USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: USA 25 AIRFOIL (usa25-il) Reynolds number: 100,000 Max Cl/Cd: 54.57 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa25-il-100000-n5.txt Download as CSV file: xf-usa25-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 25 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3424 0.10283 0.09825 -0.0252 1.0000 0.0619
-7.750 -0.3623 0.10229 0.09782 -0.0242 1.0000 0.0622
-7.500 -0.3732 0.10079 0.09639 -0.0249 1.0000 0.0625
-7.250 -0.3788 0.09878 0.09441 -0.0254 1.0000 0.0626
-7.000 -0.3810 0.09640 0.09204 -0.0257 1.0000 0.0627
-6.750 -0.3691 0.09040 0.08612 -0.0230 0.9984 0.0636
-6.500 -0.3478 0.08609 0.08178 -0.0238 0.9946 0.0653
-6.250 -0.3240 0.08240 0.07805 -0.0277 0.9884 0.0693
-6.000 -0.2899 0.07903 0.07448 -0.0397 0.9781 0.0745
-5.750 -0.2592 0.07486 0.07013 -0.0467 0.9691 0.0749
-5.250 -0.2045 0.06627 0.06126 -0.0548 0.9524 0.0750
-4.750 -0.1651 0.05310 0.04776 -0.0592 0.9372 0.0518
-4.500 -0.1417 0.04991 0.04444 -0.0605 0.9288 0.0511
-4.250 -0.1149 0.04650 0.04085 -0.0623 0.9206 0.0505
-4.000 -0.0910 0.04290 0.03700 -0.0633 0.9103 0.0511
-3.750 -0.0593 0.03873 0.03248 -0.0654 0.9036 0.0516
-3.500 -0.0375 0.03584 0.02936 -0.0651 0.8920 0.0512
-3.250 -0.0127 0.03261 0.02581 -0.0650 0.8811 0.0509
-3.000 0.0155 0.02889 0.02164 -0.0653 0.8715 0.0506
-2.750 0.0453 0.02528 0.01743 -0.0656 0.8610 0.0509
-2.500 0.0754 0.02275 0.01435 -0.0658 0.8479 0.0515
-2.250 0.1095 0.02140 0.01273 -0.0667 0.8334 0.0537
-2.000 0.1473 0.02046 0.01162 -0.0684 0.8171 0.0560
-1.750 0.1851 0.01923 0.01012 -0.0699 0.7972 0.0574
-1.500 0.2233 0.01821 0.00884 -0.0714 0.7714 0.0593
-1.250 0.2611 0.01740 0.00775 -0.0728 0.7369 0.0620
-1.000 0.2967 0.01693 0.00709 -0.0739 0.6927 0.0660
-0.750 0.3293 0.01660 0.00645 -0.0744 0.6486 0.0735
-0.500 0.3585 0.01647 0.00611 -0.0743 0.6138 0.0863
-0.250 0.3864 0.01653 0.00600 -0.0741 0.5885 0.1057
0.000 0.4135 0.01672 0.00605 -0.0738 0.5698 0.1238
0.250 0.4403 0.01692 0.00611 -0.0736 0.5550 0.1400
0.500 0.4675 0.01699 0.00601 -0.0733 0.5427 0.1495
0.750 0.4944 0.01709 0.00601 -0.0731 0.5326 0.1597
1.000 0.5212 0.01720 0.00604 -0.0728 0.5242 0.1712
1.250 0.5479 0.01730 0.00609 -0.0726 0.5171 0.1846
1.500 0.5741 0.01738 0.00612 -0.0723 0.5104 0.1982
1.750 0.6002 0.01747 0.00612 -0.0719 0.5045 0.2102
2.000 0.6252 0.01753 0.00618 -0.0714 0.4984 0.2243
2.250 0.6506 0.01762 0.00625 -0.0709 0.4934 0.2420
2.500 0.6761 0.01771 0.00633 -0.0705 0.4888 0.2653
2.750 0.7005 0.01771 0.00646 -0.0699 0.4838 0.3041
