USA 34 AIRFOIL (usa34-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 34 AIRFOIL (usa34-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.36 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa34-il-1000000-n5.txt Download as CSV file: xf-usa34-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.2663 0.08909 0.08599 -0.1478 0.8987 0.0230
-16.750 -0.2559 0.08557 0.08222 -0.1520 0.8651 0.0232
-16.500 -0.2533 0.08260 0.07909 -0.1540 0.8413 0.0233
-16.250 -0.2521 0.07961 0.07599 -0.1558 0.8254 0.0235
-16.000 -0.2490 0.07703 0.07331 -0.1574 0.8125 0.0236
-15.750 -0.2530 0.07343 0.06967 -0.1596 0.8022 0.0241
-15.500 -0.2568 0.06993 0.06609 -0.1618 0.7927 0.0242
-15.250 -0.2653 0.06584 0.06195 -0.1644 0.7853 0.0245
-14.750 -0.5307 0.02498 0.02023 -0.2006 0.7668 0.0234
-14.500 -0.5368 0.02308 0.01818 -0.1983 0.7609 0.0235
-14.000 -0.5428 0.02090 0.01579 -0.1907 0.7501 0.0240
-13.750 -0.5360 0.02009 0.01490 -0.1879 0.7455 0.0242
-13.500 -0.5260 0.01941 0.01414 -0.1854 0.7414 0.0245
-13.250 -0.5144 0.01881 0.01346 -0.1830 0.7376 0.0247
-13.000 -0.5014 0.01827 0.01284 -0.1807 0.7338 0.0249
-12.750 -0.4869 0.01774 0.01225 -0.1786 0.7308 0.0251
-12.500 -0.4707 0.01727 0.01172 -0.1766 0.7278 0.0255
-12.250 -0.4542 0.01681 0.01120 -0.1747 0.7246 0.0258
-12.000 -0.4360 0.01645 0.01078 -0.1730 0.7216 0.0262
-11.750 -0.4187 0.01605 0.01031 -0.1711 0.7184 0.0264
-11.500 -0.4003 0.01570 0.00990 -0.1693 0.7154 0.0267
-11.250 -0.3811 0.01538 0.00951 -0.1676 0.7126 0.0268
-11.000 -0.3632 0.01493 0.00900 -0.1658 0.7105 0.0272
-10.750 -0.3444 0.01451 0.00854 -0.1641 0.7086 0.0275
-10.500 -0.3251 0.01412 0.00811 -0.1624 0.7063 0.0280
-10.250 -0.3052 0.01377 0.00772 -0.1608 0.7037 0.0285
-10.000 -0.2849 0.01347 0.00737 -0.1593 0.7007 0.0288
-9.750 -0.2648 0.01319 0.00704 -0.1576 0.6974 0.0292
-9.500 -0.2445 0.01295 0.00674 -0.1560 0.6940 0.0296
-9.250 -0.2231 0.01272 0.00645 -0.1545 0.6911 0.0300
-9.000 -0.2008 0.01248 0.00618 -0.1532 0.6894 0.0304
-8.750 -0.1788 0.01222 0.00589 -0.1519 0.6874 0.0309
-8.500 -0.1577 0.01194 0.00558 -0.1504 0.6849 0.0315
-8.250 -0.1373 0.01168 0.00529 -0.1487 0.6819 0.0324
-8.000 -0.1172 0.01146 0.00503 -0.1469 0.6786 0.0333
-7.750 -0.0970 0.01126 0.00480 -0.1452 0.6755 0.0343
-7.500 -0.0773 0.01104 0.00454 -0.1433 0.6724 0.0361
-7.000 -0.0366 0.01040 0.00403 -0.1400 0.6674 0.0616
-6.750 -0.0135 0.01029 0.00393 -0.1388 0.6638 0.0650
-6.500 0.0090 0.01022 0.00384 -0.1374 0.6595 0.0679
