SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 200,000 Max Cl/Cd: 68.64 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd5060-il-200000.txt Download as CSV file: xf-sd5060-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4717 0.09617 0.09270 -0.0147 1.0000 0.0642
-9.000 -0.4952 0.09010 0.08676 -0.0250 1.0000 0.0666
-8.750 -0.5048 0.08461 0.08133 -0.0310 1.0000 0.0668
-8.500 -0.4921 0.08074 0.07748 -0.0265 1.0000 0.0684
-8.250 -0.4825 0.07824 0.07499 -0.0257 1.0000 0.0695
-8.000 -0.4795 0.07514 0.07193 -0.0265 1.0000 0.0709
-7.750 -0.4808 0.07106 0.06790 -0.0297 1.0000 0.0723
-7.500 -0.5435 0.04115 0.03703 -0.0528 1.0000 0.0409
-7.250 -0.5529 0.03150 0.02626 -0.0526 1.0000 0.0358
-7.000 -0.5426 0.02834 0.02258 -0.0508 1.0000 0.0351
-6.750 -0.5309 0.02598 0.01990 -0.0488 1.0000 0.0353
-6.500 -0.5177 0.02438 0.01817 -0.0470 1.0000 0.0364
-6.250 -0.5030 0.02326 0.01693 -0.0453 1.0000 0.0380
-6.000 -0.4871 0.02184 0.01527 -0.0436 1.0000 0.0390
-5.750 -0.4698 0.02041 0.01361 -0.0421 1.0000 0.0397
-5.500 -0.4338 0.01887 0.01181 -0.0439 0.9961 0.0412
-5.250 -0.3950 0.01777 0.01050 -0.0461 0.9912 0.0432
-5.000 -0.3579 0.01623 0.00898 -0.0483 0.9862 0.0476
-4.750 -0.3182 0.01533 0.00801 -0.0508 0.9815 0.0524
-4.500 -0.2813 0.01431 0.00698 -0.0528 0.9752 0.0610
-4.250 -0.2405 0.01316 0.00608 -0.0556 0.9710 0.1090
-4.000 -0.2031 0.01274 0.00580 -0.0578 0.9644 0.1576
-3.750 -0.1623 0.01247 0.00555 -0.0605 0.9591 0.1926
-3.500 -0.1250 0.01220 0.00539 -0.0625 0.9528 0.2279
-3.250 -0.0895 0.01193 0.00520 -0.0640 0.9453 0.2622
-3.000 -0.0565 0.01167 0.00500 -0.0649 0.9374 0.2967
-2.750 -0.0251 0.01135 0.00481 -0.0655 0.9292 0.3322
-2.500 0.0023 0.01108 0.00468 -0.0652 0.9192 0.3745
-2.250 0.0295 0.01078 0.00456 -0.0648 0.9104 0.4269
-2.000 0.0544 0.01048 0.00448 -0.0638 0.9002 0.4887
-1.750 0.0781 0.01019 0.00444 -0.0626 0.8895 0.5589
-1.500 0.1012 0.00990 0.00440 -0.0610 0.8800 0.6374
-1.250 0.1229 0.00961 0.00437 -0.0590 0.8700 0.7203
-1.000 0.1432 0.00938 0.00438 -0.0565 0.8590 0.8058
-0.750 0.1681 0.00919 0.00432 -0.0546 0.8494 0.8935
-0.500 0.2149 0.00900 0.00409 -0.0576 0.8404 0.9705
-0.250 0.2543 0.00894 0.00392 -0.0598 0.8289 1.0000
0.000 0.2777 0.00897 0.00384 -0.0587 0.8169 1.0000
0.250 0.3019 0.00900 0.00375 -0.0576 0.8049 1.0000
0.500 0.3265 0.00903 0.00366 -0.0566 0.7928 1.0000
0.750 0.3516 0.00906 0.00359 -0.0557 0.7797 1.0000
1.000 0.3771 0.00910 0.00354 -0.0549 0.7658 1.0000
1.250 0.4029 0.00914 0.00350 -0.0542 0.7517 1.0000
1.500 0.4289 0.00919 0.00348 -0.0535 0.7373 1.0000
1.750 0.4551 0.00924 0.00347 -0.0528 0.7224 1.0000
2.000 0.4813 0.00931 0.00346 -0.0522 0.7070 1.0000
2.250 0.5076 0.00938 0.00345 -0.0516 0.6909 1.0000
2.500 0.5340 0.00946 0.00348 -0.0510 0.6732 1.0000
2.750 0.5604 0.00955 0.00353 -0.0505 0.6542 1.0000
3.000 0.5867 0.00966 0.00356 -0.0499 0.6347 1.0000
