SA7024 (sa7024-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 100,000 Max Cl/Cd: 59.8 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7024-il-100000.txt Download as CSV file: xf-sa7024-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SA7024
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3168 0.10731 0.10254 -0.0250 1.0000 0.0664
-9.250 -0.3244 0.10557 0.10086 -0.0272 1.0000 0.0671
-9.000 -0.3316 0.10364 0.09901 -0.0293 1.0000 0.0674
-8.750 -0.3156 0.09691 0.09229 -0.0271 1.0000 0.0691
-8.500 -0.3044 0.09289 0.08828 -0.0256 1.0000 0.0720
-8.250 -0.3019 0.08976 0.08519 -0.0256 1.0000 0.0746
-8.000 -0.3030 0.08687 0.08236 -0.0261 1.0000 0.0775
-7.750 -0.3119 0.08476 0.08034 -0.0275 1.0000 0.0798
-7.500 -0.3245 0.08302 0.07871 -0.0286 1.0000 0.0805
-7.250 -0.3393 0.08142 0.07723 -0.0296 1.0000 0.0808
-7.000 -0.3095 0.07469 0.07045 -0.0251 1.0000 0.0874
-6.750 -0.3169 0.07237 0.06822 -0.0242 1.0000 0.0906
-6.500 -0.3284 0.07029 0.06624 -0.0247 1.0000 0.0927
-6.250 -0.3397 0.06788 0.06391 -0.0305 1.0000 0.0942
-6.000 -0.3379 0.06356 0.05967 -0.0273 1.0000 0.0966
-5.750 -0.3334 0.06078 0.05693 -0.0239 1.0000 0.1007
-5.500 -0.3345 0.05773 0.05390 -0.0267 1.0000 0.1059
-5.250 -0.3441 0.06439 0.05994 -0.0431 1.0000 0.1090
-5.000 -0.3414 0.06155 0.05727 -0.0374 1.0000 0.1117
-4.750 -0.3210 0.05771 0.05322 -0.0439 1.0000 0.1231
-4.500 -0.3152 0.05507 0.05068 -0.0400 1.0000 0.1267
-4.250 -0.2965 0.05152 0.04701 -0.0430 1.0000 0.1387
-4.000 -0.2783 0.04848 0.04386 -0.0447 1.0000 0.1521
-3.750 -0.2604 0.04570 0.04101 -0.0454 1.0000 0.1661
-3.500 -0.2427 0.04309 0.03836 -0.0456 1.0000 0.1811
-3.250 -0.2242 0.04073 0.03596 -0.0456 1.0000 0.1979
-3.000 -0.1604 0.03309 0.02703 -0.0560 1.0000 0.1371
-2.750 -0.1068 0.02524 0.01779 -0.0583 1.0000 0.0615
-2.500 -0.0747 0.02284 0.01463 -0.0584 1.0000 0.0561
-2.250 -0.0488 0.02142 0.01302 -0.0583 1.0000 0.0587
-2.000 -0.0236 0.02038 0.01176 -0.0579 1.0000 0.0630
-1.750 0.0019 0.01927 0.01046 -0.0573 1.0000 0.0643
-1.500 0.0262 0.01847 0.00954 -0.0566 1.0000 0.0669
-1.250 0.0507 0.01755 0.00873 -0.0563 1.0000 0.0748
-1.000 0.0755 0.01689 0.00812 -0.0560 1.0000 0.0975
-0.750 0.0975 0.01369 0.00788 -0.0545 0.9998 1.0000
-0.500 0.1475 0.01420 0.00789 -0.0593 0.9887 1.0000
-0.250 0.1958 0.01463 0.00799 -0.0638 0.9775 1.0000
0.000 0.2436 0.01497 0.00805 -0.0681 0.9662 1.0000
0.250 0.2914 0.01519 0.00809 -0.0722 0.9546 1.0000
0.500 0.3404 0.01531 0.00806 -0.0764 0.9432 1.0000
0.750 0.3859 0.01531 0.00797 -0.0798 0.9303 1.0000
1.000 0.4311 0.01523 0.00782 -0.0829 0.9174 1.0000
1.250 0.4767 0.01507 0.00762 -0.0860 0.9046 1.0000
