USA 34 AIRFOIL (usa34-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 34 AIRFOIL (usa34-il) Reynolds number: 200,000 Max Cl/Cd: 60.57 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa34-il-200000-n5.txt Download as CSV file: xf-usa34-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 34 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.0220 0.10093 0.09646 -0.1292 0.8948 0.0388
-13.250 -0.0515 0.08249 0.07785 -0.1439 0.8827 0.0430
-13.000 -0.0134 0.08131 0.07663 -0.1489 0.8775 0.0435
-12.750 0.0169 0.07893 0.07419 -0.1544 0.8714 0.0442
-12.250 -0.3081 0.03002 0.02419 -0.1894 0.8336 0.0455
-12.000 -0.3210 0.02836 0.02237 -0.1853 0.8261 0.0461
-11.750 -0.3198 0.02698 0.02083 -0.1828 0.8202 0.0473
-11.500 -0.3070 0.02598 0.01972 -0.1817 0.8153 0.0491
-11.250 -0.2978 0.02530 0.01898 -0.1792 0.8096 0.0510
-11.000 -0.2848 0.02489 0.01855 -0.1770 0.8037 0.0540
-10.750 -0.2675 0.02438 0.01793 -0.1756 0.7986 0.0579
-10.250 -0.2319 0.02331 0.01649 -0.1727 0.7903 0.0671
-10.000 -0.2177 0.02289 0.01593 -0.1704 0.7856 0.0702
-9.750 -0.1998 0.02259 0.01547 -0.1686 0.7810 0.0736
-9.500 -0.1791 0.02219 0.01486 -0.1675 0.7767 0.0767
-9.000 -0.1396 0.02181 0.01426 -0.1645 0.7684 0.0818
-8.750 -0.1234 0.02151 0.01381 -0.1623 0.7638 0.0840
-8.500 -0.1025 0.02142 0.01372 -0.1609 0.7600 0.0858
-8.250 -0.0793 0.02127 0.01349 -0.1600 0.7565 0.0881
-8.000 -0.0546 0.02095 0.01298 -0.1595 0.7536 0.0902
-7.750 -0.0366 0.02061 0.01245 -0.1576 0.7502 0.0916
-7.500 -0.0194 0.02040 0.01227 -0.1554 0.7462 0.0928
-7.250 0.0002 0.02029 0.01216 -0.1538 0.7421 0.0945
-7.000 0.0221 0.02012 0.01193 -0.1525 0.7381 0.0961
-6.750 0.0471 0.01985 0.01153 -0.1519 0.7347 0.0977
-6.500 0.0727 0.01955 0.01108 -0.1514 0.7315 0.0991
-6.250 0.0878 0.01931 0.01077 -0.1487 0.7273 0.1002
-6.000 0.1059 0.01906 0.01047 -0.1467 0.7229 0.1013
-5.750 0.1270 0.01888 0.01028 -0.1452 0.7186 0.1027
-5.500 0.1522 0.01868 0.01003 -0.1446 0.7147 0.1040
-5.250 0.1791 0.01849 0.00976 -0.1443 0.7109 0.1058
-5.000 0.1924 0.01836 0.00962 -0.1412 0.7056 0.1074
-4.750 0.2108 0.01818 0.00937 -0.1391 0.7006 0.1089
-4.500 0.2333 0.01797 0.00904 -0.1379 0.6961 0.1105
-4.250 0.2612 0.01769 0.00872 -0.1377 0.6921 0.1118
-4.000 0.2748 0.01753 0.00859 -0.1347 0.6863 0.1127
-3.750 0.2905 0.01736 0.00841 -0.1321 0.6801 0.1136
-3.500 0.3131 0.01714 0.00814 -0.1309 0.6748 0.1147
-3.250 0.3351 0.01695 0.00791 -0.1295 0.6698 0.1159
-3.000 0.3459 0.01682 0.00778 -0.1259 0.6628 0.1170
-2.750 0.3642 0.01663 0.00755 -0.1237 0.6564 0.1184
-2.500 0.3825 0.01647 0.00732 -0.1216 0.6502 0.1199
-2.250 0.3923 0.01635 0.00719 -0.1177 0.6420 0.1213
-2.000 0.4121 0.01618 0.00700 -0.1159 0.6352 0.1230
-1.750 0.4237 0.01612 0.00697 -0.1125 0.6271 0.1249
-1.500 0.4406 0.01604 0.00685 -0.1102 0.6193 0.1274
-1.250 0.4568 0.01602 0.00679 -0.1077 0.6111 0.1305
-1.000 0.4734 0.01599 0.00672 -0.1053 0.6024 0.1339
-0.750 0.4906 0.01597 0.00670 -0.1030 0.5940 0.1380
-0.500 0.5077 0.01600 0.00667 -0.1008 0.5856 0.1432
-0.250 0.5271 0.01600 0.00662 -0.0990 0.5784 0.1484
0.000 0.5447 0.01604 0.00665 -0.0970 0.5710 0.1540
0.250 0.5648 0.01610 0.00662 -0.0954 0.5643 0.1607
0.500 0.5831 0.01615 0.00668 -0.0935 0.5577 0.1672
0.750 0.6020 0.01624 0.00675 -0.0918 0.5513 0.1749
1.000 0.6233 0.01631 0.00677 -0.0905 0.5455 0.1834
