USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 100,000 Max Cl/Cd: 52.39 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa29-il-100000-n5.txt Download as CSV file: xf-usa29-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 29 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1890 0.10105 0.09638 -0.0634 0.9753 0.0588
-10.250 -0.1759 0.09736 0.09266 -0.0659 0.9726 0.0603
-10.000 -0.1690 0.09387 0.08916 -0.0676 0.9671 0.0623
-9.750 -0.1643 0.08928 0.08455 -0.0705 0.9631 0.0633
-9.500 -0.2994 0.09181 0.08698 -0.0656 0.9771 0.0577
-9.250 -0.2734 0.09067 0.08580 -0.0669 0.9735 0.0599
-9.000 -0.2689 0.08624 0.08135 -0.0706 0.9663 0.0602
-8.750 -0.2642 0.08082 0.07592 -0.0762 0.9603 0.0605
-8.500 -0.2676 0.07602 0.07113 -0.0803 0.9501 0.0608
-8.250 -0.2684 0.07141 0.06649 -0.0843 0.9410 0.0618
-8.000 -0.2692 0.06511 0.06013 -0.0899 0.9313 0.0631
-7.750 -0.2857 0.05641 0.05130 -0.0947 0.9184 0.0634
-7.500 -0.3240 0.04259 0.03670 -0.0990 0.9036 0.0634
-7.250 -0.3183 0.03775 0.03123 -0.0992 0.8962 0.0641
-7.000 -0.3092 0.03492 0.02791 -0.0976 0.8872 0.0652
-6.750 -0.2913 0.03247 0.02492 -0.0970 0.8806 0.0670
-6.500 -0.2742 0.03063 0.02256 -0.0956 0.8723 0.0682
-6.250 -0.2437 0.02889 0.02063 -0.0966 0.8683 0.0693
-6.000 -0.2270 0.02786 0.01946 -0.0947 0.8582 0.0702
-5.750 -0.1948 0.02662 0.01803 -0.0957 0.8537 0.0716
-5.500 -0.1756 0.02577 0.01703 -0.0941 0.8438 0.0728
-5.250 -0.1429 0.02470 0.01576 -0.0950 0.8387 0.0746
-5.000 -0.1217 0.02402 0.01490 -0.0936 0.8287 0.0769
-4.750 -0.0883 0.02311 0.01374 -0.0945 0.8232 0.0795
-4.500 -0.0670 0.02252 0.01313 -0.0932 0.8127 0.0814
-4.250 -0.0334 0.02177 0.01229 -0.0942 0.8069 0.0839
-4.000 -0.0124 0.02132 0.01175 -0.0927 0.7957 0.0865
-3.750 0.0159 0.02077 0.01106 -0.0926 0.7874 0.0900
-3.500 0.0422 0.02026 0.01047 -0.0921 0.7779 0.0941
-3.250 0.0667 0.01986 0.01002 -0.0914 0.7678 0.1012
-3.000 0.0971 0.01931 0.00940 -0.0917 0.7600 0.1116
-2.750 0.1199 0.01891 0.00898 -0.0907 0.7488 0.1250
-2.500 0.1486 0.01846 0.00859 -0.0908 0.7400 0.1463
-2.250 0.1769 0.01816 0.00833 -0.0908 0.7306 0.1761
-2.000 0.2030 0.01800 0.00818 -0.0904 0.7207 0.2066
-1.750 0.2330 0.01786 0.00806 -0.0907 0.7128 0.2390
-1.500 0.2562 0.01791 0.00810 -0.0897 0.7026 0.2619
-1.250 0.2835 0.01795 0.00808 -0.0894 0.6944 0.2797
-1.000 0.3090 0.01805 0.00809 -0.0888 0.6855 0.2961
-0.750 0.3340 0.01825 0.00819 -0.0880 0.6774 0.3157
-0.500 0.3593 0.01842 0.00824 -0.0873 0.6695 0.3330
-0.250 0.3845 0.01855 0.00826 -0.0867 0.6617 0.3465
0.000 0.4107 0.01861 0.00822 -0.0863 0.6541 0.3581
0.250 0.4372 0.01867 0.00816 -0.0859 0.6469 0.3688
0.500 0.4628 0.01874 0.00813 -0.0855 0.6395 0.3800
0.750 0.4912 0.01873 0.00806 -0.0856 0.6331 0.3912
1.000 0.5180 0.01874 0.00806 -0.0855 0.6256 0.4007
1.250 0.5510 0.01873 0.00796 -0.0865 0.6198 0.4106
