USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 50,000 Max Cl/Cd: 27.06 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa29-il-50000-n5.txt Download as CSV file: xf-usa29-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2953 0.12809 0.12128 -0.0411 1.0000 0.1356
-10.250 -0.3116 0.12713 0.12044 -0.0407 1.0000 0.1369
-10.000 -0.3244 0.12557 0.11897 -0.0400 1.0000 0.1372
-9.750 -0.3339 0.12357 0.11705 -0.0389 1.0000 0.1373
-9.250 -0.3544 0.11166 0.10521 -0.0398 1.0000 0.0910
-9.000 -0.3599 0.10940 0.10300 -0.0381 1.0000 0.0903
-8.750 -0.3723 0.10719 0.10089 -0.0368 1.0000 0.0903
-8.500 -0.3742 0.10302 0.09671 -0.0408 0.9945 0.0910
-8.250 -0.3718 0.09824 0.09193 -0.0464 0.9857 0.0913
-8.000 -0.3675 0.09380 0.08747 -0.0505 0.9764 0.0912
-7.750 -0.3575 0.08939 0.08301 -0.0543 0.9676 0.0907
-7.500 -0.3464 0.08431 0.07786 -0.0594 0.9588 0.0904
-7.250 -0.3400 0.07936 0.07285 -0.0633 0.9476 0.0903
-7.000 -0.3410 0.07277 0.06611 -0.0685 0.9355 0.0913
-6.750 -0.3260 0.06890 0.06215 -0.0713 0.9269 0.0930
-6.500 -0.3130 0.06521 0.05833 -0.0732 0.9168 0.0941
-6.250 -0.3105 0.05885 0.05165 -0.0758 0.9053 0.0939
-6.000 -0.2971 0.05362 0.04603 -0.0783 0.8970 0.0944
-5.750 -0.2860 0.04994 0.04200 -0.0785 0.8864 0.0953
-5.500 -0.2720 0.04708 0.03880 -0.0783 0.8763 0.0971
-5.250 -0.2486 0.04407 0.03532 -0.0794 0.8692 0.1005
-5.000 -0.2360 0.04151 0.03221 -0.0781 0.8583 0.1032
-4.750 -0.2091 0.03880 0.02882 -0.0788 0.8520 0.1054
-4.500 -0.1902 0.03729 0.02703 -0.0776 0.8418 0.1071
-4.250 -0.1644 0.03606 0.02563 -0.0775 0.8340 0.1096
-4.000 -0.1381 0.03493 0.02429 -0.0774 0.8258 0.1134
-3.750 -0.1128 0.03390 0.02291 -0.0771 0.8175 0.1189
-3.500 -0.0831 0.03291 0.02176 -0.0774 0.8102 0.1250
-3.250 -0.0557 0.03216 0.02088 -0.0774 0.8022 0.1316
-3.000 -0.0245 0.03130 0.01984 -0.0779 0.7948 0.1398
-2.750 0.0142 0.03054 0.01901 -0.0798 0.7892 0.1543
-2.500 0.0403 0.03028 0.01877 -0.0796 0.7797 0.1736
-2.250 0.0837 0.02971 0.01821 -0.0822 0.7754 0.2084
-2.000 0.1011 0.02984 0.01834 -0.0804 0.7643 0.2316
-1.750 0.1332 0.02982 0.01835 -0.0806 0.7595 0.2645
-1.500 0.1430 0.03034 0.01886 -0.0774 0.7480 0.2847
-1.250 0.1650 0.03061 0.01903 -0.0759 0.7410 0.3117
-1.000 0.1834 0.03089 0.01919 -0.0741 0.7323 0.3344
-0.750 0.2170 0.03070 0.01880 -0.0748 0.7268 0.3557
-0.500 0.2392 0.03080 0.01876 -0.0740 0.7175 0.3705
-0.250 0.2796 0.03038 0.01811 -0.0760 0.7133 0.3927
0.000 0.2983 0.03060 0.01827 -0.0748 0.7035 0.4099
0.250 0.3415 0.03002 0.01761 -0.0774 0.6990 0.4332
0.500 0.3665 0.03011 0.01766 -0.0774 0.6904 0.4475
0.750 0.4059 0.02973 0.01723 -0.0794 0.6850 0.4624
