FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 50,000 Max Cl/Cd: 27.94 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l120-il-50000.txt Download as CSV file: xf-fx79l120-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6809 0.10034 0.09296 -0.0063 1.0000 0.1799
-10.250 -0.6426 0.10024 0.09276 -0.0012 1.0000 0.1903
-10.000 -0.7851 0.07613 0.06886 -0.0225 1.0000 0.1510
-9.750 -0.8110 0.07079 0.06339 -0.0227 1.0000 0.1479
-9.500 -0.8232 0.06573 0.05819 -0.0224 1.0000 0.1462
-9.250 -0.8362 0.06088 0.05310 -0.0217 1.0000 0.1449
-9.000 -0.8449 0.05643 0.04830 -0.0205 1.0000 0.1449
-8.750 -0.8483 0.05241 0.04386 -0.0190 1.0000 0.1461
-8.500 -0.8475 0.04871 0.03963 -0.0173 1.0000 0.1481
-8.250 -0.8409 0.04522 0.03563 -0.0155 1.0000 0.1502
-8.000 -0.8201 0.04220 0.03263 -0.0149 1.0000 0.1552
-7.750 -0.8058 0.03964 0.02969 -0.0134 1.0000 0.1620
-7.500 -0.7873 0.03692 0.02673 -0.0123 1.0000 0.1684
-7.250 -0.7670 0.03475 0.02433 -0.0112 1.0000 0.1777
-7.000 -0.7444 0.03261 0.02218 -0.0103 1.0000 0.1892
-6.750 -0.7210 0.03059 0.02010 -0.0094 1.0000 0.2027
-6.500 -0.6981 0.02879 0.01834 -0.0084 1.0000 0.2213
-6.250 -0.6750 0.02698 0.01667 -0.0073 1.0000 0.2450
-6.000 -0.6555 0.02527 0.01532 -0.0057 1.0000 0.2804
-5.750 -0.6410 0.02355 0.01416 -0.0031 1.0000 0.3374
-5.500 -0.6327 0.02264 0.01428 0.0016 1.0000 0.4381
-5.250 -0.6213 0.02364 0.01573 0.0078 1.0000 0.5347
-5.000 -0.6039 0.02498 0.01713 0.0132 1.0000 0.5921
-4.750 -0.5834 0.02612 0.01823 0.0181 1.0000 0.6333
-4.500 -0.5640 0.02692 0.01898 0.0227 1.0000 0.6684
-4.250 -0.5405 0.02776 0.01976 0.0269 1.0000 0.7000
-4.000 -0.5123 0.02854 0.02042 0.0305 1.0000 0.7299
-3.750 -0.4807 0.02905 0.02081 0.0329 1.0000 0.7586
-3.500 -0.4634 0.02886 0.02056 0.0358 1.0000 0.7846
-3.250 -0.4055 0.02931 0.02075 0.0334 1.0000 0.8100
-3.000 -0.3860 0.02886 0.02024 0.0346 1.0000 0.8313
-2.750 -0.3475 0.02856 0.01981 0.0329 1.0000 0.8506
-2.500 -0.2990 0.02819 0.01928 0.0289 1.0000 0.8682
-2.250 -0.2672 0.02773 0.01875 0.0270 1.0000 0.8842
-2.000 -0.2451 0.02731 0.01828 0.0263 1.0000 0.8994
-1.750 -0.2208 0.02696 0.01787 0.0250 1.0000 0.9143
-1.500 -0.1926 0.02666 0.01750 0.0227 1.0000 0.9291
-1.250 -0.1563 0.02638 0.01717 0.0189 1.0000 0.9429
-1.000 -0.1198 0.02614 0.01688 0.0148 1.0000 0.9572
-0.750 -0.0816 0.02594 0.01666 0.0101 1.0000 0.9708
-0.500 -0.0372 0.02576 0.01645 0.0041 1.0000 0.9846
-0.250 0.0109 0.02563 0.01631 -0.0029 1.0000 0.9994
0.000 0.0000 0.02569 0.01637 0.0000 1.0000 1.0000
0.250 -0.0108 0.02563 0.01631 0.0029 0.9994 1.0000
0.500 0.0373 0.02576 0.01645 -0.0040 0.9846 1.0000
0.750 0.0818 0.02594 0.01665 -0.0101 0.9707 1.0000
1.000 0.1202 0.02613 0.01688 -0.0148 0.9569 1.0000
1.250 0.1563 0.02637 0.01716 -0.0189 0.9430 1.0000
1.500 0.1932 0.02665 0.01750 -0.0228 0.9290 1.0000
1.750 0.2199 0.02695 0.01786 -0.0248 0.9144 1.0000
2.000 0.2445 0.02731 0.01828 -0.0262 0.8994 1.0000
2.250 0.2700 0.02772 0.01875 -0.0274 0.8840 1.0000
2.500 0.3014 0.02817 0.01928 -0.0292 0.8680 1.0000
2.750 0.3485 0.02854 0.01980 -0.0330 0.8505 1.0000
3.000 0.3858 0.02886 0.02024 -0.0346 0.8313 1.0000
3.250 0.4055 0.02931 0.02075 -0.0334 0.8100 1.0000
3.500 0.4636 0.02886 0.02056 -0.0358 0.7846 1.0000
3.750 0.4815 0.02902 0.02079 -0.0329 0.7582 1.0000
4.000 0.5122 0.02853 0.02042 -0.0304 0.7295 1.0000
4.250 0.5404 0.02777 0.01977 -0.0269 0.6998 1.0000
4.500 0.5640 0.02694 0.01900 -0.0226 0.6683 1.0000
4.750 0.5834 0.02612 0.01823 -0.0180 0.6331 1.0000
5.000 0.6041 0.02495 0.01709 -0.0132 0.5917 1.0000
5.250 0.6213 0.02365 0.01573 -0.0078 0.5343 1.0000
5.500 0.6328 0.02265 0.01428 -0.0016 0.4377 1.0000
5.750 0.6411 0.02356 0.01417 0.0031 0.3374 1.0000
6.000 0.6555 0.02527 0.01532 0.0057 0.2802 1.0000
6.250 0.6752 0.02699 0.01668 0.0073 0.2450 1.0000
6.500 0.6981 0.02879 0.01834 0.0084 0.2210 1.0000
6.750 0.7209 0.03058 0.02009 0.0095 0.2023 1.0000
7.000 0.7444 0.03262 0.02220 0.0104 0.1889 1.0000
7.250 0.7668 0.03475 0.02434 0.0112 0.1774 1.0000
7.500 0.7874 0.03694 0.02674 0.0123 0.1682 1.0000
7.750 0.8055 0.03966 0.02972 0.0135 0.1617 1.0000
8.000 0.8201 0.04222 0.03265 0.0149 0.1552 1.0000
8.250 0.8409 0.04523 0.03565 0.0156 0.1502 1.0000
8.500 0.8476 0.04874 0.03966 0.0173 0.1481 1.0000
8.750 0.8484 0.05241 0.04386 0.0190 0.1460 1.0000
9.000 0.8444 0.05646 0.04834 0.0206 0.1446 1.0000
9.250 0.8361 0.06090 0.05311 0.0217 0.1448 1.0000
9.500 0.8228 0.06580 0.05826 0.0224 0.1462 1.0000
9.750 0.8102 0.07090 0.06350 0.0226 0.1479 1.0000
10.000 0.7851 0.07623 0.06897 0.0224 0.1510 1.0000
10.250 0.6436 0.10024 0.09276 0.0011 0.1904 1.0000
10.500 0.6833 0.10023 0.09286 0.0064 0.1800 1.0000
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Polar data table (+)
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