USA 34 AIRFOIL (usa34-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 34 AIRFOIL (usa34-il) Reynolds number: 500,000 Max Cl/Cd: 86.57 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa34-il-500000.txt Download as CSV file: xf-usa34-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.4562 0.08731 0.08404 -0.1171 0.9826 0.0335
-16.250 -0.4768 0.07919 0.07577 -0.1238 0.9788 0.0337
-16.000 -0.4788 0.07442 0.07095 -0.1280 0.9736 0.0339
-15.750 -0.4665 0.07131 0.06784 -0.1317 0.9703 0.0344
-15.500 -0.4701 0.06723 0.06373 -0.1346 0.9604 0.0346
-15.250 -0.4773 0.06265 0.05909 -0.1381 0.9483 0.0350
-15.000 -0.4834 0.05730 0.05366 -0.1435 0.9381 0.0352
-14.750 -0.4841 0.05144 0.04768 -0.1512 0.9288 0.0354
-14.500 -0.4822 0.04413 0.04021 -0.1628 0.9188 0.0358
-14.250 -0.4815 0.03266 0.02839 -0.1844 0.9017 0.0360
-14.000 -0.4513 0.02654 0.02186 -0.1987 0.8874 0.0365
-13.750 -0.4279 0.02442 0.01948 -0.2027 0.8737 0.0372
-13.500 -0.4166 0.02320 0.01805 -0.2023 0.8606 0.0376
-13.250 -0.4170 0.02208 0.01682 -0.1993 0.8492 0.0381
-13.000 -0.4168 0.02120 0.01581 -0.1958 0.8390 0.0386
-12.750 -0.4136 0.02045 0.01498 -0.1923 0.8311 0.0391
-12.500 -0.4063 0.01975 0.01418 -0.1893 0.8238 0.0395
-12.250 -0.3926 0.01906 0.01335 -0.1875 0.8176 0.0404
-12.000 -0.3827 0.01850 0.01271 -0.1845 0.8123 0.0410
-11.750 -0.3701 0.01797 0.01208 -0.1820 0.8074 0.0417
-11.500 -0.3559 0.01739 0.01142 -0.1798 0.8029 0.0426
-11.250 -0.3388 0.01678 0.01072 -0.1783 0.7984 0.0441
-11.000 -0.3232 0.01629 0.01017 -0.1761 0.7943 0.0456
-10.750 -0.3078 0.01584 0.00968 -0.1738 0.7901 0.0473
-10.500 -0.2897 0.01541 0.00923 -0.1720 0.7864 0.0504
-10.250 -0.2674 0.01513 0.00898 -0.1710 0.7831 0.0566
-10.000 -0.2398 0.01507 0.00889 -0.1707 0.7794 0.0643
-9.750 -0.2129 0.01508 0.00882 -0.1703 0.7757 0.0699
-9.500 -0.1897 0.01517 0.00889 -0.1691 0.7721 0.0742
-9.250 -0.1668 0.01515 0.00882 -0.1679 0.7686 0.0774
-9.000 -0.1422 0.01523 0.00888 -0.1670 0.7656 0.0804
-8.750 -0.1173 0.01528 0.00880 -0.1662 0.7626 0.0829
-8.500 -0.0924 0.01512 0.00860 -0.1656 0.7596 0.0851
-8.250 -0.0662 0.01515 0.00862 -0.1651 0.7563 0.0873
-8.000 -0.0458 0.01513 0.00858 -0.1634 0.7533 0.0893
-7.750 -0.0240 0.01510 0.00847 -0.1620 0.7501 0.0909
-7.500 -0.0018 0.01487 0.00818 -0.1607 0.7469 0.0925
-7.250 0.0216 0.01465 0.00796 -0.1598 0.7439 0.0940
-7.000 0.0470 0.01457 0.00786 -0.1591 0.7408 0.0956
-6.750 0.0759 0.01454 0.00776 -0.1592 0.7371 0.0971
-6.500 0.0950 0.01440 0.00760 -0.1572 0.7340 0.0984
-6.250 0.1160 0.01423 0.00739 -0.1556 0.7305 0.0993
-6.000 0.1387 0.01409 0.00720 -0.1544 0.7268 0.1002
-5.750 0.1624 0.01388 0.00692 -0.1534 0.7234 0.1010