1.000 0.4378 0.02958 0.01708 -0.0803 0.6785 0.4765
1.250 0.4653 0.02956 0.01709 -0.0805 0.6712 0.4900
1.500 0.5053 0.02905 0.01662 -0.0824 0.6671 0.5078
1.750 0.5177 0.02954 0.01721 -0.0802 0.6579 0.5219
2.000 0.5513 0.02911 0.01694 -0.0810 0.6530 0.5492
2.500 0.7049 0.02880 0.01743 -0.1010 0.6403 1.0000
2.750 0.7399 0.02877 0.01726 -0.1020 0.6357 1.0000
3.000 0.7460 0.02976 0.01824 -0.0987 0.6267 1.0000
3.250 0.7760 0.02991 0.01830 -0.0989 0.6215 1.0000
3.500 0.7877 0.03074 0.01911 -0.0965 0.6140 1.0000
3.750 0.8083 0.03123 0.01955 -0.0953 0.6075 1.0000
4.000 0.8440 0.03119 0.01946 -0.0963 0.6034 1.0000
4.250 0.8373 0.03273 0.02104 -0.0913 0.5940 1.0000
4.500 0.8674 0.03288 0.02116 -0.0915 0.5892 1.0000
4.750 0.8685 0.03418 0.02248 -0.0877 0.5812 1.0000
5.000 0.8861 0.03483 0.02316 -0.0862 0.5752 1.0000
5.250 0.9223 0.03477 0.02309 -0.0872 0.5715 1.0000
5.500 0.9006 0.03704 0.02543 -0.0805 0.5614 1.0000
5.750 0.9312 0.03718 0.02559 -0.0807 0.5571 1.0000
6.000 0.9099 0.03944 0.02791 -0.0742 0.5479 1.0000
6.250 0.9290 0.04006 0.02857 -0.0729 0.5426 1.0000
6.500 0.9700 0.03979 0.02835 -0.0744 0.5395 1.0000
6.750 0.9247 0.04345 0.03206 -0.0659 0.5277 1.0000
7.000 0.9591 0.04329 0.03196 -0.0662 0.5245 1.0000
7.250 0.9211 0.04741 0.03612 -0.0601 0.5124 1.0000
7.500 0.9514 0.04735 0.03616 -0.0598 0.5092 1.0000
8.000 0.9467 0.05185 0.04080 -0.0549 0.4936 1.0000
8.500 0.9439 0.05678 0.04589 -0.0510 0.4780 1.0000
9.000 0.9441 0.06189 0.05117 -0.0480 0.4625 1.0000
9.500 0.9451 0.06714 0.05662 -0.0455 0.4470 1.0000
10.000 0.9464 0.07247 0.06215 -0.0433 0.4318 1.0000
10.500 0.9481 0.07789 0.06779 -0.0414 0.4167 1.0000
11.000 0.9504 0.08336 0.07348 -0.0398 0.4017 1.0000
11.500 0.9537 0.08880 0.07920 -0.0384 0.3868 1.0000
11.750 0.9485 0.09221 0.08272 -0.0379 0.3776 1.0000
12.000 0.9859 0.08849 0.07921 -0.0352 0.3657 1.0000
12.250 1.0039 0.08627 0.07715 -0.0324 0.3462 1.0000
12.500 1.0299 0.08300 0.07411 -0.0296 0.3277 1.0000
12.750 1.0539 0.08017 0.07147 -0.0270 0.3073 1.0000
13.000 1.0461 0.08363 0.07508 -0.0266 0.2910 1.0000
13.250 1.0345 0.08776 0.07933 -0.0266 0.2705 1.0000
13.500 1.0305 0.09071 0.08240 -0.0262 0.2438 1.0000
13.750 1.0403 0.08917 0.07944 -0.0230 0.1038 1.0000
14.000 1.0236 0.09454 0.08449 -0.0235 0.0836 1.0000
14.250 1.0111 0.09954 0.08933 -0.0241 0.0734 1.0000
14.500 1.0031 0.10398 0.09373 -0.0246 0.0672 1.0000
14.750 0.9972 0.10814 0.09787 -0.0251 0.0628 1.0000
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Polar data table (+)
Polar graphs
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