NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 50,000 Max Cl/Cd: 25.67 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20710-il-50000-n5.txt Download as CSV file: xf-sc20710-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5960 0.09734 0.08921 -0.0385 1.0000 0.0618
-11.000 -0.6084 0.09043 0.08234 -0.0422 1.0000 0.0616
-10.750 -0.6262 0.08396 0.07592 -0.0456 1.0000 0.0613
-10.500 -0.6481 0.07839 0.07037 -0.0477 1.0000 0.0608
-10.250 -0.6729 0.07382 0.06580 -0.0482 1.0000 0.0604
-10.000 -0.6935 0.06895 0.06085 -0.0497 1.0000 0.0602
-9.750 -0.7078 0.06428 0.05598 -0.0509 1.0000 0.0604
-9.500 -0.7156 0.05971 0.05109 -0.0519 1.0000 0.0610
-9.250 -0.7165 0.05519 0.04613 -0.0529 1.0000 0.0619
-9.000 -0.7101 0.05081 0.04119 -0.0540 1.0000 0.0629
-8.750 -0.6965 0.04740 0.03752 -0.0543 1.0000 0.0639
-8.500 -0.6798 0.04466 0.03456 -0.0544 1.0000 0.0654
-8.250 -0.6611 0.04244 0.03215 -0.0545 1.0000 0.0682
-8.000 -0.6404 0.03994 0.02926 -0.0549 1.0000 0.0718
-7.750 -0.6173 0.03735 0.02608 -0.0552 1.0000 0.0750
-7.500 -0.5959 0.03543 0.02411 -0.0549 1.0000 0.0782
-7.250 -0.5733 0.03393 0.02248 -0.0545 1.0000 0.0832
-7.000 -0.5497 0.03234 0.02054 -0.0538 1.0000 0.0879
-6.750 -0.5282 0.03102 0.01927 -0.0528 1.0000 0.0931
-6.500 -0.5057 0.02994 0.01803 -0.0518 1.0000 0.1000
-6.250 -0.4847 0.02889 0.01694 -0.0501 1.0000 0.1058
-6.000 -0.4627 0.02800 0.01602 -0.0489 1.0000 0.1150
-5.750 -0.4407 0.02707 0.01514 -0.0479 1.0000 0.1245
-5.500 -0.4173 0.02615 0.01421 -0.0474 1.0000 0.1373
-5.250 -0.3921 0.02515 0.01333 -0.0476 1.0000 0.1570
-5.000 -0.3647 0.02396 0.01240 -0.0486 1.0000 0.1910
-4.750 -0.3306 0.02209 0.01140 -0.0521 1.0000 0.2971
-4.500 -0.3193 0.02168 0.01234 -0.0474 1.0000 0.4830
-4.000 -0.2855 0.02305 0.01370 -0.0403 1.0000 0.6415
-3.750 -0.2670 0.02375 0.01427 -0.0373 1.0000 0.6791
-3.500 -0.2539 0.02442 0.01485 -0.0329 1.0000 0.7071
-3.250 -0.2434 0.02499 0.01537 -0.0278 1.0000 0.7336
-3.000 -0.2304 0.02538 0.01569 -0.0236 1.0000 0.7603
-2.750 -0.2199 0.02551 0.01577 -0.0189 1.0000 0.7815
-2.500 -0.2035 0.02545 0.01561 -0.0161 1.0000 0.7993
-2.250 -0.1840 0.02527 0.01535 -0.0144 1.0000 0.8128
-2.000 -0.1617 0.02507 0.01506 -0.0136 1.0000 0.8243
-1.750 -0.1367 0.02491 0.01481 -0.0136 1.0000 0.8344
-1.500 -0.1150 0.02466 0.01450 -0.0128 1.0000 0.8424
-1.250 -0.0871 0.02457 0.01435 -0.0136 1.0000 0.8504
-1.000 -0.0646 0.02435 0.01410 -0.0130 1.0000 0.8571
-0.750 -0.0366 0.02430 0.01402 -0.0139 1.0000 0.8637
-0.500 -0.0120 0.02417 0.01390 -0.0139 1.0000 0.8693
-0.250 0.0147 0.02414 0.01387 -0.0144 1.0000 0.8748
0.000 0.0436 0.02420 0.01396 -0.0156 1.0000 0.8797
0.250 0.0684 0.02418 0.01399 -0.0158 1.0000 0.8845
0.500 0.0957 0.02427 0.01414 -0.0166 1.0000 0.8892
0.750 0.1242 0.02444 0.01440 -0.0178 1.0000 0.8939
1.000 0.1490 0.02454 0.01460 -0.0181 1.0000 0.8985
1.250 0.1754 0.02475 0.01493 -0.0189 1.0000 0.9035
1.500 0.2078 0.02507 0.01540 -0.0209 0.9967 0.9078
1.750 0.2566 0.02538 0.01590 -0.0258 0.9815 0.9110
2.000 0.3103 0.02549 0.01624 -0.0311 0.9602 0.9136
2.250 0.3699 0.02492 0.01595 -0.0362 0.9235 0.9159
2.500 0.4255 0.02351 0.01482 -0.0388 0.8704 0.9182
2.750 0.4552 0.02253 0.01410 -0.0373 0.8121 0.9219
3.000 0.5321 0.02073 0.01160 -0.0403 0.5419 0.9227
3.250 0.5463 0.02257 0.01189 -0.0375 0.3018 0.9269
3.500 0.5653 0.02413 0.01272 -0.0367 0.2022 0.9314
3.750 0.5902 0.02530 0.01361 -0.0366 0.1614 0.9358
4.000 0.6162 0.02633 0.01449 -0.0367 0.1401 0.9401
4.250 0.6456 0.02734 0.01551 -0.0372 0.1238 0.9444
4.500 0.6776 0.02844 0.01667 -0.0380 0.1123 0.9488
4.750 0.7102 0.02957 0.01793 -0.0388 0.1022 0.9539
5.000 0.7428 0.03101 0.01934 -0.0398 0.0950 0.9595
5.250 0.7750 0.03242 0.02104 -0.0405 0.0877 0.9658
5.750 0.8366 0.03611 0.02518 -0.0421 0.0773 0.9896
6.000 0.8658 0.03801 0.02728 -0.0429 0.0723 1.0000
6.250 0.8936 0.04054 0.02993 -0.0438 0.0694 1.0000
6.500 0.9173 0.04348 0.03355 -0.0435 0.0666 1.0000
6.750 0.9381 0.04637 0.03695 -0.0432 0.0635 1.0000
7.000 0.9579 0.04913 0.04003 -0.0431 0.0610 1.0000
7.250 0.9758 0.05226 0.04350 -0.0428 0.0597 1.0000
7.500 0.9907 0.05574 0.04729 -0.0424 0.0587 1.0000
7.750 1.0021 0.05964 0.05145 -0.0419 0.0579 1.0000
8.000 1.0023 0.06414 0.05655 -0.0403 0.0573 1.0000
8.250 0.9975 0.06885 0.06176 -0.0388 0.0568 1.0000
8.500 0.9871 0.07376 0.06708 -0.0376 0.0563 1.0000
8.750 0.9717 0.07871 0.07235 -0.0367 0.0561 1.0000
9.000 0.9529 0.08367 0.07754 -0.0362 0.0562 1.0000
9.250 0.9323 0.08946 0.08351 -0.0375 0.0564 1.0000
9.500 0.9131 0.09607 0.09025 -0.0408 0.0567 1.0000
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Polar data table (+)
Polar graphs
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