-5.500 0.1880 0.01355 0.00655 -0.1528 0.7198 0.1024
-5.250 0.2130 0.01340 0.00640 -0.1521 0.7160 0.1037
-5.000 0.2318 0.01329 0.00631 -0.1500 0.7120 0.1051
-4.750 0.2527 0.01312 0.00612 -0.1484 0.7076 0.1061
-4.500 0.2753 0.01295 0.00591 -0.1471 0.7034 0.1071
-4.250 0.3020 0.01283 0.00572 -0.1467 0.6992 0.1082
-4.000 0.3227 0.01271 0.00558 -0.1450 0.6949 0.1094
-3.750 0.3405 0.01260 0.00545 -0.1427 0.6897 0.1104
-3.500 0.3597 0.01234 0.00518 -0.1407 0.6844 0.1119
-3.250 0.3842 0.01217 0.00498 -0.1398 0.6792 0.1136
-3.000 0.3994 0.01205 0.00489 -0.1369 0.6735 0.1151
-2.750 0.4153 0.01191 0.00475 -0.1342 0.6671 0.1164
-2.500 0.4352 0.01180 0.00457 -0.1323 0.6610 0.1177
-2.250 0.4461 0.01166 0.00444 -0.1285 0.6538 0.1190
-2.000 0.4580 0.01154 0.00428 -0.1249 0.6454 0.1203
-1.750 0.4725 0.01147 0.00416 -0.1219 0.6371 0.1216
-1.500 0.4842 0.01132 0.00402 -0.1183 0.6272 0.1242
-1.250 0.4977 0.01129 0.00398 -0.1152 0.6175 0.1268
-1.000 0.5109 0.01131 0.00395 -0.1119 0.6066 0.1300
-0.750 0.5257 0.01137 0.00396 -0.1091 0.5956 0.1333
-0.500 0.5388 0.01139 0.00395 -0.1059 0.5853 0.1389
-0.250 0.5542 0.01147 0.00400 -0.1033 0.5754 0.1453
0.000 0.5698 0.01154 0.00404 -0.1007 0.5669 0.1532
0.250 0.5877 0.01163 0.00411 -0.0986 0.5592 0.1610
0.500 0.6051 0.01172 0.00417 -0.0965 0.5522 0.1697
0.750 0.6240 0.01181 0.00425 -0.0946 0.5462 0.1778
1.000 0.6426 0.01189 0.00435 -0.0928 0.5402 0.1870
1.250 0.6614 0.01203 0.00445 -0.0910 0.5343 0.1965
1.500 0.6821 0.01211 0.00458 -0.0896 0.5295 0.2110
1.750 0.7024 0.01218 0.00473 -0.0881 0.5251 0.2310
2.000 0.7228 0.01229 0.00489 -0.0867 0.5205 0.2559
2.250 0.7439 0.01243 0.00505 -0.0855 0.5161 0.2810
2.500 0.7665 0.01258 0.00522 -0.0845 0.5116 0.3026
2.750 0.7860 0.01268 0.00539 -0.0830 0.5079 0.3204
3.000 0.8058 0.01281 0.00556 -0.0815 0.5035 0.3384
3.250 0.8268 0.01296 0.00573 -0.0803 0.4990 0.3581
3.500 0.8526 0.01311 0.00590 -0.0801 0.4943 0.3845
3.750 0.8708 0.01318 0.00614 -0.0785 0.4905 0.4236
4.000 1.1246 0.01299 0.00720 -0.1280 0.4820 1.0000
4.250 1.1441 0.01323 0.00739 -0.1265 0.4784 1.0000
4.500 1.1659 0.01349 0.00759 -0.1255 0.4745 1.0000
4.750 1.1819 0.01369 0.00782 -0.1234 0.4713 1.0000
5.000 1.1960 0.01393 0.00806 -0.1210 0.4664 1.0000
5.250 1.2137 0.01418 0.00829 -0.1192 0.4628 1.0000
5.500 1.2317 0.01448 0.00853 -0.1176 0.4585 1.0000
5.750 1.2489 0.01476 0.00881 -0.1159 0.4545 1.0000
6.000 1.2659 0.01503 0.00911 -0.1141 0.4513 1.0000
6.250 1.2817 0.01532 0.00942 -0.1122 0.4472 1.0000
6.500 1.2979 0.01565 0.00973 -0.1104 0.4432 1.0000
6.750 1.3154 0.01602 0.01004 -0.1088 0.4389 1.0000
