468 -0.0256 1.0000 0.0813
-14.750 -1.2813 0.03817 0.03250 -0.0258 1.0000 0.0830
-14.500 -1.2833 0.03553 0.02986 -0.0259 1.0000 0.0848
-14.250 -1.2802 0.03340 0.02770 -0.0259 1.0000 0.0867
-14.000 -1.2732 0.03167 0.02591 -0.0258 1.0000 0.0888
-13.750 -1.2653 0.03006 0.02423 -0.0256 1.0000 0.0909
-13.500 -1.2636 0.02803 0.02221 -0.0251 1.0000 0.0930
-13.250 -1.2568 0.02648 0.02063 -0.0246 1.0000 0.0953
-13.000 -1.2460 0.02527 0.01937 -0.0241 1.0000 0.0979
-12.750 -1.2394 0.02385 0.01792 -0.0232 1.0000 0.1005
-12.500 -1.2321 0.02256 0.01664 -0.0222 1.0000 0.1031
-12.250 -1.2206 0.02161 0.01564 -0.0212 1.0000 0.1062
-12.000 -1.2105 0.02065 0.01465 -0.0200 1.0000 0.1091
-11.750 -1.2026 0.01968 0.01370 -0.0183 1.0000 0.1122
-11.500 -1.1904 0.01900 0.01300 -0.0168 1.0000 0.1157
-11.250 -1.1789 0.01836 0.01233 -0.0149 1.0000 0.1190
-11.000 -1.1673 0.01772 0.01172 -0.0129 1.0000 0.1227
-10.750 -1.1479 0.01726 0.01124 -0.0119 1.0000 0.1270
-10.500 -1.1302 0.01667 0.01068 -0.0108 1.0000 0.1314
-10.250 -1.1095 0.01619 0.01022 -0.0100 1.0000 0.1363
-10.000 -1.0877 0.01575 0.00977 -0.0094 1.0000 0.1412
-9.750 -1.0660 0.01526 0.00934 -0.0088 1.0000 0.1467
-9.500 -1.0416 0.01491 0.00897 -0.0084 1.0000 0.1521
-9.250 -1.0188 0.01443 0.00856 -0.0080 1.0000 0.1582
-9.000 -0.9800 0.01408 0.00819 -0.0104 0.9548 0.1654
-8.750 -0.9577 0.01376 0.00786 -0.0094 0.9216 0.1721
-8.250 -0.9167 0.01327 0.00727 -0.0065 0.8770 0.1849
-8.000 -0.8929 0.01309 0.00702 -0.0055 0.8595 0.1915
-7.750 -0.8696 0.01277 0.00670 -0.0047 0.8432 0.1990
-7.500 -0.8441 0.01259 0.00646 -0.0042 0.8284 0.2063
-7.250 -0.8198 0.01230 0.00617 -0.0035 0.8144 0.2143
-7.000 -0.7934 0.01213 0.00595 -0.0031 0.8005 0.2221
-6.750 -0.7677 0.01185 0.00569 -0.0026 0.7875 0.2305
-6.250 -0.7145 0.01145 0.00525 -0.0019 0.7621 0.2476
-6.000 -0.6870 0.01133 0.00506 -0.0017 0.7504 0.2559
-5.750 -0.6602 0.01108 0.00485 -0.0014 0.7381 0.2653
-5.500 -0.6323 0.01097 0.00468 -0.0012 0.7268 0.2740
-5.250 -0.6050 0.01076 0.00449 -0.0010 0.7149 0.2837
-5.000 -0.5768 0.01065 0.00434 -0.0009 0.7038 0.2926
-4.750 -0.5491 0.01047 0.00418 -0.0007 0.6923 0.3025
-4.500 -0.5207 0.01037 0.00404 -0.0006 0.6815 0.3116
-4.250 -0.4926 0.01021 0.00390 -0.0004 0.6701 0.3216
-4.000 -0.4640 0.01012 0.00377 -0.0004 0.6596 0.3311
-3.750 -0.4357 0.00998 0.00366 -0.0003 0.6483 0.3412
-3.500 -0.4069 0.00991 0.00355 -0.0002 0.6379 0.3507
-3.250 -0.3783 0.00979 0.00345 -0.0002 0.6269 0.3609
-3.000 -0.3495 0.00973 0.00335 -0.0001 0.6166 0.3705
-2.750 -0.3206 0.00963 0.00327 -0.0001 0.6057 0.3808
-2.500 -0.2917 0.00958 0.00319 0.0000 0.5954 0.3904
-2.250 -0.2626 0.00949 0.00313 0.0000 0.5847 0.4008
-2.000 -0.2337 0.00947 0.00306 0.0000 0.5745 0.4105
-1.750 -0.2045 0.00938 0.00301 0.0000 0.5639 0.4210
-1.250 -0.1462 0.00931 0.00293 0.0000 0.5433 0.4412
-1.000 -0.1171 0.00931 0.00288 0.0000 0.5328 0.4510
-0.750 -0.0877 0.00925 0.00287 0.0000 0.5227 0.4615
-0.500 -0.0586 0.00927 0.00284 0.0000 0.5122 0.4714
-0.250 -0.0293 0.00923 0.00285 0.0000 0.5023 0.4819
0.000 0.0000 0.00925 0.00283 0.0000 0.4917 0.4917
0.250 0.0292 0.00923 0.00285 0.0000 0.4819 0.5023
0.500 0.0585 0.00927 0.00284 0.0000 0.4714 0.5122
0.750 0.0877 0.00925 0.00287 0.0000 0.4615 0.5228
1.000 0.1170 0.00931 0.00288 0.0000 0.4510 0.5328
1.250 0.1461 0.00931 0.00293 0.0000 0.4412 0.5433
1.750 0.2044 0.00938 0.00301 0.0000 0.4209 0.5639
2.000 0.2337 0.00947 0.00306 0.0000 0.4106 0.5745