1.250 0.6431 0.01642 0.00690 -0.0890 0.5404 0.1932
1.500 0.6624 0.01653 0.00706 -0.0874 0.5352 0.2061
1.750 0.6833 0.01664 0.00720 -0.0861 0.5302 0.2229
2.000 0.7070 0.01676 0.00730 -0.0854 0.5258 0.2449
2.250 0.7256 0.01692 0.00754 -0.0838 0.5213 0.2658
2.500 0.7446 0.01710 0.00776 -0.0822 0.5166 0.2874
2.750 0.7659 0.01726 0.00795 -0.0811 0.5125 0.3094
3.000 0.7892 0.01740 0.00811 -0.0804 0.5088 0.3316
3.250 0.8148 0.01753 0.00826 -0.0802 0.5052 0.3555
3.500 0.8325 0.01772 0.00858 -0.0786 0.5011 0.3807
3.750 0.8525 0.01786 0.00887 -0.0775 0.4970 0.4194
4.250 1.0969 0.01811 0.01008 -0.1182 0.4860 1.0000
4.500 1.1095 0.01844 0.01046 -0.1156 0.4817 1.0000
4.750 1.1244 0.01879 0.01081 -0.1135 0.4774 1.0000
5.000 1.1403 0.01913 0.01111 -0.1116 0.4726 1.0000
5.250 1.1599 0.01945 0.01136 -0.1103 0.4688 1.0000
5.500 1.1801 0.01978 0.01164 -0.1092 0.4654 1.0000
5.750 1.1943 0.02018 0.01210 -0.1071 0.4619 1.0000
6.000 1.2087 0.02060 0.01255 -0.1051 0.4580 1.0000
6.250 1.2246 0.02101 0.01295 -0.1034 0.4542 1.0000
6.500 1.2427 0.02139 0.01330 -0.1020 0.4507 1.0000
6.750 1.2638 0.02173 0.01356 -0.1012 0.4472 1.0000
7.000 1.2745 0.02229 0.01420 -0.0988 0.4432 1.0000
7.250 1.2852 0.02287 0.01484 -0.0964 0.4384 1.0000
7.500 1.2976 0.02341 0.01537 -0.0944 0.4332 1.0000
7.750 1.3147 0.02385 0.01575 -0.0931 0.4291 1.0000
8.000 1.3260 0.02451 0.01647 -0.0910 0.4249 1.0000
8.250 1.3367 0.02522 0.01725 -0.0890 0.4202 1.0000
8.500 1.3483 0.02589 0.01793 -0.0871 0.4153 1.0000
8.750 1.3628 0.02646 0.01845 -0.0856 0.4107 1.0000
9.000 1.3704 0.02738 0.01945 -0.0834 0.4051 1.0000
9.250 1.3798 0.02825 0.02037 -0.0814 0.3997 1.0000
9.500 1.3915 0.02902 0.02113 -0.0798 0.3949 1.0000
9.750 1.4029 0.02985 0.02198 -0.0782 0.3904 1.0000
10.000 1.4117 0.03087 0.02309 -0.0765 0.3856 1.0000
10.250 1.4217 0.03183 0.02409 -0.0749 0.3808 1.0000
10.500 1.4324 0.03274 0.02498 -0.0733 0.3758 1.0000
10.750 1.4400 0.03393 0.02625 -0.0716 0.3705 1.0000
11.000 1.4468 0.03519 0.02756 -0.0699 0.3648 1.0000
11.250 1.4559 0.03628 0.02866 -0.0685 0.3596 1.0000
11.500 1.4625 0.03762 0.03006 -0.0669 0.3540 1.0000
11.750 1.4677 0.03910 0.03160 -0.0653 0.3475 1.0000
12.000 1.4744 0.04044 0.03294 -0.0638 0.3417 1.0000
12.250 1.4772 0.04220 0.03478 -0.0622 0.3342 1.0000
12.500 1.4804 0.04392 0.03652 -0.0606 0.3269 1.0000
12.750 1.4830 0.04577 0.03841 -0.0592 0.3192 1.0000
13.000 1.4853 0.04767 0.04035 -0.0578 0.3118 1.0000
13.250 1.4864 0.04973 0.04243 -0.0563 0.3040 1.0000
13.500 1.4867 0.05192 0.04467 -0.0550 0.2956 1.0000
13.750 1.4859 0.05425 0.04702 -0.0537 0.2874 1.0000
14.000 1.4835 0.05681 0.04960 -0.0524 0.2780 1.0000
14.250 1.4806 0.05947 0.05229 -0.0513 0.2687 1.0000
14.500 1.4742 0.06253 0.05533 -0.0501 0.2585 1.0000
14.750 1.4691 0.06557 0.05840 -0.0491 0.2483 1.0000
15.000 1.4634 0.06872 0.06156 -0.0482 0.2393 1.0000
15.250 1.4568 0.07201 0.06484 -0.0473 0.2301 1.0000
15.500 1.4519 0.07521 0.06807 -0.0467 0.2221 1.0000
15.750 1.4448 0.07866 0.07150 -0.0461 0.2142 1.0000
16.000 1.4411 0.08177 0.07464 -0.0456 0.2071 1.0000
16.250 1.4368 0.08497 0.07785 -0.0452 0.2010 1.0000
16.500 1.4353 0.08785 0.08075 -0.0449 0.1960 1.0000
16.750 1.4335 0.09082 0.08376 -0.0446 0.1907 1.0000
17.000 1.4318 0.09373 0.08666 -0.0444 0.1859 1.0000
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