12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 50,000 Max Cl/Cd: 22.2 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk-il-50000.txt Download as CSV file: xf-joukowsk-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: 12% JOUKOWSKI 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5899 0.11716 0.10946 0.0364 1.0000 0.3509
-9.500 -0.8393 0.06949 0.06205 -0.0093 1.0000 0.1760
-9.250 -0.8556 0.06310 0.05548 -0.0110 1.0000 0.1767
-8.750 -0.8417 0.05581 0.04799 -0.0109 1.0000 0.1865
-8.500 -0.8542 0.04970 0.04131 -0.0119 1.0000 0.1898
-8.250 -0.8349 0.04741 0.03904 -0.0112 1.0000 0.1978
-8.000 -0.8313 0.04317 0.03421 -0.0113 1.0000 0.2059
-7.750 -0.8089 0.04146 0.03260 -0.0105 1.0000 0.2169
-7.500 -0.7917 0.03903 0.02999 -0.0099 1.0000 0.2286
-7.250 -0.7736 0.03677 0.02752 -0.0093 1.0000 0.2423
-7.000 -0.7529 0.03506 0.02571 -0.0085 1.0000 0.2582
-6.750 -0.7310 0.03356 0.02420 -0.0077 1.0000 0.2754
-6.500 -0.7086 0.03233 0.02297 -0.0067 1.0000 0.2948
-6.250 -0.6870 0.03098 0.02154 -0.0059 1.0000 0.3164
-6.000 -0.6641 0.02991 0.02050 -0.0048 1.0000 0.3384
-5.750 -0.6407 0.02917 0.01987 -0.0035 1.0000 0.3619
-5.500 -0.6183 0.02821 0.01889 -0.0024 1.0000 0.3870
-5.250 -0.5946 0.02767 0.01848 -0.0009 1.0000 0.4115
-5.000 -0.5720 0.02696 0.01780 0.0004 1.0000 0.4377
-4.750 -0.5489 0.02649 0.01744 0.0021 1.0000 0.4630
-4.500 -0.5266 0.02595 0.01694 0.0037 1.0000 0.4888
-4.250 -0.5043 0.02554 0.01661 0.0055 1.0000 0.5143
-4.000 -0.4828 0.02508 0.01622 0.0073 1.0000 0.5394
-3.750 -0.4619 0.02474 0.01595 0.0095 1.0000 0.5641
-3.500 -0.4423 0.02427 0.01554 0.0115 1.0000 0.5892
-3.250 -0.4235 0.02400 0.01537 0.0140 1.0000 0.6123
-3.000 -0.4071 0.02349 0.01489 0.0162 1.0000 0.6383
-2.750 -0.3914 0.02326 0.01476 0.0192 1.0000 0.6600
-2.500 -0.3778 0.02295 0.01452 0.0222 1.0000 0.6834
-2.250 -0.3660 0.02257 0.01417 0.0249 1.0000 0.7082
-2.000 -0.3548 0.02236 0.01404 0.0282 1.0000 0.7310
-1.750 -0.3449 0.02203 0.01373 0.0310 1.0000 0.7574
-1.500 -0.3337 0.02187 0.01363 0.0340 1.0000 0.7819
-1.250 -0.3243 0.02164 0.01343 0.0367 1.0000 0.8104
-1.000 -0.3121 0.02152 0.01337 0.0392 1.0000 0.8398
-0.750 -0.2947 0.02146 0.01334 0.0406 1.0000 0.8721
-0.500 -0.2625 0.02157 0.01347 0.0390 1.0000 0.9089
-0.250 -0.1648 0.02237 0.01423 0.0256 0.9927 0.9432
0.000 0.0003 0.02300 0.01480 -0.0001 0.9703 0.9703
0.250 0.1649 0.02237 0.01423 -0.0256 0.9432 0.9926
0.500 0.2624 0.02157 0.01347 -0.0390 0.9089 1.0000
0.750 0.2947 0.02146 0.01335 -0.0406 0.8723 1.0000
1.000 0.3120 0.02152 0.01336 -0.0392 0.8398 1.0000
1.250 0.3241 0.02164 0.01343 -0.0367 0.8105 1.0000
1.500 0.3337 0.02187 0.01363 -0.0340 0.7819 1.0000
1.750 0.3449 0.02203 0.01373 -0.0310 0.7574 1.0000
2.000 0.3548 0.02235 0.01403 -0.0282 0.7310 1.0000
2.250 0.3660 0.02257 0.01417 -0.0249 0.7082 1.0000
2.500 0.3778 0.02295 0.01452 -0.0222 0.6835 1.0000
2.750 0.3914 0.02326 0.01476 -0.0192 0.6599 1.0000
3.000 0.4071 0.02349 0.01489 -0.0162 0.6383 1.0000
3.250 0.4235 0.02400 0.01537 -0.0140 0.6123 1.0000
3.500 0.4423 0.02427 0.01554 -0.0115 0.5892 1.0000
3.750 0.4619 0.02474 0.01595 -0.0095 0.5641 1.0000
4.000 0.4829 0.02508 0.01621 -0.0073 0.5394 1.0000
4.250 0.5043 0.02554 0.01661 -0.0055 0.5142 1.0000
4.500 0.5266 0.02595 0.01694 -0.0037 0.4888 1.0000
4.750 0.5489 0.02649 0.01744 -0.0021 0.4630 1.0000
5.000 0.5720 0.02696 0.01780 -0.0004 0.4377 1.0000
5.250 0.5946 0.02767 0.01848 0.0009 0.4115 1.0000
5.500 0.6183 0.02821 0.01890 0.0024 0.3871 1.0000
5.750 0.6407 0.02917 0.01987 0.0035 0.3619 1.0000
6.000 0.6641 0.02991 0.02050 0.0048 0.3384 1.0000
6.250 0.6870 0.03098 0.02152 0.0059 0.3164 1.0000
6.500 0.7086 0.03232 0.02297 0.0068 0.2948 1.0000
6.750 0.7310 0.03357 0.02420 0.0077 0.2754 1.0000
7.000 0.7529 0.03506 0.02572 0.0086 0.2582 1.0000
7.250 0.7736 0.03677 0.02753 0.0093 0.2423 1.0000
7.500 0.7916 0.03903 0.02999 0.0099 0.2286 1.0000
7.750 0.8088 0.04145 0.03259 0.0105 0.2169 1.0000
8.000 0.8312 0.04316 0.03420 0.0113 0.2059 1.0000
8.250 0.8348 0.04743 0.03905 0.0112 0.1979 1.0000
8.500 0.8542 0.04969 0.04130 0.0119 0.1898 1.0000
8.750 0.8416 0.05579 0.04797 0.0110 0.1864 1.0000
9.000 0.8170 0.06310 0.05562 0.0087 0.1861 1.0000
9.250 0.7818 0.07167 0.06433 0.0047 0.1884 1.0000
9.500 0.7548 0.07967 0.07229 0.0005 0.1904 1.0000
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Polar data table (+)
Polar graphs
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