3.000 0.8035 0.01687 0.00692 -0.0857 0.4764 1.0000
3.250 0.8264 0.01714 0.00715 -0.0847 0.4722 1.0000
3.500 0.8490 0.01741 0.00739 -0.0837 0.4676 1.0000
3.750 0.8720 0.01770 0.00762 -0.0828 0.4626 1.0000
4.000 0.8943 0.01800 0.00788 -0.0817 0.4572 1.0000
4.250 0.9152 0.01827 0.00816 -0.0804 0.4504 1.0000
4.500 0.9376 0.01858 0.00836 -0.0793 0.4438 1.0000
4.750 0.9570 0.01883 0.00869 -0.0777 0.4363 1.0000
5.000 0.9790 0.01913 0.00897 -0.0766 0.4303 1.0000
5.250 1.0007 0.01945 0.00933 -0.0754 0.4253 1.0000
5.500 1.0217 0.01976 0.00973 -0.0741 0.4199 1.0000
5.750 1.0438 0.02008 0.01009 -0.0731 0.4148 1.0000
6.000 1.0650 0.02041 0.01049 -0.0719 0.4095 1.0000
6.250 1.0852 0.02074 0.01094 -0.0705 0.4037 1.0000
6.500 1.1072 0.02107 0.01132 -0.0694 0.3986 1.0000
6.750 1.1276 0.02142 0.01182 -0.0681 0.3931 1.0000
7.000 1.1472 0.02175 0.01230 -0.0666 0.3867 1.0000
7.250 1.1647 0.02194 0.01256 -0.0646 0.3771 1.0000
7.500 1.1791 0.02198 0.01266 -0.0620 0.3638 1.0000
7.750 1.1924 0.02204 0.01281 -0.0592 0.3492 1.0000
8.000 1.2071 0.02220 0.01312 -0.0568 0.3355 1.0000
8.250 1.2215 0.02239 0.01343 -0.0544 0.3199 1.0000
8.500 1.2361 0.02265 0.01381 -0.0521 0.3025 1.0000
8.750 1.2484 0.02296 0.01413 -0.0494 0.2801 1.0000
9.000 1.2552 0.02346 0.01447 -0.0459 0.2488 1.0000
9.250 1.2593 0.02427 0.01511 -0.0421 0.2190 1.0000
9.500 1.2639 0.02516 0.01592 -0.0385 0.1966 1.0000
9.750 1.2683 0.02615 0.01686 -0.0351 0.1788 1.0000
10.000 1.2723 0.02723 0.01792 -0.0318 0.1620 1.0000
10.250 1.2732 0.02856 0.01918 -0.0283 0.1346 1.0000
10.500 1.2684 0.03027 0.02071 -0.0245 0.0938 1.0000
10.750 1.2535 0.03275 0.02289 -0.0201 0.0632 1.0000
11.000 1.2459 0.03493 0.02503 -0.0169 0.0456 1.0000
11.250 1.2351 0.03754 0.02757 -0.0140 0.0299 1.0000
11.500 1.2291 0.04001 0.03009 -0.0120 0.0271 1.0000
11.750 1.2229 0.04271 0.03289 -0.0104 0.0253 1.0000
12.000 1.2168 0.04566 0.03598 -0.0094 0.0243 1.0000
12.250 1.2103 0.04890 0.03938 -0.0088 0.0236 1.0000
12.500 1.2035 0.05244 0.04309 -0.0087 0.0231 1.0000
12.750 1.1954 0.05640 0.04723 -0.0091 0.0227 1.0000
13.000 1.1871 0.06062 0.05162 -0.0099 0.0223 1.0000
13.250 1.1783 0.06507 0.05624 -0.0109 0.0220 1.0000
13.500 1.1683 0.06982 0.06114 -0.0121 0.0216 1.0000
13.750 1.1584 0.07462 0.06610 -0.0134 0.0213 1.0000
14.000 1.1474 0.07965 0.07127 -0.0148 0.0208 1.0000
14.250 1.1373 0.08464 0.07640 -0.0163 0.0205 1.0000
14.500 1.1268 0.08977 0.08166 -0.0179 0.0202 1.0000
14.750 1.1161 0.09503 0.08704 -0.0196 0.0198 1.0000
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