Joukovsky f=0% t=18% (joukowsk0018-jf) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=18% (joukowsk0018-jf) Reynolds number: 50,000 Max Cl/Cd: 14.89 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0018-jf-50000.txt Download as CSV file: xf-joukowsk0018-jf-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4141 0.12701 0.11848 0.0226 1.0000 0.4085
-10.250 -0.3827 0.12246 0.11390 0.0219 1.0000 0.4176
-10.000 -0.4174 0.12369 0.11519 0.0220 1.0000 0.4270
-9.750 -0.3647 0.11660 0.10806 0.0207 1.0000 0.4354
-9.500 -0.3851 0.11667 0.10816 0.0209 1.0000 0.4469
-9.250 -0.3477 0.11097 0.10246 0.0196 1.0000 0.4541
-9.000 -0.3562 0.11019 0.10169 0.0198 1.0000 0.4670
-8.750 -0.3308 0.10553 0.09704 0.0187 1.0000 0.4734
-8.500 -0.3288 0.10405 0.09558 0.0188 1.0000 0.4871
-8.250 -0.4047 0.09394 0.08543 0.0107 1.0000 0.4065
-8.000 -0.3872 0.08983 0.08130 0.0093 1.0000 0.4046
-7.750 -0.3816 0.08576 0.07723 0.0079 1.0000 0.4026
-7.500 -0.3857 0.08162 0.07311 0.0064 1.0000 0.4025
-7.250 -0.3982 0.07714 0.06867 0.0047 1.0000 0.4038
-7.000 -0.4284 0.07148 0.06307 0.0027 1.0000 0.4059
-6.750 -0.3726 0.07235 0.06396 0.0042 1.0000 0.4192
-6.500 -0.3941 0.06778 0.05945 0.0029 1.0000 0.4235
-6.250 -0.3857 0.06545 0.05720 0.0029 1.0000 0.4317
-6.000 -0.3766 0.06354 0.05535 0.0031 1.0000 0.4404
-5.750 -0.4422 0.05904 0.05106 0.0059 1.0000 0.4437
-5.500 -0.5647 0.05338 0.04554 0.0138 1.0000 0.4437
-5.250 -0.6266 0.04866 0.04076 0.0180 1.0000 0.4499
-5.000 -0.6072 0.04987 0.04207 0.0210 1.0000 0.4573
-4.750 -0.6583 0.04420 0.03616 0.0229 1.0000 0.4688
-4.500 -0.6301 0.04588 0.03801 0.0252 0.9989 0.4757
-4.250 -0.5848 0.04465 0.03666 0.0193 0.9828 0.4927
-4.000 -0.5440 0.04321 0.03507 0.0137 0.9666 0.5107
-3.750 -0.4676 0.04551 0.03751 0.0099 0.9519 0.5225
-3.500 -0.4219 0.04494 0.03688 0.0058 0.9360 0.5379
-3.250 -0.3944 0.04348 0.03531 0.0026 0.9200 0.5546
-3.000 -0.3252 0.04473 0.03661 -0.0011 0.9050 0.5678
-2.750 -0.2746 0.04448 0.03634 -0.0048 0.8903 0.5824
-2.500 -0.2441 0.04344 0.03522 -0.0072 0.8757 0.5989
-2.250 -0.1830 0.04398 0.03578 -0.0099 0.8605 0.6120
-2.000 -0.1699 0.04349 0.03528 -0.0087 0.8442 0.6244
-1.750 -0.1563 0.04302 0.03477 -0.0076 0.8288 0.6385
-1.500 -0.1016 0.04325 0.03501 -0.0094 0.8152 0.6508
-1.250 -0.1056 0.04250 0.03422 -0.0067 0.8002 0.6654
-1.000 -0.0731 0.04295 0.03470 -0.0059 0.7845 0.6761
-0.750 -0.0519 0.04251 0.03422 -0.0049 0.7721 0.6904
