SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 50,000 Max Cl/Cd: 37.31 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7080-il-50000-n5.txt Download as CSV file: xf-sd7080-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7080 (9.2%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4277 0.09786 0.09074 -0.0308 1.0000 0.0568
-8.750 -0.4232 0.09442 0.08735 -0.0311 1.0000 0.0553
-8.500 -0.4228 0.09075 0.08375 -0.0320 1.0000 0.0540
-8.250 -0.4252 0.08705 0.08013 -0.0332 1.0000 0.0527
-8.000 -0.4306 0.08331 0.07649 -0.0345 1.0000 0.0515
-7.750 -0.4382 0.07918 0.07248 -0.0366 1.0000 0.0504
-7.500 -0.4456 0.07413 0.06748 -0.0399 1.0000 0.0490
-7.250 -0.4559 0.06816 0.06148 -0.0434 1.0000 0.0473
-7.000 -0.4661 0.06209 0.05505 -0.0464 1.0000 0.0454
-6.750 -0.4637 0.05842 0.05128 -0.0461 1.0000 0.0451
-6.500 -0.4596 0.05478 0.04747 -0.0458 1.0000 0.0449
-6.250 -0.4533 0.05115 0.04361 -0.0455 1.0000 0.0447
-6.000 -0.4445 0.04754 0.03967 -0.0451 1.0000 0.0447
-5.750 -0.4329 0.04406 0.03568 -0.0448 1.0000 0.0452
-5.500 -0.4198 0.04102 0.03240 -0.0442 1.0000 0.0465
-5.250 -0.4041 0.03875 0.02996 -0.0435 1.0000 0.0482
-5.000 -0.3865 0.03638 0.02727 -0.0428 1.0000 0.0496
-4.750 -0.3669 0.03394 0.02442 -0.0421 1.0000 0.0504
-4.500 -0.3459 0.03171 0.02178 -0.0413 1.0000 0.0513
-4.250 -0.3241 0.02978 0.01949 -0.0403 1.0000 0.0526
-4.000 -0.3017 0.02811 0.01749 -0.0393 1.0000 0.0543
-3.750 -0.2793 0.02669 0.01574 -0.0382 1.0000 0.0564
-3.500 -0.2575 0.02544 0.01435 -0.0370 1.0000 0.0597
-3.250 -0.2361 0.02454 0.01339 -0.0361 1.0000 0.0670
-3.000 -0.2136 0.02362 0.01239 -0.0353 1.0000 0.0756
-2.750 -0.1909 0.02271 0.01140 -0.0345 1.0000 0.0883
-2.500 -0.1672 0.02170 0.01057 -0.0342 1.0000 0.1284
-2.250 -0.1436 0.02029 0.01004 -0.0346 1.0000 0.2681
-2.000 -0.1246 0.01910 0.00992 -0.0334 1.0000 0.4856
-1.750 -0.1052 0.01842 0.01014 -0.0304 0.9944 0.7223
-1.500 -0.0516 0.01806 0.00982 -0.0342 0.9855 1.0000
-1.250 -0.0095 0.01835 0.00966 -0.0376 0.9749 1.0000
-1.000 0.0317 0.01864 0.00957 -0.0408 0.9639 1.0000
-0.750 0.0729 0.01891 0.00951 -0.0439 0.9528 1.0000
-0.500 0.1150 0.01915 0.00949 -0.0470 0.9416 1.0000
-0.250 0.1545 0.01934 0.00947 -0.0495 0.9292 1.0000
0.000 0.1924 0.01950 0.00944 -0.0516 0.9159 1.0000
0.250 0.2302 0.01962 0.00942 -0.0536 0.9024 1.0000
0.500 0.2679 0.01972 0.00941 -0.0555 0.8887 1.0000
0.750 0.3045 0.01977 0.00937 -0.0570 0.8743 1.0000
1.000 0.3396 0.01979 0.00931 -0.0581 0.8594 1.0000
1.250 0.3739 0.01977 0.00924 -0.0589 0.8441 1.0000
1.500 0.4077 0.01971 0.00915 -0.0595 0.8284 1.0000
1.750 0.4367 0.01971 0.00912 -0.0593 0.8098 1.0000
2.000 0.4672 0.01967 0.00908 -0.0592 0.7915 1.0000