1.500 0.5209 0.01485 0.00738 -0.0886 0.8914 1.0000
1.750 0.5631 0.01458 0.00713 -0.0906 0.8774 1.0000
2.000 0.6032 0.01429 0.00685 -0.0920 0.8624 1.0000
2.250 0.6371 0.01410 0.00667 -0.0923 0.8436 1.0000
2.500 0.6701 0.01391 0.00653 -0.0923 0.8237 1.0000
2.750 0.7005 0.01380 0.00641 -0.0918 0.8019 1.0000
3.000 0.7302 0.01374 0.00631 -0.0911 0.7793 1.0000
3.250 0.7567 0.01379 0.00635 -0.0900 0.7536 1.0000
3.500 0.7829 0.01389 0.00641 -0.0889 0.7269 1.0000
3.750 0.8084 0.01403 0.00656 -0.0877 0.6987 1.0000
4.000 0.8334 0.01423 0.00669 -0.0864 0.6693 1.0000
4.250 0.8575 0.01448 0.00689 -0.0850 0.6380 1.0000
4.500 0.8811 0.01478 0.00714 -0.0837 0.6056 1.0000
4.750 0.9047 0.01513 0.00740 -0.0824 0.5733 1.0000
5.000 0.9276 0.01553 0.00781 -0.0810 0.5392 1.0000
5.250 0.9502 0.01598 0.00819 -0.0796 0.5047 1.0000
5.500 0.9721 0.01647 0.00863 -0.0783 0.4685 1.0000
5.750 0.9934 0.01701 0.00907 -0.0768 0.4313 1.0000
6.000 1.0140 0.01761 0.00957 -0.0753 0.3932 1.0000
6.250 1.0342 0.01827 0.01023 -0.0738 0.3542 1.0000
6.500 1.0538 0.01901 0.01090 -0.0723 0.3154 1.0000
6.750 1.0728 0.01988 0.01168 -0.0708 0.2769 1.0000
7.000 1.0907 0.02086 0.01256 -0.0692 0.2372 1.0000
7.250 1.1075 0.02204 0.01359 -0.0675 0.1975 1.0000
7.500 1.1231 0.02345 0.01480 -0.0658 0.1603 1.0000
7.750 1.1386 0.02489 0.01621 -0.0640 0.1255 1.0000
8.000 1.1516 0.02627 0.01755 -0.0622 0.0899 1.0000
8.250 1.1610 0.02846 0.01955 -0.0600 0.0584 1.0000
8.500 1.1720 0.03151 0.02253 -0.0575 0.0449 1.0000
8.750 1.1907 0.03402 0.02529 -0.0557 0.0390 1.0000
9.000 1.2093 0.03701 0.02834 -0.0545 0.0358 1.0000
9.250 1.2287 0.04184 0.03343 -0.0535 0.0341 1.0000
9.500 1.2420 0.04531 0.03738 -0.0516 0.0336 1.0000
9.750 1.2497 0.04906 0.04163 -0.0493 0.0332 1.0000
10.000 1.2515 0.05270 0.04578 -0.0467 0.0327 1.0000
10.250 1.2484 0.05648 0.05000 -0.0441 0.0324 1.0000
10.500 1.2398 0.06024 0.05416 -0.0413 0.0322 1.0000
10.750 1.2253 0.06374 0.05797 -0.0382 0.0320 1.0000
11.000 1.2080 0.06751 0.06200 -0.0360 0.0321 1.0000
11.250 1.1892 0.07179 0.06653 -0.0350 0.0323 1.0000
11.500 1.1693 0.07662 0.07157 -0.0353 0.0326 1.0000
11.750 1.1493 0.08219 0.07732 -0.0370 0.0330 1.0000
12.000 1.1293 0.08848 0.08376 -0.0398 0.0334 1.0000
12.250 1.1107 0.09556 0.09094 -0.0433 0.0339 1.0000
12.500 1.0542 0.11252 0.10833 -0.0585 0.0383 1.0000
12.750 1.0201 0.12901 0.12480 -0.0694 0.0409 1.0000
13.000 1.0085 0.13854 0.13429 -0.0744 0.0426 1.0000
13.250 1.0034 0.14581 0.14151 -0.0777 0.0438 1.0000
13.500 1.0037 0.15128 0.14698 -0.0793 0.0451 1.0000
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Polar data table (+)
Polar graphs
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