FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.55 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l100-il-1000000.txt Download as CSV file: xf-fx79l100-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.0237 0.11818 0.11630 0.0241 1.0000 0.0082
-16.000 -1.0338 0.11105 0.10909 0.0205 1.0000 0.0079
-15.750 -1.0523 0.10222 0.10017 0.0158 1.0000 0.0078
-15.500 -1.0928 0.08853 0.08631 0.0077 1.0000 0.0078
-15.250 -1.1298 0.07684 0.07446 0.0005 1.0000 0.0076
-15.000 -1.1580 0.06743 0.06488 -0.0055 1.0000 0.0076
-14.750 -1.1715 0.06107 0.05836 -0.0096 1.0000 0.0077
-14.250 -1.1900 0.05091 0.04792 -0.0156 1.0000 0.0077
-14.000 -1.2113 0.04466 0.04144 -0.0188 1.0000 0.0079
-13.750 -1.2136 0.04129 0.03795 -0.0202 1.0000 0.0078
-13.500 -1.2404 0.03539 0.03174 -0.0216 1.0000 0.0080
-13.250 -1.2440 0.03263 0.02880 -0.0213 1.0000 0.0080
-13.000 -1.2468 0.03031 0.02632 -0.0201 1.0000 0.0081
-12.750 -1.2464 0.02850 0.02440 -0.0180 1.0000 0.0085
-12.500 -1.2357 0.02753 0.02337 -0.0164 1.0000 0.0087
-12.250 -1.2208 0.02658 0.02235 -0.0154 1.0000 0.0089
-12.000 -1.2084 0.02523 0.02087 -0.0141 1.0000 0.0090
-11.750 -1.1913 0.02436 0.01991 -0.0131 1.0000 0.0093
-11.500 -1.1744 0.02337 0.01882 -0.0121 1.0000 0.0095
-11.250 -1.1598 0.02197 0.01728 -0.0108 1.0000 0.0096
-11.000 -1.1412 0.02106 0.01626 -0.0098 1.0000 0.0099
-10.750 -1.1220 0.02018 0.01529 -0.0089 1.0000 0.0101
-10.500 -1.1009 0.01950 0.01452 -0.0081 1.0000 0.0105
-10.250 -1.0794 0.01887 0.01380 -0.0074 1.0000 0.0106
-10.000 -1.0626 0.01756 0.01235 -0.0060 1.0000 0.0110
-9.750 -1.0444 0.01648 0.01120 -0.0049 1.0000 0.0118
-9.500 -1.0219 0.01592 0.01060 -0.0041 1.0000 0.0123
-9.250 -0.9988 0.01545 0.01009 -0.0035 1.0000 0.0130
-9.000 -0.9755 0.01498 0.00958 -0.0029 1.0000 0.0136
-8.750 -0.9514 0.01463 0.00918 -0.0023 1.0000 0.0142
-8.500 -0.9312 0.01375 0.00821 -0.0012 1.0000 0.0154
-8.250 -0.9084 0.01323 0.00768 -0.0004 1.0000 0.0165
-8.000 -0.8841 0.01290 0.00733 0.0002 1.0000 0.0176
-7.750 -0.8600 0.01254 0.00694 0.0008 1.0000 0.0185
-7.500 -0.8353 0.01227 0.00662 0.0014 1.0000 0.0190
-7.250 -0.8140 0.01157 0.00590 0.0025 1.0000 0.0214
-7.000 -0.7900 0.01124 0.00556 0.0032 1.0000 0.0227
-6.750 -0.7655 0.01097 0.00527 0.0038 1.0000 0.0242
-6.500 -0.7413 0.01069 0.00496 0.0045 1.0000 0.0255
-6.250 -0.7185 0.01025 0.00452 0.0055 1.0000 0.0286
-6.000 -0.6943 0.01002 0.00430 0.0062 1.0000 0.0312
-5.750 -0.6701 0.00979 0.00406 0.0069 1.0000 0.0330
-5.500 -0.6478 0.00940 0.00368 0.0080 1.0000 0.0380
-5.250 -0.6241 0.00919 0.00347 0.0089 1.0000 0.0412
-5.000 -0.5923 0.00883 0.00315 0.0079 0.9914 0.0480
-4.750 -0.5550 0.00858 0.00291 0.0058 0.9818 0.0550
-4.500 -0.5152 0.00827 0.00266 0.0031 0.9657 0.0674
-4.250 -0.4633 0.00789 0.00238 -0.0025 0.9487 0.0934
-4.000 -0.4089 0.00740 0.00207 -0.0088 0.9172 0.1456
-3.750 -0.3761 0.00702 0.00181 -0.0102 0.8747 0.2099
-3.500 -0.3538 0.00666 0.00160 -0.0091 0.8408 0.2795
-3.000 -0.3111 0.00598 0.00129 -0.0065 0.7925 0.4270
-2.750 -0.2873 0.00583 0.00121 -0.0056 0.7739 0.4697
-2.500 -0.2624 0.00576 0.00116 -0.0048 0.7573 0.4986
-2.250 -0.2368 0.00572 0.00111 -0.0042 0.7428 0.5193
-2.000 -0.2111 0.00569 0.00107 -0.0036 0.7296 0.5385
-1.750 -0.1850 0.00568 0.00104 -0.0031 0.7176 0.5531
-1.500 -0.1588 0.00565 0.00101 -0.0026 0.7062 0.5694
-1.250 -0.1323 0.00563 0.00099 -0.0022 0.6956 0.5830
-1.000 -0.1061 0.00562 0.00098 -0.0017 0.6856 0.5984
-0.750 -0.0795 0.00562 0.00097 -0.0013 0.6759 0.6120
-0.500 -0.0530 0.00560 0.00097 -0.0009 0.6667 0.6230
