FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-100 AIRFOIL (fx60100-il) Reynolds number: 50,000 Max Cl/Cd: 40.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100-il-50000.txt Download as CSV file: xf-fx60100-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3758 0.12290 0.11589 -0.0269 1.0000 0.2065
-9.500 -0.3494 0.11654 0.10951 -0.0253 1.0000 0.2141
-9.250 -0.3692 0.11706 0.11018 -0.0270 1.0000 0.2207
-9.000 -0.3426 0.11095 0.10405 -0.0253 1.0000 0.2285
-8.750 -0.3605 0.11083 0.10410 -0.0264 1.0000 0.2352
-8.500 -0.3375 0.10554 0.09878 -0.0248 1.0000 0.2438
-8.250 -0.3489 0.10430 0.09769 -0.0250 1.0000 0.2505
-8.000 -0.3349 0.10050 0.09388 -0.0238 1.0000 0.2593
-7.750 -0.3403 0.09838 0.09189 -0.0232 1.0000 0.2664
-7.500 -0.3445 0.09675 0.09037 -0.0219 1.0000 0.2767
-7.250 -0.3349 0.09318 0.08686 -0.0206 1.0000 0.2837
-7.000 -0.3677 0.09424 0.08815 -0.0181 1.0000 0.2921
-6.750 -0.3425 0.08922 0.08312 -0.0168 1.0000 0.3023
-6.500 -0.3637 0.08853 0.08262 -0.0138 1.0000 0.3084
-6.250 -0.3576 0.08561 0.07975 -0.0116 1.0000 0.3165
-5.750 -0.4087 0.05862 0.05241 -0.0572 1.0000 0.1231
-5.500 -0.3880 0.05140 0.04473 -0.0629 1.0000 0.1083
-5.250 -0.3677 0.04666 0.03981 -0.0651 1.0000 0.1028
-5.000 -0.3284 0.03999 0.03183 -0.0728 1.0000 0.0953
-4.750 -0.2983 0.03655 0.02778 -0.0750 1.0000 0.0958
-4.500 -0.2713 0.03346 0.02445 -0.0760 1.0000 0.0982
-4.250 -0.2429 0.03105 0.02173 -0.0766 1.0000 0.1006
-4.000 -0.2142 0.02898 0.01932 -0.0767 1.0000 0.1039
-3.750 -0.1860 0.02726 0.01724 -0.0763 1.0000 0.1099
-3.500 -0.1608 0.02572 0.01582 -0.0759 1.0000 0.1258
-3.250 -0.1318 0.02399 0.01426 -0.0761 1.0000 0.1632
-3.000 -0.1110 0.02348 0.01591 -0.0729 1.0000 0.4881
-2.750 -0.1049 0.02460 0.01708 -0.0669 1.0000 0.5521
-2.500 -0.0969 0.02512 0.01761 -0.0617 1.0000 0.5986
-2.250 -0.0865 0.02521 0.01764 -0.0575 1.0000 0.6356
-2.000 -0.0730 0.02511 0.01744 -0.0545 1.0000 0.6718
-1.750 -0.0586 0.02488 0.01711 -0.0519 1.0000 0.7026
-1.500 -0.0420 0.02464 0.01672 -0.0501 1.0000 0.7318
-1.250 -0.0244 0.02440 0.01634 -0.0488 1.0000 0.7600
-1.000 -0.0063 0.02419 0.01601 -0.0477 1.0000 0.7876
-0.750 0.0110 0.02398 0.01572 -0.0466 1.0000 0.8159
-0.500 0.0262 0.02377 0.01546 -0.0451 1.0000 0.8465
-0.250 0.0409 0.02354 0.01522 -0.0438 1.0000 0.8825
0.000 0.0596 0.02324 0.01500 -0.0439 1.0000 0.9452
0.250 0.0919 0.02360 0.01518 -0.0486 1.0000 1.0000
