WORTMANN FX 71-120 AIRFOIL (fx71120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 71-120 AIRFOIL (fx71120-il) Reynolds number: 100,000 Max Cl/Cd: 26.26 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71120-il-100000.txt Download as CSV file: xf-fx71120-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-120 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5172 0.09460 0.08855 -0.0011 1.0000 0.2405
-8.750 -0.8259 0.05285 0.04570 -0.0215 1.0000 0.1496
-8.500 -0.8176 0.04952 0.04228 -0.0202 1.0000 0.1481
-8.250 -0.8140 0.04624 0.03878 -0.0182 1.0000 0.1467
-8.000 -0.8089 0.04328 0.03557 -0.0161 1.0000 0.1458
-7.750 -0.8015 0.04060 0.03262 -0.0139 1.0000 0.1453
-7.500 -0.7920 0.03813 0.02986 -0.0117 1.0000 0.1446
-7.250 -0.7804 0.03584 0.02729 -0.0096 1.0000 0.1439
-7.000 -0.7665 0.03382 0.02502 -0.0076 1.0000 0.1435
-6.750 -0.7509 0.03205 0.02300 -0.0058 1.0000 0.1434
-6.500 -0.7338 0.03049 0.02122 -0.0040 1.0000 0.1436
-6.250 -0.7155 0.02908 0.01963 -0.0024 1.0000 0.1441
-6.000 -0.6965 0.02784 0.01823 -0.0008 1.0000 0.1449
-5.750 -0.6769 0.02674 0.01699 0.0007 1.0000 0.1463
-5.500 -0.6570 0.02574 0.01584 0.0023 1.0000 0.1478
-5.250 -0.6366 0.02481 0.01477 0.0038 1.0000 0.1493
-5.000 -0.6159 0.02397 0.01380 0.0052 1.0000 0.1506
-4.750 -0.5939 0.02283 0.01272 0.0063 1.0000 0.1525
-4.500 -0.5725 0.02197 0.01195 0.0076 1.0000 0.1548
-4.250 -0.5516 0.02126 0.01130 0.0089 1.0000 0.1576
-4.000 -0.5311 0.02062 0.01067 0.0104 1.0000 0.1614
-3.750 -0.5109 0.02006 0.01007 0.0120 1.0000 0.1655
-3.500 -0.4917 0.01930 0.00949 0.0135 1.0000 0.1708
-3.250 -0.4730 0.01876 0.00906 0.0152 1.0000 0.1785
-3.000 -0.4555 0.01816 0.00863 0.0170 1.0000 0.1894
-2.750 -0.4388 0.01759 0.00827 0.0189 1.0000 0.2073
-2.500 -0.4235 0.01690 0.00791 0.0210 1.0000 0.2425
-2.250 -0.4112 0.01596 0.00759 0.0235 1.0000 0.3229
-2.000 -0.3998 0.01522 0.00753 0.0262 1.0000 0.4289
-1.750 -0.3871 0.01481 0.00763 0.0289 1.0000 0.5238
-1.500 -0.3732 0.01459 0.00783 0.0315 1.0000 0.6067
-1.250 -0.3579 0.01453 0.00810 0.0341 1.0000 0.6812
-1.000 -0.3382 0.01461 0.00848 0.0359 0.9993 0.7508
-0.750 -0.2765 0.01517 0.00933 0.0306 0.9855 0.8375
-0.500 -0.1982 0.01600 0.01029 0.0231 0.9747 0.9057
-0.250 -0.0986 0.01706 0.01135 0.0119 0.9701 0.9434
0.000 -0.0001 0.01733 0.01160 0.0000 0.9586 0.9586
0.250 0.0982 0.01706 0.01135 -0.0119 0.9435 0.9701
0.500 0.1982 0.01599 0.01029 -0.0231 0.9054 0.9747
0.750 0.2768 0.01517 0.00932 -0.0307 0.8373 0.9855
1.000 0.3381 0.01461 0.00848 -0.0359 0.7509 0.9993
1.250 0.3580 0.01452 0.00810 -0.0341 0.6815 1.0000
1.500 0.3732 0.01459 0.00783 -0.0315 0.6067 1.0000
1.750 0.3871 0.01481 0.00763 -0.0289 0.5243 1.0000
2.000 0.3997 0.01522 0.00753 -0.0261 0.4287 1.0000
2.250 0.4111 0.01596 0.00759 -0.0234 0.3222 1.0000
2.500 0.4234 0.01691 0.00792 -0.0210 0.2412 1.0000
2.750 0.4387 0.01759 0.00827 -0.0189 0.2068 1.0000
3.000 0.4555 0.01815 0.00862 -0.0170 0.1895 1.0000
3.250 0.4730 0.01875 0.00905 -0.0152 0.1786 1.0000
3.500 0.4916 0.01929 0.00949 -0.0135 0.1710 1.0000
3.750 0.5109 0.02006 0.01006 -0.0120 0.1656 1.0000
4.000 0.5311 0.02062 0.01067 -0.0104 0.1613 1.0000
4.250 0.5516 0.02126 0.01130 -0.0089 0.1577 1.0000
4.500 0.5724 0.02197 0.01195 -0.0076 0.1548 1.0000
4.750 0.5939 0.02283 0.01272 -0.0063 0.1524 1.0000
5.000 0.6158 0.02396 0.01379 -0.0052 0.1506 1.0000
5.250 0.6366 0.02481 0.01477 -0.0037 0.1493 1.0000
5.500 0.6570 0.02574 0.01584 -0.0022 0.1478 1.0000
5.750 0.6769 0.02674 0.01698 -0.0007 0.1462 1.0000
6.000 0.6965 0.02784 0.01823 0.0008 0.1449 1.0000
6.250 0.7155 0.02908 0.01963 0.0024 0.1441 1.0000
6.500 0.7338 0.03048 0.02122 0.0040 0.1436 1.0000
6.750 0.7508 0.03205 0.02301 0.0058 0.1434 1.0000
7.000 0.7665 0.03382 0.02501 0.0076 0.1435 1.0000
7.250 0.7804 0.03584 0.02729 0.0096 0.1439 1.0000
7.500 0.7920 0.03813 0.02986 0.0117 0.1447 1.0000
7.750 0.8016 0.04060 0.03262 0.0139 0.1453 1.0000
8.000 0.8090 0.04329 0.03558 0.0160 0.1459 1.0000
8.250 0.8141 0.04623 0.03877 0.0182 0.1466 1.0000
8.500 0.8176 0.04952 0.04228 0.0202 0.1481 1.0000
8.750 0.8256 0.05286 0.04572 0.0215 0.1495 1.0000
9.000 0.5180 0.09461 0.08855 0.0010 0.2405 1.0000
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Polar data table (+)
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