-0.500 -0.0349 0.04251 0.03422 -0.0032 0.7571 0.7036
-0.250 -0.0205 0.04261 0.03434 -0.0014 0.7426 0.7156
0.000 0.0000 0.04206 0.03373 0.0000 0.7319 0.7319
0.250 0.0206 0.04261 0.03434 0.0014 0.7155 0.7427
0.500 0.0351 0.04251 0.03422 0.0032 0.7036 0.7572
0.750 0.0518 0.04252 0.03422 0.0050 0.6905 0.7722
1.000 0.0731 0.04295 0.03470 0.0059 0.6760 0.7845
1.250 0.1055 0.04250 0.03422 0.0067 0.6654 0.8002
1.500 0.1014 0.04325 0.03501 0.0094 0.6509 0.8153
1.750 0.1562 0.04302 0.03477 0.0076 0.6385 0.8288
2.000 0.1702 0.04348 0.03527 0.0087 0.6244 0.8442
2.250 0.1830 0.04397 0.03578 0.0099 0.6119 0.8605
2.500 0.2434 0.04345 0.03524 0.0072 0.5990 0.8757
2.750 0.2744 0.04447 0.03633 0.0048 0.5824 0.8903
3.000 0.3254 0.04472 0.03660 0.0011 0.5679 0.9051
3.250 0.3946 0.04348 0.03531 -0.0027 0.5546 0.9201
3.500 0.4217 0.04498 0.03693 -0.0058 0.5380 0.9361
3.750 0.4678 0.04551 0.03750 -0.0099 0.5226 0.9519
4.000 0.5440 0.04323 0.03509 -0.0137 0.5107 0.9667
4.250 0.5847 0.04466 0.03667 -0.0193 0.4927 0.9829
4.500 0.6302 0.04587 0.03799 -0.0252 0.4757 0.9990
4.750 0.6582 0.04419 0.03614 -0.0228 0.4688 1.0000
5.000 0.6070 0.04986 0.04206 -0.0210 0.4574 1.0000
5.250 0.6251 0.04878 0.04088 -0.0180 0.4500 1.0000
5.500 0.5657 0.05331 0.04546 -0.0138 0.4437 1.0000
5.750 0.4427 0.05900 0.05102 -0.0059 0.4437 1.0000
6.000 0.3771 0.06351 0.05533 -0.0031 0.4404 1.0000
6.250 0.3849 0.06552 0.05727 -0.0030 0.4318 1.0000
6.500 0.3947 0.06775 0.05942 -0.0030 0.4234 1.0000
6.750 0.3733 0.07233 0.06393 -0.0043 0.4192 1.0000
7.000 0.4290 0.07146 0.06305 -0.0027 0.4059 1.0000
7.250 0.3991 0.07711 0.06864 -0.0048 0.4038 1.0000
7.500 0.3864 0.08159 0.07309 -0.0064 0.4024 1.0000
7.750 0.3819 0.08575 0.07722 -0.0080 0.4025 1.0000
8.000 0.3872 0.08982 0.08129 -0.0095 0.4045 1.0000
8.250 0.4046 0.09394 0.08542 -0.0108 0.4065 1.0000
8.500 0.3287 0.10396 0.09549 -0.0189 0.4869 1.0000
8.750 0.3326 0.10557 0.09708 -0.0188 0.4732 1.0000
9.000 0.3560 0.11009 0.10159 -0.0199 0.4668 1.0000
9.250 0.3492 0.11099 0.10248 -0.0198 0.4539 1.0000
9.500 0.3847 0.11656 0.10806 -0.0210 0.4468 1.0000
9.750 0.3661 0.11663 0.10809 -0.0209 0.4352 1.0000
10.000 0.4179 0.12367 0.11516 -0.0222 0.4270 1.0000
10.250 0.3840 0.12247 0.11392 -0.0221 0.4173 1.0000
10.500 0.4161 0.12712 0.11860 -0.0228 0.4084 1.0000
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Polar data table (+)
Polar graphs
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