FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 200,000 Max Cl/Cd: 52.57 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l120-il-200000.txt Download as CSV file: xf-fx79l120-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.9384 0.06707 0.06244 -0.0320 1.0000 0.0378
-12.500 -0.9579 0.06209 0.05728 -0.0335 1.0000 0.0376
-12.250 -0.9824 0.05770 0.05265 -0.0340 1.0000 0.0377
-12.000 -0.9979 0.05406 0.04879 -0.0332 1.0000 0.0377
-11.750 -1.0146 0.05110 0.04558 -0.0307 1.0000 0.0378
-11.500 -1.0291 0.04766 0.04186 -0.0279 1.0000 0.0381
-11.250 -1.0282 0.04408 0.03816 -0.0266 1.0000 0.0390
-11.000 -1.0177 0.04240 0.03644 -0.0255 1.0000 0.0401
-10.750 -1.0069 0.04076 0.03471 -0.0242 1.0000 0.0411
-10.500 -0.9995 0.03852 0.03223 -0.0224 1.0000 0.0423
-10.250 -0.9907 0.03610 0.02951 -0.0206 1.0000 0.0431
-10.000 -0.9794 0.03398 0.02706 -0.0188 1.0000 0.0444
-9.750 -0.9661 0.03266 0.02539 -0.0170 1.0000 0.0458
-9.500 -0.9488 0.02985 0.02249 -0.0162 1.0000 0.0477
-9.250 -0.9294 0.02865 0.02126 -0.0153 1.0000 0.0497
-9.000 -0.9098 0.02741 0.01989 -0.0143 1.0000 0.0518
-8.750 -0.8897 0.02626 0.01856 -0.0131 1.0000 0.0541
-8.500 -0.8693 0.02462 0.01677 -0.0122 1.0000 0.0568
-8.250 -0.8484 0.02349 0.01569 -0.0113 1.0000 0.0598
-8.000 -0.8271 0.02257 0.01471 -0.0103 1.0000 0.0629
-7.750 -0.8056 0.02193 0.01391 -0.0092 1.0000 0.0663
-7.500 -0.7859 0.02043 0.01251 -0.0082 1.0000 0.0705
-7.250 -0.7651 0.01967 0.01173 -0.0070 1.0000 0.0749
-7.000 -0.7446 0.01885 0.01085 -0.0058 1.0000 0.0797
-6.750 -0.7259 0.01794 0.01004 -0.0044 1.0000 0.0855
-6.500 -0.7050 0.01736 0.00937 -0.0032 1.0000 0.0916
-6.250 -0.6878 0.01641 0.00856 -0.0015 1.0000 0.0994
-6.000 -0.6693 0.01568 0.00787 0.0001 1.0000 0.1094
-5.750 -0.6509 0.01500 0.00725 0.0016 1.0000 0.1221
-5.500 -0.6342 0.01422 0.00663 0.0034 1.0000 0.1417
-5.250 -0.6194 0.01336 0.00602 0.0054 1.0000 0.1778
-5.000 -0.6101 0.01233 0.00549 0.0081 1.0000 0.2504
-4.750 -0.6008 0.01141 0.00519 0.0105 0.9968 0.3595
-4.500 -0.5593 0.01092 0.00510 0.0072 0.9821 0.4651
-4.250 -0.5161 0.01082 0.00508 0.0041 0.9690 0.5141
-4.000 -0.4724 0.01081 0.00508 0.0010 0.9555 0.5471
-3.750 -0.4295 0.01083 0.00502 -0.0019 0.9403 0.5725
-3.500 -0.3882 0.01084 0.00502 -0.0044 0.9243 0.5918
-3.250 -0.3508 0.01088 0.00501 -0.0060 0.9067 0.6089
-3.000 -0.3182 0.01095 0.00501 -0.0066 0.8888 0.6246
-2.750 -0.2894 0.01104 0.00504 -0.0064 0.8719 0.6396
-2.500 -0.2625 0.01114 0.00506 -0.0058 0.8565 0.6540
-2.250 -0.2358 0.01121 0.00512 -0.0051 0.8425 0.6663
-2.000 -0.2094 0.01127 0.00514 -0.0044 0.8301 0.6778
-1.750 -0.1837 0.01130 0.00510 -0.0037 0.8181 0.6889
-1.500 -0.1578 0.01131 0.00509 -0.0030 0.8063 0.6985
-1.250 -0.1315 0.01131 0.00505 -0.0025 0.7961 0.7070
-1.000 -0.1053 0.01132 0.00501 -0.0019 0.7861 0.7164
-0.750 -0.0791 0.01130 0.00499 -0.0014 0.7762 0.7243
