FX 69-PR-281 (fx69pr281-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 69-PR-281 (fx69pr281-il) Reynolds number: 100,000 Max Cl/Cd: 26.09 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69pr281-il-100000-n5.txt Download as CSV file: xf-fx69pr281-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 69-PR-281
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2364 0.09986 0.09303 -0.1253 0.8287 0.1314
-10.500 0.2537 0.09210 0.08507 -0.1324 0.8032 0.1389
-10.250 0.2859 0.09103 0.08390 -0.1348 0.7883 0.1401
-10.000 0.3055 0.08970 0.08252 -0.1357 0.7723 0.1419
-9.750 0.2939 0.08425 0.07692 -0.1393 0.7628 0.1480
-9.500 0.3140 0.08374 0.07639 -0.1390 0.7476 0.1492
-9.000 0.3367 0.08012 0.07263 -0.1405 0.7242 0.1548
-7.500 0.3206 0.06402 0.05620 -0.1430 0.6675 0.1786
-7.250 0.3423 0.06410 0.05623 -0.1419 0.6563 0.1797
-6.750 -0.0048 0.03632 0.02792 -0.1416 0.6562 0.2035
-6.500 0.0281 0.03658 0.02819 -0.1412 0.6480 0.2050
-6.250 0.0373 0.03640 0.02808 -0.1386 0.6381 0.2066
-6.000 0.0475 0.03580 0.02741 -0.1370 0.6294 0.2088
-5.750 0.0540 0.03447 0.02586 -0.1362 0.6222 0.2119
-5.500 0.0456 0.03281 0.02396 -0.1337 0.6136 0.2155
-5.250 0.0576 0.03196 0.02297 -0.1323 0.6050 0.2181
-5.000 0.0860 0.03185 0.02283 -0.1320 0.5974 0.2200
-4.750 0.1009 0.03167 0.02268 -0.1300 0.5889 0.2220
-4.500 0.1170 0.03128 0.02225 -0.1285 0.5805 0.2245
-4.250 0.1382 0.03062 0.02140 -0.1281 0.5732 0.2278
-4.000 0.1555 0.02977 0.02027 -0.1276 0.5661 0.2316
-3.750 0.1716 0.02946 0.01997 -0.1258 0.5578 0.2338
-3.500 0.1939 0.02934 0.01986 -0.1247 0.5502 0.2359
-3.250 0.2216 0.02916 0.01959 -0.1245 0.5436 0.2386
-3.000 0.2359 0.02897 0.01943 -0.1225 0.5356 0.2413
-2.750 0.2550 0.02864 0.01900 -0.1213 0.5281 0.2446
-2.500 0.2804 0.02817 0.01827 -0.1213 0.5213 0.2485
-2.250 0.3008 0.02794 0.01800 -0.1202 0.5142 0.2511
-2.000 0.3175 0.02789 0.01802 -0.1182 0.5062 0.2533
-1.750 0.3394 0.02779 0.01790 -0.1171 0.4991 0.2561
-1.500 0.3639 0.02768 0.01769 -0.1165 0.4926 0.2594
-1.250 0.3783 0.02758 0.01758 -0.1144 0.4850 0.2625
-1.000 0.3985 0.02741 0.01728 -0.1133 0.4781 0.2662
-0.750 0.4256 0.02722 0.01691 -0.1132 0.4720 0.2697
-0.500 0.4423 0.02726 0.01702 -0.1113 0.4652 0.2722
-0.250 0.4578 0.02733 0.01715 -0.1093 0.4578 0.2750
0.000 0.4788 0.02734 0.01711 -0.1081 0.4513 0.2784
0.250 0.5025 0.02735 0.01701 -0.1075 0.4454 0.2823
0.500 0.5176 0.02747 0.01713 -0.1056 0.4383 0.2860
0.750 0.5376 0.02754 0.01708 -0.1045 0.4319 0.2897
1.000 0.5614 0.02756 0.01708 -0.1038 0.4265 0.2930
1.250 0.5779 0.02783 0.01740 -0.1021 0.4204 0.2964
1.500 0.5946 0.02809 0.01769 -0.1005 0.4140 0.3001
1.750 0.6156 0.02826 0.01778 -0.0995 0.4085 0.3045
2.000 0.6414 0.02837 0.01773 -0.0993 0.4038 0.3094
2.250 0.6553 0.02876 0.01816 -0.0975 0.3979 0.3134
2.500 0.6718 0.02908 0.01855 -0.0960 0.3924 0.3172
2.750 0.6923 0.02934 0.01878 -0.0950 0.3877 0.3216
3.000 0.7172 0.02955 0.01889 -0.0946 0.3834 0.3269
3.250 0.7300 0.03009 0.01949 -0.0928 0.3784 0.3318
3.500 0.7464 0.03055 0.01991 -0.0916 0.3736 0.3371
3.750 0.7648 0.03089 0.02030 -0.0905 0.3694 0.3420
4.000 0.7897 0.03112 0.02048 -0.0901 0.3657 0.3480
4.250 0.8054 0.03169 0.02107 -0.0888 0.3616 0.3540
4.500 0.8178 0.03238 0.02179 -0.0873 0.3573 0.3602
4.750 0.8336 0.03295 0.02238 -0.0861 0.3534 0.3665
5.000 0.8524 0.03340 0.02286 -0.0852 0.3498 0.3733
5.250 0.8784 0.03367 0.02306 -0.0850 0.3467 0.3820
5.500 0.8932 0.03441 0.02380 -0.0839 0.3433 0.3900
5.750 0.8996 0.03543 0.02496 -0.0820 0.3394 0.3966
6.000 0.9105 0.03631 0.02594 -0.0806 0.3357 0.4040
6.250 0.9267 0.03702 0.02667 -0.0797 0.3324 0.4136
6.500 0.9484 0.03753 0.02711 -0.0793 0.3295 0.4244
6.750 0.9784 0.03770 0.02725 -0.0795 0.3269 0.4364
7.000 0.9733 0.03944 0.02918 -0.0771 0.3234 0.4444
7.250 0.9737 0.04106 0.03090 -0.0754 0.3198 0.4536
7.500 0.9815 0.04231 0.03225 -0.0742 0.3164 0.4634
7.750 0.9969 0.04319 0.03317 -0.0735 0.3135 0.4762
8.000 1.0198 0.04370 0.03361 -0.0733 0.3110 0.4909
8.250 1.0424 0.04424 0.03417 -0.0730 0.3087 0.5056
8.500 1.0195 0.04757 0.03776 -0.0706 0.3050 0.5128
9.000 1.0128 0.05225 0.04271 -0.0684 0.2982 0.5352
9.250 1.0315 0.05305 0.04349 -0.0681 0.2957 0.5537
9.500 1.0596 0.05308 0.04352 -0.0680 0.2937 0.5749
9.750 1.0307 0.05782 0.04849 -0.0667 0.2899 0.5828
10.000 0.9318 0.07025 0.06138 -0.0664 0.2818 0.5689
10.250 0.9545 0.07065 0.06179 -0.0662 0.2798 0.5917
10.500 0.9880 0.06983 0.06097 -0.0658 0.2785 0.6218
10.750 1.0247 0.06865 0.05979 -0.0653 0.2774 0.6573
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