3.250 0.6130 0.00979 0.00362 -0.0493 0.6142 1.0000
3.500 0.6392 0.00993 0.00372 -0.0488 0.5911 1.0000
3.750 0.6653 0.01010 0.00382 -0.0482 0.5668 1.0000
4.000 0.6911 0.01030 0.00393 -0.0477 0.5404 1.0000
4.250 0.7167 0.01054 0.00408 -0.0471 0.5114 1.0000
4.500 0.7420 0.01082 0.00427 -0.0465 0.4783 1.0000
4.750 0.7667 0.01117 0.00448 -0.0459 0.4428 1.0000
5.000 0.7912 0.01157 0.00475 -0.0453 0.4047 1.0000
5.250 0.8149 0.01207 0.00508 -0.0446 0.3647 1.0000
5.500 0.8384 0.01263 0.00546 -0.0440 0.3259 1.0000
5.750 0.8616 0.01324 0.00590 -0.0434 0.2925 1.0000
6.000 0.8848 0.01387 0.00638 -0.0428 0.2632 1.0000
6.250 0.9082 0.01449 0.00691 -0.0422 0.2386 1.0000
6.500 0.9313 0.01514 0.00747 -0.0416 0.2185 1.0000
6.750 0.9547 0.01576 0.00804 -0.0410 0.2009 1.0000
7.000 0.9778 0.01640 0.00864 -0.0404 0.1861 1.0000
7.250 1.0008 0.01705 0.00929 -0.0398 0.1729 1.0000
7.500 1.0235 0.01774 0.00994 -0.0391 0.1610 1.0000
7.750 1.0455 0.01850 0.01064 -0.0384 0.1500 1.0000
8.000 1.0687 0.01902 0.01126 -0.0378 0.1394 1.0000
8.250 1.0908 0.01974 0.01203 -0.0371 0.1296 1.0000
8.500 1.1119 0.02056 0.01285 -0.0363 0.1203 1.0000
8.750 1.1332 0.02123 0.01357 -0.0355 0.1111 1.0000
9.000 1.1539 0.02201 0.01444 -0.0346 0.1020 1.0000
9.250 1.1730 0.02297 0.01541 -0.0337 0.0937 1.0000
9.500 1.1923 0.02368 0.01618 -0.0327 0.0853 1.0000
9.750 1.2105 0.02461 0.01725 -0.0316 0.0771 1.0000
10.000 1.2264 0.02567 0.01828 -0.0304 0.0696 1.0000
10.250 1.2434 0.02630 0.01905 -0.0292 0.0622 1.0000
10.500 1.2570 0.02749 0.02032 -0.0277 0.0557 1.0000
10.750 1.2689 0.02852 0.02138 -0.0261 0.0499 1.0000
11.000 1.2775 0.02987 0.02287 -0.0240 0.0446 1.0000
11.250 1.2833 0.03109 0.02412 -0.0219 0.0401 1.0000
11.500 1.2867 0.03303 0.02621 -0.0197 0.0363 1.0000
11.750 1.2910 0.03465 0.02795 -0.0179 0.0329 1.0000
12.000 1.2903 0.03718 0.03046 -0.0161 0.0304 1.0000
12.250 1.2928 0.03946 0.03297 -0.0147 0.0286 1.0000
12.500 1.2944 0.04173 0.03542 -0.0136 0.0267 1.0000
12.750 1.2953 0.04393 0.03770 -0.0130 0.0250 1.0000
13.000 1.2947 0.04672 0.04056 -0.0124 0.0240 1.0000
13.250 1.2893 0.05054 0.04452 -0.0119 0.0229 1.0000
13.500 1.2854 0.05386 0.04808 -0.0120 0.0223 1.0000
13.750 1.2796 0.05767 0.05212 -0.0125 0.0218 1.0000
14.000 1.2719 0.06191 0.05659 -0.0134 0.0214 1.0000
14.250 1.2620 0.06662 0.06152 -0.0149 0.0210 1.0000
14.500 1.2504 0.07181 0.06692 -0.0169 0.0207 1.0000
14.750 1.2367 0.07763 0.07296 -0.0196 0.0206 1.0000
15.000 1.2210 0.08412 0.07966 -0.0230 0.0205 1.0000
15.250 1.2028 0.09154 0.08730 -0.0272 0.0205 1.0000
15.500 1.1818 0.10000 0.09597 -0.0324 0.0206 1.0000
15.750 1.1573 0.10985 0.10604 -0.0387 0.0209 1.0000
16.000 1.1296 0.12116 0.11756 -0.0461 0.0214 1.0000
16.250 1.0972 0.13447 0.13105 -0.0549 0.0219 1.0000
16.500 1.0604 0.14989 0.14659 -0.0646 0.0227 1.0000
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