-0.500 -0.0525 0.01132 0.00494 -0.0009 0.7680 0.7333
-0.250 -0.0264 0.01129 0.00495 -0.0005 0.7581 0.7410
0.000 0.0000 0.01131 0.00492 0.0000 0.7500 0.7503
0.250 0.0264 0.01129 0.00494 0.0005 0.7408 0.7581
0.500 0.0526 0.01132 0.00494 0.0010 0.7333 0.7679
0.750 0.0791 0.01130 0.00499 0.0014 0.7243 0.7762
1.000 0.1054 0.01132 0.00501 0.0019 0.7164 0.7862
1.250 0.1315 0.01131 0.00505 0.0025 0.7071 0.7961
1.500 0.1578 0.01131 0.00509 0.0031 0.6984 0.8063
1.750 0.1838 0.01130 0.00510 0.0037 0.6889 0.8181
2.000 0.2094 0.01127 0.00514 0.0044 0.6778 0.8301
2.250 0.2359 0.01121 0.00512 0.0051 0.6663 0.8424
2.500 0.2626 0.01114 0.00506 0.0058 0.6539 0.8564
2.750 0.2894 0.01104 0.00503 0.0064 0.6394 0.8720
3.000 0.3182 0.01095 0.00502 0.0066 0.6246 0.8890
3.250 0.3509 0.01088 0.00501 0.0060 0.6088 0.9069
3.500 0.3882 0.01084 0.00502 0.0044 0.5917 0.9244
3.750 0.4296 0.01083 0.00502 0.0019 0.5726 0.9403
4.000 0.4725 0.01081 0.00507 -0.0010 0.5471 0.9555
4.250 0.5162 0.01082 0.00509 -0.0041 0.5144 0.9690
4.500 0.5595 0.01092 0.00510 -0.0072 0.4649 0.9822
4.750 0.6009 0.01143 0.00519 -0.0105 0.3578 0.9971
5.000 0.6099 0.01235 0.00549 -0.0080 0.2490 1.0000
5.250 0.6195 0.01336 0.00602 -0.0054 0.1776 1.0000
5.500 0.6343 0.01421 0.00662 -0.0034 0.1419 1.0000
5.750 0.6510 0.01499 0.00725 -0.0016 0.1223 1.0000
6.000 0.6693 0.01569 0.00788 0.0000 0.1092 1.0000
6.250 0.6878 0.01642 0.00857 0.0015 0.0995 1.0000
6.500 0.7049 0.01738 0.00939 0.0032 0.0915 1.0000
6.750 0.7260 0.01794 0.01004 0.0044 0.0854 1.0000
7.000 0.7444 0.01890 0.01089 0.0058 0.0795 1.0000
7.250 0.7652 0.01967 0.01174 0.0070 0.0748 1.0000
7.500 0.7860 0.02041 0.01248 0.0082 0.0703 1.0000
7.750 0.8056 0.02186 0.01385 0.0093 0.0661 1.0000
8.000 0.8272 0.02257 0.01470 0.0103 0.0629 1.0000
8.250 0.8485 0.02351 0.01571 0.0113 0.0598 1.0000
8.500 0.8694 0.02463 0.01678 0.0122 0.0568 1.0000
8.750 0.8898 0.02629 0.01859 0.0131 0.0542 1.0000
9.000 0.9098 0.02741 0.01990 0.0143 0.0517 1.0000
9.250 0.9296 0.02871 0.02133 0.0153 0.0498 1.0000
9.500 0.9489 0.02994 0.02260 0.0162 0.0478 1.0000
9.750 0.9661 0.03269 0.02542 0.0170 0.0457 1.0000
10.000 0.9793 0.03398 0.02708 0.0188 0.0443 1.0000
10.250 0.9909 0.03616 0.02957 0.0206 0.0432 1.0000
10.500 1.0000 0.03845 0.03215 0.0224 0.0422 1.0000
10.750 1.0068 0.04082 0.03478 0.0242 0.0412 1.0000
11.000 1.0208 0.04205 0.03603 0.0252 0.0398 1.0000
11.250 1.0308 0.04383 0.03784 0.0264 0.0388 1.0000
11.500 1.0291 0.04781 0.04201 0.0279 0.0380 1.0000
11.750 1.0145 0.05098 0.04547 0.0308 0.0377 1.0000
12.000 0.9977 0.05394 0.04868 0.0332 0.0376 1.0000
12.250 0.9772 0.05765 0.05265 0.0340 0.0375 1.0000
12.500 0.9610 0.06200 0.05717 0.0335 0.0377 1.0000
12.750 0.9365 0.06715 0.06254 0.0316 0.0377 1.0000
13.000 0.6565 0.13672 0.13285 -0.0141 0.0731 1.0000
13.250 0.5426 0.12584 0.12233 0.0029 0.0785 1.0000
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