2.250 0.4989 0.01959 0.00899 -0.0592 0.7734 1.0000
2.500 0.5286 0.01956 0.00895 -0.0589 0.7534 1.0000
2.750 0.5580 0.01954 0.00892 -0.0584 0.7323 1.0000
3.000 0.5873 0.01954 0.00893 -0.0579 0.7105 1.0000
3.250 0.6157 0.01959 0.00895 -0.0573 0.6873 1.0000
3.500 0.6426 0.01972 0.00906 -0.0565 0.6626 1.0000
3.750 0.6696 0.01988 0.00921 -0.0557 0.6378 1.0000
4.000 0.6961 0.02009 0.00937 -0.0548 0.6127 1.0000
4.250 0.7210 0.02039 0.00964 -0.0539 0.5862 1.0000
4.500 0.7454 0.02074 0.00996 -0.0529 0.5598 1.0000
4.750 0.7696 0.02113 0.01037 -0.0519 0.5336 1.0000
5.000 0.7935 0.02156 0.01077 -0.0508 0.5079 1.0000
5.250 0.8170 0.02203 0.01119 -0.0498 0.4825 1.0000
5.500 0.8399 0.02255 0.01172 -0.0488 0.4569 1.0000
5.750 0.8624 0.02312 0.01230 -0.0478 0.4317 1.0000
6.000 0.8847 0.02371 0.01294 -0.0467 0.4074 1.0000
6.250 0.9068 0.02435 0.01358 -0.0457 0.3837 1.0000
6.500 0.9282 0.02504 0.01433 -0.0447 0.3599 1.0000
6.750 0.9493 0.02577 0.01505 -0.0436 0.3375 1.0000
7.000 0.9699 0.02655 0.01590 -0.0425 0.3150 1.0000
7.250 0.9900 0.02737 0.01681 -0.0414 0.2938 1.0000
7.500 1.0095 0.02826 0.01778 -0.0402 0.2726 1.0000
7.750 1.0285 0.02919 0.01872 -0.0390 0.2533 1.0000
8.000 1.0466 0.03021 0.01988 -0.0377 0.2331 1.0000
8.250 1.0640 0.03127 0.02101 -0.0364 0.2149 1.0000
8.500 1.0803 0.03239 0.02219 -0.0351 0.1977 1.0000
8.750 1.0959 0.03365 0.02361 -0.0337 0.1804 1.0000
9.000 1.1100 0.03496 0.02505 -0.0321 0.1641 1.0000
9.250 1.1233 0.03638 0.02659 -0.0306 0.1493 1.0000
9.500 1.1348 0.03790 0.02822 -0.0289 0.1354 1.0000
9.750 1.1459 0.03961 0.03006 -0.0273 0.1232 1.0000
10.000 1.1541 0.04138 0.03195 -0.0254 0.1114 1.0000
10.250 1.1603 0.04324 0.03386 -0.0235 0.1013 1.0000
10.500 1.1626 0.04519 0.03600 -0.0213 0.0918 1.0000
10.750 1.1621 0.04748 0.03851 -0.0191 0.0827 1.0000
11.000 1.1598 0.04979 0.04087 -0.0173 0.0755 1.0000
11.250 1.1551 0.05240 0.04367 -0.0159 0.0685 1.0000
11.500 1.1499 0.05541 0.04679 -0.0149 0.0630 1.0000
11.750 1.1441 0.05879 0.05042 -0.0144 0.0583 1.0000
12.000 1.1383 0.06198 0.05359 -0.0144 0.0546 1.0000
12.250 1.1297 0.06643 0.05834 -0.0148 0.0517 1.0000
12.500 1.1188 0.07136 0.06357 -0.0160 0.0494 1.0000
12.750 1.1071 0.07654 0.06896 -0.0178 0.0476 1.0000
13.000 1.0956 0.08199 0.07459 -0.0201 0.0462 1.0000
13.250 1.0861 0.08724 0.07993 -0.0225 0.0447 1.0000
13.500 1.0787 0.09230 0.08499 -0.0246 0.0433 1.0000
13.750 1.0615 0.09992 0.09285 -0.0287 0.0432 1.0000
14.000 1.0427 0.10831 0.10144 -0.0335 0.0433 1.0000
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Polar data table (+)
Polar graphs
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