Joukovsky f=0% t=21% (joukowsk0021-jf) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=21% (joukowsk0021-jf) Reynolds number: 100,000 Max Cl/Cd: 29.92 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0021-jf-100000.txt Download as CSV file: xf-joukowsk0021-jf-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5202 0.12751 0.12114 0.0044 1.0000 0.2150
-12.500 -0.5233 0.12161 0.11522 0.0020 1.0000 0.2148
-12.000 -1.0624 0.04429 0.03676 -0.0289 1.0000 0.2293
-11.750 -1.0529 0.04276 0.03525 -0.0281 1.0000 0.2335
-11.500 -1.0101 0.04329 0.03597 -0.0285 1.0000 0.2391
-11.250 -1.0358 0.04061 0.03312 -0.0256 1.0000 0.2431
-11.000 -1.0695 0.03794 0.03009 -0.0213 1.0000 0.2469
-10.750 -1.0161 0.03830 0.03082 -0.0231 1.0000 0.2527
-10.500 -1.0070 0.03728 0.02976 -0.0218 1.0000 0.2582
-10.250 -1.0230 0.03518 0.02735 -0.0187 1.0000 0.2635
-10.000 -0.9804 0.03520 0.02769 -0.0199 1.0000 0.2692
-9.750 -0.9658 0.03449 0.02699 -0.0190 1.0000 0.2752
-9.500 -0.9804 0.03303 0.02529 -0.0153 1.0000 0.2806
-9.250 -0.9664 0.03286 0.02535 -0.0133 1.0000 0.2849
-9.000 -0.9732 0.03281 0.02538 -0.0090 1.0000 0.2885
-8.750 -0.9558 0.03196 0.02437 -0.0096 0.9916 0.2960
-8.500 -0.9035 0.03145 0.02397 -0.0144 0.9805 0.3043
-8.250 -0.8579 0.03074 0.02316 -0.0187 0.9684 0.3142
-8.000 -0.8026 0.03027 0.02280 -0.0237 0.9595 0.3230
-7.750 -0.7610 0.02965 0.02209 -0.0269 0.9466 0.3329
-7.500 -0.7218 0.02921 0.02170 -0.0290 0.9323 0.3408
-7.250 -0.6886 0.02907 0.02157 -0.0298 0.9170 0.3489
-7.000 -0.6709 0.02836 0.02069 -0.0289 0.9006 0.3573
-6.750 -0.6381 0.02854 0.02102 -0.0286 0.8870 0.3639
-6.500 -0.6235 0.02812 0.02043 -0.0267 0.8723 0.3725
-6.250 -0.6015 0.02790 0.02025 -0.0254 0.8572 0.3793
-6.000 -0.5775 0.02797 0.02037 -0.0241 0.8442 0.3864
-5.750 -0.5667 0.02735 0.01949 -0.0218 0.8314 0.3958
-5.500 -0.5371 0.02750 0.01983 -0.0211 0.8180 0.4018
-5.250 -0.5169 0.02736 0.01963 -0.0192 0.8077 0.4101
-5.000 -0.4972 0.02698 0.01917 -0.0183 0.7939 0.4186
-4.750 -0.4714 0.02708 0.01933 -0.0167 0.7846 0.4253
-4.500 -0.4525 0.02673 0.01885 -0.0158 0.7710 0.4354
-4.250 -0.4269 0.02665 0.01882 -0.0143 0.7620 0.4421
-4.000 -0.4013 0.02670 0.01893 -0.0138 0.7490 0.4503
-3.750 -0.3818 0.02625 0.01831 -0.0123 0.7398 0.4600
-3.500 -0.3534 0.02644 0.01865 -0.0118 0.7279 0.4667
-3.250 -0.3315 0.02618 0.01827 -0.0106 0.7180 0.4768
-3.000 -0.3060 0.02611 0.01823 -0.0097 0.7081 0.4845
-2.750 -0.2797 0.02616 0.01833 -0.0089 0.6969 0.4925
-2.500 -0.2582 0.02576 0.01772 -0.0076 0.6895 0.5031
-2.250 -0.2300 0.02599 0.01815 -0.0072 0.6767 0.5099
-2.000 -0.2056 0.02580 0.01785 -0.0061 0.6682 0.5199
-1.750 -0.1805 0.02576 0.01784 -0.0055 0.6578 0.5283
-1.500 -0.1536 0.02583 0.01795 -0.0046 0.6477 0.5364
-1.250 -0.1301 0.02547 0.01738 -0.0036 0.6408 0.5477
-1.000 -0.1030 0.02574 0.01786 -0.0032 0.6282 0.5544
