Joukovsky f=0% t=21% (joukowsk0021-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: Joukovsky f=0% t=21% (joukowsk0021-jf) Reynolds number: 50,000 Max Cl/Cd: 17.2 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk0021-jf-50000-n5.txt Download as CSV file: xf-joukowsk0021-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=21%
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5498 0.10861 0.09923 -0.0066 1.0000 0.2021
-12.000 -0.5291 0.10784 0.09849 -0.0063 1.0000 0.2051
-11.500 -0.5471 0.09726 0.08788 -0.0109 1.0000 0.2173
-11.000 -0.5725 0.08589 0.07648 -0.0158 1.0000 0.2314
-10.750 -0.5434 0.08654 0.07716 -0.0148 1.0000 0.2338
-10.250 -0.5670 0.07594 0.06655 -0.0190 1.0000 0.2489
-9.750 -0.5977 0.06514 0.05573 -0.0230 1.0000 0.2654
-9.250 -0.6413 0.05444 0.04498 -0.0264 1.0000 0.2828
-9.000 -0.5976 0.05629 0.04696 -0.0252 1.0000 0.2855
-8.750 -0.7112 0.04464 0.03507 -0.0266 1.0000 0.2990
-8.500 -0.6488 0.04696 0.03759 -0.0267 1.0000 0.3027
-8.250 -0.6276 0.04679 0.03752 -0.0262 1.0000 0.3079
-8.000 -0.7113 0.04133 0.03188 -0.0222 0.9803 0.3163
-7.750 -0.6528 0.04193 0.03260 -0.0256 0.9641 0.3225
-7.500 -0.6213 0.04076 0.03134 -0.0284 0.9423 0.3311
-7.250 -0.5996 0.03933 0.02980 -0.0301 0.9210 0.3394
-7.000 -0.5594 0.03943 0.02993 -0.0314 0.9040 0.3462
-6.750 -0.5687 0.03712 0.02733 -0.0300 0.8825 0.3561
-6.500 -0.5283 0.03768 0.02799 -0.0302 0.8676 0.3614
-6.250 -0.5122 0.03713 0.02736 -0.0290 0.8516 0.3690
-6.000 -0.5085 0.03599 0.02607 -0.0271 0.8351 0.3773
-5.750 -0.4797 0.03623 0.02636 -0.0262 0.8211 0.3832
-5.500 -0.4712 0.03535 0.02534 -0.0242 0.8080 0.3921
-5.250 -0.4531 0.03500 0.02497 -0.0230 0.7938 0.3991
-5.000 -0.4288 0.03501 0.02497 -0.0217 0.7824 0.4059
-4.750 -0.4244 0.03390 0.02367 -0.0199 0.7688 0.4163
-4.500 -0.3946 0.03416 0.02400 -0.0189 0.7582 0.4217
-4.250 -0.3745 0.03395 0.02378 -0.0177 0.7454 0.4297
-4.000 -0.3602 0.03329 0.02298 -0.0161 0.7357 0.4390
-3.750 -0.3339 0.03345 0.02322 -0.0153 0.7230 0.4453
-3.500 -0.3172 0.03291 0.02254 -0.0137 0.7141 0.4551
-3.250 -0.2953 0.03283 0.02250 -0.0129 0.7015 0.4625
-3.000 -0.2708 0.03277 0.02242 -0.0117 0.6921 0.4700
-2.750 -0.2554 0.03223 0.02178 -0.0107 0.6813 0.4807
-2.500 -0.2278 0.03240 0.02201 -0.0097 0.6708 0.4870
-2.250 -0.2058 0.03217 0.02172 -0.0086 0.6620 0.4961
-2.000 -0.1854 0.03200 0.02154 -0.0078 0.6506 0.5051
-1.750 -0.1591 0.03199 0.02152 -0.0065 0.6424 0.5125
-1.500 -0.1420 0.03166 0.02112 -0.0058 0.6314 0.5238
-1.250 -0.1151 0.03179 0.02130 -0.0048 0.6220 0.5303