2.250 0.2626 0.00949 0.00313 0.0000 0.4008 0.5847
2.500 0.2917 0.00958 0.00319 0.0000 0.3904 0.5954
2.750 0.3206 0.00963 0.00327 0.0001 0.3808 0.6057
3.000 0.3494 0.00973 0.00335 0.0001 0.3705 0.6165
3.250 0.3783 0.00979 0.00345 0.0002 0.3609 0.6269
3.500 0.4069 0.00991 0.00355 0.0002 0.3507 0.6379
3.750 0.4356 0.00998 0.00366 0.0003 0.3412 0.6483
4.000 0.4640 0.01012 0.00377 0.0004 0.3311 0.6596
4.250 0.4926 0.01021 0.00390 0.0005 0.3217 0.6700
4.500 0.5207 0.01037 0.00404 0.0006 0.3117 0.6815
4.750 0.5491 0.01047 0.00418 0.0007 0.3025 0.6923
5.000 0.5768 0.01065 0.00434 0.0009 0.2926 0.7038
5.250 0.6050 0.01076 0.00449 0.0010 0.2837 0.7149
5.500 0.6322 0.01097 0.00468 0.0012 0.2740 0.7268
5.750 0.6602 0.01108 0.00485 0.0014 0.2653 0.7381
6.000 0.6870 0.01133 0.00506 0.0017 0.2559 0.7504
6.250 0.7145 0.01145 0.00525 0.0020 0.2477 0.7621
6.750 0.7677 0.01185 0.00569 0.0026 0.2306 0.7875
7.000 0.7933 0.01213 0.00595 0.0031 0.2220 0.8005
7.250 0.8197 0.01230 0.00617 0.0035 0.2143 0.8145
7.500 0.8441 0.01259 0.00646 0.0042 0.2063 0.8283
7.750 0.8696 0.01277 0.00670 0.0047 0.1990 0.8432
8.000 0.8929 0.01309 0.00702 0.0056 0.1915 0.8596
8.250 0.9167 0.01327 0.00727 0.0065 0.1849 0.8770
8.750 0.9576 0.01375 0.00786 0.0094 0.1720 0.9216
9.000 0.9801 0.01408 0.00819 0.0104 0.1654 0.9548
9.250 1.0188 0.01443 0.00856 0.0080 0.1582 1.0000
9.500 1.0417 0.01491 0.00897 0.0084 0.1521 1.0000
9.750 1.0660 0.01526 0.00933 0.0087 0.1466 1.0000
10.000 1.0877 0.01575 0.00977 0.0094 0.1411 1.0000
10.250 1.1096 0.01619 0.01021 0.0100 0.1362 1.0000
10.500 1.1302 0.01667 0.01068 0.0108 0.1314 1.0000
10.750 1.1480 0.01726 0.01124 0.0119 0.1270 1.0000
11.000 1.1674 0.01772 0.01172 0.0129 0.1227 1.0000
11.250 1.1791 0.01836 0.01233 0.0148 0.1189 1.0000
11.500 1.1908 0.01900 0.01299 0.0167 0.1156 1.0000
11.750 1.2030 0.01967 0.01369 0.0183 0.1121 1.0000
12.000 1.2108 0.02064 0.01465 0.0199 0.1091 1.0000
12.250 1.2213 0.02159 0.01562 0.0212 0.1061 1.0000
12.500 1.2326 0.02255 0.01662 0.0222 0.1032 1.0000
12.750 1.2400 0.02383 0.01790 0.0232 0.1005 1.0000
13.000 1.2467 0.02525 0.01934 0.0240 0.0979 1.0000
13.250 1.2575 0.02645 0.02060 0.0246 0.0954 1.0000
13.500 1.2644 0.02801 0.02218 0.0251 0.0930 1.0000
13.750 1.2662 0.03002 0.02419 0.0255 0.0908 1.0000
14.000 1.2741 0.03164 0.02588 0.0257 0.0888 1.0000
14.250 1.2811 0.03337 0.02767 0.0259 0.0867 1.0000
14.500 1.2842 0.03551 0.02982 0.0258 0.0847 1.0000
14.750 1.2820 0.03816 0.03247 0.0257 0.0828 1.0000
15.000 1.2876 0.04020 0.03461 0.0255 0.0811 1.0000
15.250 1.2917 0.04243 0.03690 0.0252 0.0795 1.0000
15.500 1.2925 0.04501 0.03953 0.0247 0.0779 1.0000
15.750 1.2903 0.04797 0.04250 0.0240 0.0764 1.0000
16.000 1.2888 0.05094 0.04552 0.0232 0.0750 1.0000
16.250 1.2910 0.05370 0.04837 0.0224 0.0735 1.0000
16.500 1.2917 0.05666 0.05140 0.0214 0.0721 1.0000
16.750 1.2910 0.05983 0.05461 0.0203 0.0707 1.0000
17.000 1.2873 0.06338 0.05817 0.0189 0.0694 1.0000
17.250 1.2861 0.06675 0.06161 0.0176 0.0682 1.0000
17.500 1.2863 0.07006 0.06501 0.0163 0.0669 1.0000
17.750 1.2853 0.07358 0.06860 0.0147 0.0657 1.0000
18.000 1.2836 0.07723 0.07230 0.0131 0.0646 1.0000
18.250 1.2818 0.08087 0.07594 0.0115 0.0634 1.0000
18.500 1.2802 0.08449 0.07960 0.0098 0.0623 1.0000
18.750 1.2786 0.08836 0.08358 0.0079 0.0612 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Joukovsky f=0% t=18% (joukowsk0018-jf)