-6.250 0.0305 0.01017 0.00373 -0.1358 0.6550 0.0690
-6.000 0.0525 0.01007 0.00363 -0.1344 0.6510 0.0706
-5.750 0.0763 0.00999 0.00355 -0.1333 0.6468 0.0720
-5.500 0.0984 0.00992 0.00346 -0.1319 0.6410 0.0732
-5.250 0.1182 0.00989 0.00337 -0.1299 0.6344 0.0741
-5.000 0.1409 0.00983 0.00329 -0.1286 0.6276 0.0750
-4.750 0.1591 0.00982 0.00322 -0.1264 0.6175 0.0754
-4.500 0.1787 0.00979 0.00314 -0.1244 0.6068 0.0763
-4.250 0.1954 0.00977 0.00306 -0.1219 0.5933 0.0770
-4.000 0.2114 0.00982 0.00303 -0.1193 0.5776 0.0776
-3.750 0.2270 0.00990 0.00303 -0.1166 0.5613 0.0783
-3.500 0.2441 0.00998 0.00304 -0.1142 0.5474 0.0792
-3.250 0.2626 0.01003 0.00305 -0.1121 0.5384 0.0800
-3.000 0.2802 0.01011 0.00307 -0.1098 0.5285 0.0808
-2.750 0.3001 0.01015 0.00308 -0.1080 0.5223 0.0814
-2.500 0.3210 0.01019 0.00309 -0.1064 0.5166 0.0821
-2.250 0.3408 0.01024 0.00310 -0.1046 0.5108 0.0826
-2.000 0.3603 0.01031 0.00314 -0.1027 0.5054 0.0831
-1.750 0.3820 0.01032 0.00314 -0.1013 0.5015 0.0839
-1.500 0.4023 0.01034 0.00315 -0.0997 0.4969 0.0849
-1.250 0.4224 0.01038 0.00318 -0.0979 0.4929 0.0859
-1.000 0.4418 0.01044 0.00322 -0.0961 0.4888 0.0868
-0.750 0.4623 0.01048 0.00326 -0.0945 0.4852 0.0889
-0.500 0.4846 0.01050 0.00329 -0.0933 0.4823 0.0898
-0.250 0.5061 0.01055 0.00333 -0.0919 0.4790 0.0909
0.250 0.5461 0.01068 0.00346 -0.0886 0.4718 0.0945
0.500 0.5654 0.01078 0.00354 -0.0869 0.4684 0.0967
0.750 0.5862 0.01084 0.00362 -0.0855 0.4655 0.1005
1.000 0.6078 0.01088 0.00370 -0.0842 0.4610 0.1091
1.250 0.6286 0.01095 0.00380 -0.0828 0.4579 0.1181
1.500 0.6490 0.01103 0.00392 -0.0814 0.4551 0.1278
1.750 0.6671 0.01119 0.00407 -0.0795 0.4500 0.1330
2.000 0.6869 0.01132 0.00421 -0.0780 0.4469 0.1395
2.250 0.7091 0.01140 0.00432 -0.0769 0.4448 0.1438
2.500 0.7305 0.01152 0.00444 -0.0758 0.4418 0.1474
2.750 0.7514 0.01163 0.00459 -0.0745 0.4381 0.1544
3.000 0.7717 0.01179 0.00475 -0.0732 0.4347 0.1588
3.250 0.7891 0.01203 0.00497 -0.0714 0.4296 0.1629
3.500 0.8104 0.01218 0.00515 -0.0704 0.4261 0.1706
3.750 0.8326 0.01231 0.00532 -0.0695 0.4231 0.1777
4.000 0.8552 0.01245 0.00553 -0.0688 0.4192 0.2032
4.250 0.8764 0.01264 0.00580 -0.0679 0.4152 0.2332
4.500 0.8959 0.01292 0.00611 -0.0668 0.4106 0.2564
4.750 0.9188 0.01311 0.00635 -0.0662 0.4061 0.2724
5.000 0.9410 0.01335 0.00662 -0.0656 0.4010 0.2874
5.250 0.9612 0.01367 0.00696 -0.0647 0.3957 0.3010
5.500 0.9822 0.01399 0.00730 -0.0640 0.3920 0.3142