0.500 0.1315 0.02443 0.01575 -0.0543 1.0000 1.0000
0.750 0.1666 0.02534 0.01642 -0.0589 0.9999 1.0000
1.000 0.2322 0.02693 0.01773 -0.0686 0.9838 1.0000
1.250 0.2864 0.02822 0.01880 -0.0757 0.9673 1.0000
1.500 0.3351 0.02939 0.01982 -0.0813 0.9510 1.0000
1.750 0.3809 0.03049 0.02081 -0.0862 0.9346 1.0000
2.000 0.4275 0.03151 0.02174 -0.0907 0.9172 1.0000
2.250 0.4756 0.03242 0.02261 -0.0951 0.8999 1.0000
2.500 0.5165 0.03324 0.02343 -0.0982 0.8823 1.0000
2.750 0.5517 0.03406 0.02426 -0.1003 0.8643 1.0000
3.000 0.5902 0.03478 0.02502 -0.1026 0.8468 1.0000
3.250 0.6348 0.03525 0.02555 -0.1053 0.8289 1.0000
3.500 0.6781 0.03556 0.02599 -0.1074 0.8106 1.0000
3.750 0.7094 0.03609 0.02662 -0.1080 0.7905 1.0000
4.000 0.7528 0.03614 0.02680 -0.1097 0.7725 1.0000
4.250 0.8099 0.03521 0.02613 -0.1119 0.7549 1.0000
4.500 0.8409 0.03513 0.02618 -0.1112 0.7320 1.0000
4.750 0.8949 0.03342 0.02474 -0.1116 0.7127 1.0000
5.000 0.9305 0.03260 0.02409 -0.1103 0.6884 1.0000
5.250 0.9744 0.03095 0.02262 -0.1090 0.6636 1.0000
5.500 1.0134 0.02956 0.02139 -0.1073 0.6354 1.0000
5.750 1.0465 0.02866 0.02057 -0.1052 0.6032 1.0000
6.000 1.0803 0.02782 0.01971 -0.1031 0.5675 1.0000
6.250 1.1057 0.02753 0.01935 -0.1004 0.5237 1.0000
6.500 1.1247 0.02774 0.01943 -0.0973 0.4737 1.0000
6.750 1.1445 0.02823 0.01961 -0.0945 0.4217 1.0000
7.000 1.1614 0.02942 0.02058 -0.0919 0.3699 1.0000
7.250 1.1795 0.03088 0.02169 -0.0897 0.3233 1.0000
7.500 1.1967 0.03256 0.02316 -0.0877 0.2835 1.0000
7.750 1.2169 0.03444 0.02485 -0.0862 0.2514 1.0000
8.000 1.2364 0.03646 0.02683 -0.0849 0.2256 1.0000
8.250 1.2610 0.03883 0.02906 -0.0842 0.2063 1.0000
8.500 1.2796 0.04113 0.03157 -0.0829 0.1901 1.0000
8.750 1.3014 0.04373 0.03426 -0.0820 0.1775 1.0000
9.000 1.3193 0.04678 0.03772 -0.0807 0.1690 1.0000
9.250 1.3373 0.05037 0.04159 -0.0796 0.1630 1.0000
9.500 1.3440 0.05411 0.04599 -0.0775 0.1584 1.0000
9.750 1.3656 0.05727 0.04910 -0.0770 0.1510 1.0000
10.000 1.3582 0.06140 0.05394 -0.0740 0.1481 1.0000
10.250 1.3504 0.06592 0.05896 -0.0715 0.1461 1.0000
10.500 1.3371 0.07085 0.06432 -0.0691 0.1456 1.0000
10.750 1.3152 0.07606 0.06988 -0.0668 0.1460 1.0000
11.000 1.2842 0.08127 0.07533 -0.0645 0.1471 1.0000
11.250 1.2506 0.08722 0.08144 -0.0638 0.1485 1.0000
11.500 1.2192 0.09422 0.08855 -0.0650 0.1500 1.0000
11.750 1.1956 0.10187 0.09622 -0.0673 0.1512 1.0000
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