1.500 0.5793 0.01879 0.00803 -0.0868 0.6123 0.4194
1.750 0.6132 0.01879 0.00800 -0.0881 0.6060 0.4280
2.000 0.6433 0.01887 0.00805 -0.0887 0.5997 0.4357
2.250 0.6719 0.01893 0.00814 -0.0890 0.5930 0.4427
2.500 0.7029 0.01898 0.00815 -0.0897 0.5877 0.4510
2.750 0.7250 0.01909 0.00835 -0.0888 0.5808 0.4583
3.000 0.7501 0.01918 0.00847 -0.0883 0.5749 0.4675
3.250 0.7758 0.01923 0.00856 -0.0880 0.5698 0.4778
3.500 0.7951 0.01936 0.00882 -0.0865 0.5633 0.4898
3.750 0.8185 0.01939 0.00897 -0.0857 0.5579 0.5101
4.250 0.9758 0.01944 0.01009 -0.1078 0.5433 0.9921
4.500 1.0146 0.01972 0.01034 -0.1104 0.5381 1.0000
4.750 1.0319 0.02008 0.01079 -0.1085 0.5319 1.0000
5.000 1.0534 0.02036 0.01107 -0.1074 0.5267 1.0000
5.250 1.0752 0.02064 0.01135 -0.1063 0.5219 1.0000
5.500 1.0915 0.02103 0.01183 -0.1042 0.5159 1.0000
5.750 1.1126 0.02133 0.01216 -0.1030 0.5108 1.0000
6.000 1.1337 0.02164 0.01250 -0.1018 0.5061 1.0000
6.250 1.1485 0.02207 0.01305 -0.0995 0.5001 1.0000
6.500 1.1690 0.02238 0.01341 -0.0982 0.4952 1.0000
6.750 1.1895 0.02272 0.01381 -0.0969 0.4905 1.0000
7.000 1.2027 0.02320 0.01443 -0.0944 0.4846 1.0000
7.250 1.2225 0.02352 0.01481 -0.0930 0.4795 1.0000
7.500 1.2346 0.02384 0.01521 -0.0901 0.4712 1.0000
7.750 1.2464 0.02388 0.01523 -0.0869 0.4594 1.0000
8.000 1.2524 0.02406 0.01545 -0.0828 0.4466 1.0000
8.250 1.2532 0.02440 0.01585 -0.0778 0.4335 1.0000
8.500 1.2529 0.02473 0.01623 -0.0727 0.4215 1.0000
8.750 1.2551 0.02511 0.01664 -0.0683 0.4096 1.0000
9.000 1.2567 0.02557 0.01713 -0.0639 0.3964 1.0000
9.250 1.2562 0.02620 0.01780 -0.0594 0.3812 1.0000
9.500 1.2540 0.02702 0.01865 -0.0550 0.3634 1.0000
9.750 1.2506 0.02804 0.01967 -0.0507 0.3420 1.0000
10.000 1.2441 0.02938 0.02093 -0.0465 0.3135 1.0000
10.250 1.2319 0.03126 0.02264 -0.0420 0.2750 1.0000
10.500 1.2151 0.03379 0.02491 -0.0378 0.2314 1.0000
10.750 1.1942 0.03702 0.02786 -0.0339 0.1867 1.0000
11.000 1.1636 0.04150 0.03195 -0.0304 0.1325 1.0000
11.250 1.1381 0.04604 0.03622 -0.0280 0.0853 1.0000
11.500 1.1147 0.05077 0.04072 -0.0262 0.0570 1.0000
11.750 1.1036 0.05451 0.04445 -0.0251 0.0489 1.0000
12.000 1.0975 0.05784 0.04786 -0.0243 0.0450 1.0000
12.250 1.0895 0.06151 0.05160 -0.0236 0.0415 1.0000
12.500 1.0826 0.06516 0.05533 -0.0231 0.0392 1.0000
12.750 1.0784 0.06857 0.05888 -0.0227 0.0370 1.0000
13.000 1.0746 0.07201 0.06246 -0.0225 0.0358 1.0000
13.250 1.0688 0.07578 0.06635 -0.0223 0.0344 1.0000
13.500 1.0640 0.07948 0.07018 -0.0223 0.0336 1.0000
13.750 1.0583 0.08334 0.07415 -0.0224 0.0327 1.0000
14.000 1.0518 0.08735 0.07825 -0.0225 0.0319 1.0000
14.250 1.0483 0.09094 0.08193 -0.0226 0.0310 1.0000
14.500 1.0490 0.09395 0.08506 -0.0225 0.0298 1.0000
14.750 1.0508 0.09674 0.08798 -0.0224 0.0289 1.0000
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