5.750 1.0067 0.01422 0.00758 -0.0639 0.3879 0.3320
6.250 1.2326 0.01411 0.00892 -0.1021 0.3713 0.9933
6.500 1.2650 0.01456 0.00935 -0.1038 0.3653 0.9974
6.750 1.3124 0.01509 0.00982 -0.1089 0.3584 1.0000
7.000 1.3287 0.01553 0.01026 -0.1073 0.3530 1.0000
7.250 1.3431 0.01607 0.01078 -0.1055 0.3458 1.0000
7.500 1.3563 0.01669 0.01137 -0.1036 0.3393 1.0000
7.750 1.3697 0.01733 0.01197 -0.1018 0.3303 1.0000
8.000 1.3815 0.01806 0.01267 -0.0998 0.3226 1.0000
8.250 1.3916 0.01891 0.01347 -0.0977 0.3107 1.0000
8.500 1.4035 0.01969 0.01422 -0.0958 0.3025 1.0000
8.750 1.4122 0.02067 0.01516 -0.0937 0.2919 1.0000
9.000 1.4236 0.02153 0.01599 -0.0919 0.2827 1.0000
9.250 1.4314 0.02263 0.01704 -0.0898 0.2722 1.0000
9.500 1.4381 0.02381 0.01817 -0.0877 0.2601 1.0000
9.750 1.4427 0.02515 0.01945 -0.0854 0.2456 1.0000
10.000 1.4447 0.02671 0.02093 -0.0829 0.2300 1.0000
10.250 1.4478 0.02823 0.02239 -0.0806 0.2157 1.0000
10.500 1.4469 0.03008 0.02416 -0.0781 0.1999 1.0000
10.750 1.4483 0.03182 0.02586 -0.0759 0.1871 1.0000
11.000 1.4546 0.03327 0.02729 -0.0743 0.1803 1.0000
11.250 1.4624 0.03463 0.02865 -0.0728 0.1750 1.0000
11.500 1.4666 0.03630 0.03030 -0.0711 0.1686 1.0000
11.750 1.4770 0.03750 0.03152 -0.0700 0.1659 1.0000
12.000 1.4850 0.03893 0.03298 -0.0688 0.1632 1.0000
12.250 1.4932 0.04035 0.03441 -0.0676 0.1604 1.0000
12.500 1.5000 0.04192 0.03600 -0.0663 0.1575 1.0000
12.750 1.5064 0.04355 0.03766 -0.0651 0.1546 1.0000
13.000 1.5156 0.04493 0.03907 -0.0642 0.1521 1.0000
13.250 1.5231 0.04652 0.04070 -0.0631 0.1504 1.0000
13.500 1.5303 0.04812 0.04233 -0.0621 0.1482 1.0000
13.750 1.5342 0.05006 0.04428 -0.0610 0.1451 1.0000
14.000 1.5380 0.05205 0.04630 -0.0600 0.1424 1.0000
14.250 1.5438 0.05386 0.04816 -0.0591 0.1406 1.0000
14.500 1.5502 0.05565 0.04999 -0.0583 0.1387 1.0000
14.750 1.5571 0.05738 0.05177 -0.0575 0.1370 1.0000
15.000 1.5602 0.05955 0.05397 -0.0567 0.1343 1.0000
15.250 1.5602 0.06202 0.05646 -0.0558 0.1303 1.0000
15.500 1.5612 0.06445 0.05893 -0.0550 0.1267 1.0000
15.750 1.5634 0.06678 0.06130 -0.0544 0.1232 1.0000
16.000 1.5582 0.06988 0.06439 -0.0535 0.1158 1.0000
16.500 1.5322 0.07803 0.07247 -0.0518 0.0935 1.0000
16.750 1.5262 0.08139 0.07586 -0.0513 0.0893 1.0000
17.000 1.5234 0.08439 0.07889 -0.0509 0.0867 1.0000
17.250 1.5216 0.08732 0.08187 -0.0505 0.0851 1.0000
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Polar data table (+)
Polar graphs
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