-0.750 -0.0771 0.02560 0.01764 -0.0022 0.6201 0.5644
-0.500 -0.0522 0.02559 0.01764 -0.0016 0.6103 0.5735
-0.250 -0.0254 0.02568 0.01779 -0.0007 0.6002 0.5816
0.000 0.0000 0.02537 0.01727 0.0000 0.5936 0.5936
0.250 0.0254 0.02568 0.01779 0.0007 0.5816 0.6002
0.500 0.0522 0.02559 0.01764 0.0016 0.5735 0.6103
0.750 0.0771 0.02560 0.01764 0.0022 0.5643 0.6201
1.000 0.1030 0.02574 0.01786 0.0031 0.5544 0.6282
1.250 0.1301 0.02547 0.01738 0.0036 0.5477 0.6408
1.500 0.1536 0.02583 0.01795 0.0046 0.5364 0.6477
1.750 0.1805 0.02576 0.01784 0.0055 0.5283 0.6578
2.000 0.2056 0.02580 0.01785 0.0061 0.5198 0.6682
2.250 0.2300 0.02600 0.01815 0.0072 0.5099 0.6767
2.500 0.2582 0.02576 0.01772 0.0076 0.5031 0.6895
2.750 0.2797 0.02616 0.01833 0.0089 0.4925 0.6969
3.000 0.3060 0.02611 0.01823 0.0097 0.4845 0.7081
3.250 0.3315 0.02618 0.01826 0.0106 0.4768 0.7180
3.500 0.3534 0.02645 0.01865 0.0118 0.4668 0.7279
3.750 0.3818 0.02625 0.01831 0.0123 0.4600 0.7398
4.000 0.4013 0.02670 0.01893 0.0138 0.4503 0.7489
4.250 0.4269 0.02665 0.01882 0.0143 0.4421 0.7620
4.500 0.4526 0.02673 0.01885 0.0158 0.4354 0.7710
4.750 0.4714 0.02708 0.01933 0.0167 0.4254 0.7846
5.000 0.4972 0.02697 0.01916 0.0183 0.4186 0.7939
5.250 0.5169 0.02736 0.01963 0.0192 0.4101 0.8077
5.500 0.5371 0.02749 0.01983 0.0211 0.4018 0.8180
5.750 0.5668 0.02735 0.01949 0.0218 0.3958 0.8314
6.000 0.5775 0.02797 0.02037 0.0241 0.3864 0.8442
6.250 0.6015 0.02789 0.02024 0.0254 0.3793 0.8572
6.500 0.6236 0.02811 0.02043 0.0266 0.3725 0.8724
6.750 0.6381 0.02854 0.02102 0.0286 0.3639 0.8871
7.000 0.6710 0.02836 0.02068 0.0288 0.3573 0.9006
7.250 0.6887 0.02906 0.02157 0.0297 0.3489 0.9171
7.500 0.7220 0.02921 0.02169 0.0289 0.3408 0.9324
7.750 0.7610 0.02965 0.02209 0.0269 0.3329 0.9466
8.000 0.8027 0.03026 0.02279 0.0236 0.3230 0.9596
8.250 0.8580 0.03074 0.02316 0.0187 0.3143 0.9684
8.500 0.9038 0.03144 0.02396 0.0143 0.3043 0.9805
8.750 0.9560 0.03195 0.02437 0.0096 0.2960 0.9917
9.000 0.9730 0.03280 0.02537 0.0090 0.2885 1.0000
9.250 0.9663 0.03286 0.02534 0.0133 0.2849 1.0000
9.500 0.9804 0.03302 0.02528 0.0153 0.2806 1.0000
9.750 0.9660 0.03449 0.02699 0.0189 0.2752 1.0000
10.000 0.9807 0.03520 0.02768 0.0199 0.2691 1.0000
10.250 1.0232 0.03519 0.02735 0.0187 0.2635 1.0000
10.500 1.0072 0.03727 0.02975 0.0218 0.2581 1.0000
10.750 1.0167 0.03829 0.03080 0.0231 0.2526 1.0000
11.000 1.0695 0.03794 0.03010 0.0213 0.2469 1.0000
11.250 1.0362 0.04061 0.03312 0.0256 0.2430 1.0000
11.500 1.0111 0.04326 0.03593 0.0284 0.2390 1.0000
11.750 1.0542 0.04273 0.03522 0.0280 0.2335 1.0000
12.000 1.0629 0.04428 0.03676 0.0289 0.2293 1.0000
12.250 0.4714 0.12632 0.12000 -0.0059 0.2286 1.0000
12.500 0.4403 0.13953 0.13333 -0.0124 0.2625 1.0000
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