-1.000 -0.0914 0.03173 0.02122 -0.0037 0.6133 0.5393
-0.750 -0.0713 0.03159 0.02107 -0.0030 0.6025 0.5492
-0.500 -0.0443 0.03160 0.02108 -0.0018 0.5950 0.5566
-0.250 -0.0250 0.03156 0.02102 -0.0011 0.5842 0.5676
0.000 0.0000 0.03158 0.02106 0.0000 0.5752 0.5753
0.250 0.0250 0.03156 0.02102 0.0010 0.5676 0.5842
0.500 0.0443 0.03160 0.02107 0.0018 0.5566 0.5950
0.750 0.0713 0.03159 0.02107 0.0030 0.5492 0.6026
1.000 0.0914 0.03173 0.02122 0.0037 0.5393 0.6133
1.250 0.1151 0.03179 0.02131 0.0047 0.5303 0.6220
1.500 0.1420 0.03166 0.02112 0.0058 0.5238 0.6314
1.750 0.1591 0.03198 0.02152 0.0065 0.5125 0.6423
2.000 0.1854 0.03200 0.02154 0.0078 0.5050 0.6506
2.250 0.2058 0.03217 0.02172 0.0086 0.4961 0.6620
2.500 0.2278 0.03240 0.02201 0.0097 0.4870 0.6708
2.750 0.2554 0.03223 0.02178 0.0107 0.4807 0.6813
3.000 0.2708 0.03277 0.02242 0.0117 0.4700 0.6921
3.250 0.2953 0.03283 0.02250 0.0129 0.4625 0.7015
3.500 0.3173 0.03291 0.02254 0.0137 0.4551 0.7141
3.750 0.3340 0.03345 0.02321 0.0153 0.4453 0.7230
4.000 0.3603 0.03329 0.02298 0.0161 0.4390 0.7356
4.250 0.3745 0.03395 0.02378 0.0177 0.4297 0.7455
4.500 0.3947 0.03416 0.02399 0.0189 0.4217 0.7582
4.750 0.4244 0.03390 0.02367 0.0199 0.4163 0.7689
5.000 0.4289 0.03500 0.02496 0.0217 0.4058 0.7824
5.250 0.4532 0.03500 0.02496 0.0230 0.3991 0.7939
5.500 0.4713 0.03535 0.02533 0.0242 0.3921 0.8081
5.750 0.4799 0.03622 0.02636 0.0262 0.3832 0.8211
6.000 0.5087 0.03598 0.02606 0.0270 0.3773 0.8351
6.250 0.5125 0.03712 0.02735 0.0290 0.3690 0.8517
6.500 0.5285 0.03768 0.02799 0.0302 0.3614 0.8677
6.750 0.5690 0.03710 0.02731 0.0300 0.3561 0.8825
7.000 0.5599 0.03941 0.02990 0.0314 0.3461 0.9040
7.250 0.6000 0.03931 0.02979 0.0301 0.3394 0.9210
7.500 0.6218 0.04074 0.03133 0.0284 0.3311 0.9424
7.750 0.6535 0.04189 0.03256 0.0255 0.3224 0.9641
8.000 0.7113 0.04135 0.03191 0.0222 0.3162 0.9807
8.250 0.6285 0.04673 0.03747 0.0261 0.3079 1.0000
8.500 0.6496 0.04693 0.03756 0.0266 0.3027 1.0000
8.750 0.7123 0.04459 0.03502 0.0266 0.2990 1.0000
9.000 0.5990 0.05619 0.04685 0.0252 0.2855 1.0000
9.250 0.6432 0.05428 0.04482 0.0264 0.2828 1.0000
9.750 0.5989 0.06507 0.05566 0.0230 0.2654 1.0000
10.750 0.5448 0.08647 0.07709 0.0147 0.2338 1.0000
11.000 0.5739 0.08579 0.07638 0.0157 0.2314 1.0000
11.500 0.5487 0.09715 0.08777 0.0109 0.2173 1.0000
12.000 0.5306 0.10776 0.09841 0.0062 0.2051 1.0000
12.250 0.5516 0.10849 0.09911 0.0065 0.2021 1.0000
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