-0.250 -0.0268 0.00560 0.00097 -0.0004 0.6570 0.6359
0.000 0.0000 0.00559 0.00096 0.0000 0.6467 0.6466
0.250 0.0268 0.00560 0.00097 0.0004 0.6364 0.6567
0.500 0.0530 0.00560 0.00097 0.0009 0.6248 0.6665
0.750 0.0794 0.00562 0.00097 0.0013 0.6116 0.6759
1.000 0.1058 0.00563 0.00098 0.0017 0.5973 0.6859
1.250 0.1322 0.00563 0.00099 0.0022 0.5829 0.6956
1.500 0.1587 0.00565 0.00101 0.0026 0.5688 0.7061
1.750 0.1849 0.00568 0.00103 0.0031 0.5526 0.7175
2.000 0.2110 0.00569 0.00107 0.0036 0.5382 0.7298
2.250 0.2367 0.00572 0.00111 0.0042 0.5197 0.7428
2.500 0.2623 0.00576 0.00116 0.0048 0.4974 0.7573
2.750 0.2872 0.00584 0.00121 0.0056 0.4688 0.7738
3.000 0.3110 0.00598 0.00129 0.0065 0.4272 0.7925
3.250 0.3335 0.00621 0.00141 0.0076 0.3703 0.8145
3.500 0.3539 0.00664 0.00160 0.0091 0.2835 0.8412
3.750 0.3759 0.00703 0.00181 0.0102 0.2090 0.8749
4.000 0.4086 0.00742 0.00207 0.0088 0.1435 0.9170
4.250 0.4628 0.00788 0.00238 0.0026 0.0942 0.9485
4.500 0.5149 0.00827 0.00265 -0.0030 0.0676 0.9655
4.750 0.5550 0.00857 0.00290 -0.0058 0.0557 0.9818
5.000 0.5924 0.00884 0.00315 -0.0080 0.0482 0.9916
5.250 0.6240 0.00921 0.00349 -0.0089 0.0413 1.0000
5.500 0.6477 0.00940 0.00368 -0.0081 0.0379 1.0000
5.750 0.6700 0.00980 0.00406 -0.0070 0.0326 1.0000
6.000 0.6944 0.01000 0.00428 -0.0062 0.0313 1.0000
6.250 0.7186 0.01023 0.00451 -0.0055 0.0290 1.0000
6.500 0.7417 0.01064 0.00491 -0.0046 0.0259 1.0000
6.750 0.7655 0.01096 0.00527 -0.0039 0.0243 1.0000
7.000 0.7901 0.01121 0.00553 -0.0032 0.0226 1.0000
7.250 0.8142 0.01154 0.00585 -0.0026 0.0212 1.0000
7.500 0.8357 0.01220 0.00655 -0.0015 0.0190 1.0000
7.750 0.8606 0.01245 0.00684 -0.0009 0.0182 1.0000
8.000 0.8847 0.01280 0.00721 -0.0003 0.0170 1.0000
8.250 0.9086 0.01318 0.00761 0.0003 0.0160 1.0000
8.500 0.9277 0.01419 0.00868 0.0017 0.0145 1.0000
8.750 0.9513 0.01462 0.00916 0.0023 0.0141 1.0000
9.000 0.9746 0.01509 0.00970 0.0030 0.0135 1.0000
9.250 0.9983 0.01549 0.01013 0.0036 0.0128 1.0000
9.500 1.0219 0.01590 0.01057 0.0041 0.0121 1.0000
9.750 1.0438 0.01653 0.01125 0.0049 0.0117 1.0000
10.000 1.0619 0.01764 0.01244 0.0061 0.0110 1.0000
10.250 1.0786 0.01895 0.01389 0.0075 0.0106 1.0000
10.500 1.0995 0.01967 0.01471 0.0083 0.0105 1.0000
10.750 1.1186 0.02062 0.01576 0.0093 0.0103 1.0000
11.000 1.1389 0.02133 0.01656 0.0101 0.0100 1.0000
11.250 1.1578 0.02222 0.01755 0.0110 0.0097 1.0000
11.500 1.1742 0.02336 0.01882 0.0122 0.0095 1.0000
11.750 1.1911 0.02435 0.01990 0.0132 0.0093 1.0000
12.000 1.2058 0.02555 0.02123 0.0143 0.0091 1.0000
12.250 1.2200 0.02666 0.02245 0.0155 0.0090 1.0000
12.500 1.2373 0.02735 0.02316 0.0163 0.0087 1.0000
12.750 1.2424 0.02888 0.02483 0.0184 0.0086 1.0000
13.000 1.2481 0.03024 0.02628 0.0200 0.0084 1.0000
13.250 1.2465 0.03246 0.02865 0.0213 0.0083 1.0000
13.500 1.2438 0.03505 0.03137 0.0215 0.0081 1.0000
13.750 1.2096 0.04188 0.03856 0.0199 0.0077 1.0000
14.000 1.2083 0.04512 0.04192 0.0185 0.0078 1.0000
14.250 1.2094 0.04823 0.04513 0.0169 0.0079 1.0000
14.500 1.1817 0.05577 0.05292 0.0127 0.0078 1.0000
14.750 1.1729 0.06087 0.05814 0.0096 0.0078 1.0000
15.000 1.1555 0.06778 0.06520 0.0053 0.0079 1.0000
15.250 1.1325 0.07619 0.07378 -0.0001 0.0079 1.0000
15.500 1.1174 0.08367 0.08137 -0.0048 0.0079 1.0000
15.750 1.0838 0.09543 0.09329 -0.0119 0.0079 1.0000
16.000 1.0674 0.10383 0.10179 -0.0166 0.0081 1.0000
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Polar data table (+)
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