7.000 1.3321 0.01636 0.01041 -0.1072 0.4357 1.0000
7.250 1.3476 0.01672 0.01081 -0.1054 0.4319 1.0000
7.500 1.3638 0.01710 0.01121 -0.1037 0.4281 1.0000
7.750 1.3791 0.01753 0.01162 -0.1020 0.4242 1.0000
8.000 1.3956 0.01798 0.01202 -0.1005 0.4198 1.0000
8.250 1.4095 0.01845 0.01257 -0.0987 0.4159 1.0000
8.500 1.4233 0.01896 0.01312 -0.0969 0.4110 1.0000
8.750 1.4369 0.01953 0.01367 -0.0951 0.4064 1.0000
9.000 1.4513 0.02010 0.01420 -0.0935 0.4022 1.0000
9.250 1.4663 0.02064 0.01482 -0.0920 0.3984 1.0000
9.500 1.4804 0.02124 0.01546 -0.0905 0.3939 1.0000
9.750 1.4937 0.02190 0.01612 -0.0889 0.3893 1.0000
10.000 1.5047 0.02270 0.01689 -0.0871 0.3843 1.0000
10.250 1.5195 0.02333 0.01760 -0.0858 0.3801 1.0000
10.500 1.5321 0.02409 0.01840 -0.0843 0.3750 1.0000
10.750 1.5427 0.02497 0.01926 -0.0826 0.3699 1.0000
11.000 1.5539 0.02586 0.02018 -0.0811 0.3646 1.0000
11.250 1.5655 0.02675 0.02112 -0.0796 0.3588 1.0000
11.500 1.5745 0.02781 0.02217 -0.0779 0.3530 1.0000
11.750 1.5843 0.02885 0.02324 -0.0764 0.3474 1.0000
12.000 1.5943 0.02991 0.02434 -0.0750 0.3408 1.0000
12.250 1.5987 0.03134 0.02574 -0.0731 0.3338 1.0000
12.500 1.6081 0.03251 0.02696 -0.0717 0.3260 1.0000
12.750 1.6116 0.03409 0.02853 -0.0699 0.3183 1.0000
13.000 1.6189 0.03545 0.02993 -0.0685 0.3102 1.0000
13.250 1.6183 0.03741 0.03186 -0.0665 0.3008 1.0000
13.500 1.6228 0.03905 0.03354 -0.0650 0.2910 1.0000
13.750 1.6216 0.04117 0.03564 -0.0631 0.2804 1.0000
14.000 1.6153 0.04378 0.03821 -0.0611 0.2682 1.0000
14.250 1.6106 0.04633 0.04074 -0.0592 0.2552 1.0000
14.500 1.6040 0.04910 0.04350 -0.0575 0.2421 1.0000
14.750 1.5958 0.05214 0.04651 -0.0557 0.2307 1.0000
15.000 1.5848 0.05550 0.04984 -0.0541 0.2199 1.0000
15.250 1.5777 0.05857 0.05292 -0.0527 0.2108 1.0000
15.500 1.5715 0.06163 0.05598 -0.0515 0.2033 1.0000
15.750 1.5662 0.06467 0.05904 -0.0505 0.1971 1.0000
16.000 1.5592 0.06793 0.06230 -0.0495 0.1920 1.0000
16.250 1.5581 0.07058 0.06500 -0.0488 0.1871 1.0000
16.500 1.5551 0.07348 0.06794 -0.0482 0.1831 1.0000
16.750 1.5493 0.07671 0.07118 -0.0475 0.1791 1.0000
17.000 1.5509 0.07916 0.07368 -0.0471 0.1758 1.0000
17.250 1.5506 0.08182 0.07640 -0.0467 0.1723 1.0000
17.500 1.5487 0.08467 0.07928 -0.0463 0.1688 1.0000
17.750 1.5438 0.08787 0.08248 -0.0459 0.1650 1.0000
18.000 1.5454 0.09036 0.08505 -0.0457 0.1617 1.0000
18.250 1.5467 0.09290 0.08765 -0.0455 0.1582 1.0000
18.500 1.5417 0.09622 0.09099 -0.0454 0.1539 1.0000
18.750 1.5387 0.09924 0.09402 -0.0453 0.1498 1.0000
19.000 1.5396 0.10192 0.09679 -0.0454 0.1459 1.0000
19.250 1.5365 0.10506 0.09996 -0.0455 0.1410 1.0000
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