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USA 34 AIRFOIL (usa34-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 34 AIRFOIL (usa34-il)
Reynolds number: 100,000
Max Cl/Cd: 40.86 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa34-il-100000-n5.txt
Download as CSV file: xf-usa34-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.0212   0.11586   0.11012  -0.1149   0.9051   0.0552
 -12.500   0.0287   0.11162   0.10584  -0.1181   0.9012   0.0559
 -12.250   0.0291   0.10591   0.10009  -0.1229   0.8981   0.0572
 -12.000   0.0527   0.10357   0.09772  -0.1259   0.8957   0.0584
 -11.750   0.0680   0.10004   0.09415  -0.1296   0.8927   0.0597
 -11.500   0.0717   0.09628   0.09036  -0.1321   0.8861   0.0608
 -11.250   0.0739   0.09081   0.08485  -0.1367   0.8815   0.0621
 -11.000   0.0941   0.08750   0.08149  -0.1412   0.8779   0.0643
 -10.750   0.1107   0.08327   0.07719  -0.1466   0.8744   0.0668
 -10.500   0.0912   0.07767   0.07159  -0.1490   0.8660   0.0692
 -10.250   0.1126   0.07587   0.06975  -0.1514   0.8606   0.0712
 -10.000   0.0958   0.06792   0.06175  -0.1587   0.8554   0.0763
  -9.750   0.1072   0.06757   0.06140  -0.1575   0.8471   0.0781
  -9.500   0.0637   0.05972   0.05355  -0.1622   0.8381   0.0842
  -9.250   0.0909   0.05903   0.05279  -0.1640   0.8333   0.0868
  -9.000  -0.1171   0.04102   0.03418  -0.1578   0.8153   0.0922
  -8.750  -0.0689   0.04327   0.03661  -0.1584   0.8120   0.0940
  -8.500  -0.0823   0.04282   0.03613  -0.1525   0.8040   0.0955
  -8.250  -0.1031   0.03922   0.03207  -0.1488   0.7981   0.0993
  -8.000  -0.0833   0.03773   0.03033  -0.1489   0.7949   0.1022
  -7.750  -0.0780   0.03813   0.03078  -0.1448   0.7886   0.1038
  -7.500  -0.0749   0.03790   0.03048  -0.1408   0.7822   0.1061
  -7.250  -0.0772   0.03531   0.02726  -0.1377   0.7774   0.1104
  -7.000  -0.0337   0.03568   0.02778  -0.1400   0.7749   0.1132
  -6.750  -0.0279   0.03572   0.02782  -0.1361   0.7688   0.1151
  -6.500  -0.0303   0.03534   0.02733  -0.1310   0.7616   0.1173
  -6.250  -0.0182   0.03368   0.02519  -0.1290   0.7573   0.1205
  -6.000   0.0167   0.03307   0.02452  -0.1304   0.7546   0.1232
  -5.750   0.0172   0.03302   0.02445  -0.1254   0.7476   0.1245
  -5.500   0.0206   0.03277   0.02416  -0.1210   0.7403   0.1261
  -5.250   0.0474   0.03178   0.02293  -0.1209   0.7365   0.1281
  -5.000   0.0812   0.03057   0.02140  -0.1221   0.7338   0.1302
  -4.750   0.0640   0.03058   0.02134  -0.1139   0.7244   0.1307
  -4.500   0.0792   0.02985   0.02036  -0.1115   0.7186   0.1319
  -4.250   0.1111   0.02884   0.01903  -0.1121   0.7151   0.1331
  -4.000   0.1538   0.02788   0.01796  -0.1147   0.7125   0.1342
  -3.750   0.1293   0.02825   0.01835  -0.1050   0.7009   0.1345
  -3.500   0.1578   0.02763   0.01764  -0.1049   0.6964   0.1356
  -3.250   0.1963   0.02688   0.01677  -0.1066   0.6934   0.1372
  -3.000   0.1888   0.02708   0.01696  -0.1001   0.6836   0.1379
  -2.750   0.2094   0.02672   0.01649  -0.0986   0.6776   0.1394
  -2.500   0.2462   0.02602   0.01566  -0.0998   0.6740   0.1419
  -2.250   0.2475   0.02619   0.01577  -0.0950   0.6651   0.1435
  -2.000   0.2650   0.02603   0.01548  -0.0929   0.6583   0.1458
  -1.750   0.3005   0.02539   0.01481  -0.0939   0.6548   0.1486
  -1.500   0.3018   0.02570   0.01515  -0.0893   0.6457   0.1503
  -1.250   0.3217   0.02554   0.01496  -0.0877   0.6393   0.1530
  -1.000   0.3580   0.02494   0.01427  -0.0888   0.6357   0.1576
  -0.750   0.3563   0.02545   0.01475  -0.0837   0.6260   0.1602
  -0.500   0.3806   0.02519   0.01450  -0.0829   0.6208   0.1645
  -0.250   0.4165   0.02467   0.01395  -0.0840   0.6174   0.1715
   0.000   0.4175   0.02523   0.01451  -0.0796   0.6084   0.1757
   0.250   0.4434   0.02502   0.01433  -0.0791   0.6031   0.1835
   0.750   0.4875   0.02502   0.01436  -0.0771   0.5922   0.2021
   1.000   0.5101   0.02507   0.01441  -0.0762   0.5869   0.2138
   1.250   0.5464   0.02476   0.01410  -0.0775   0.5833   0.2296
   1.500   0.5856   0.02454   0.01389  -0.0795   0.5795   0.2515
   1.750   0.5956   0.02518   0.01459  -0.0770   0.5721   0.2679
   2.000   0.6300   0.02510   0.01457  -0.0782   0.5676   0.2978
   2.250   0.6731   0.02480   0.01429  -0.0809   0.5645   0.3352
   2.500   0.7025   0.02490   0.01446  -0.0815   0.5600   0.3674
   2.750   0.7188   0.02540   0.01506  -0.0802   0.5540   0.3957
   3.000   0.7550   0.02523   0.01508  -0.0820   0.5497   0.4506
   3.500   0.9545   0.02441   0.01506  -0.1105   0.5423   1.0000
   3.750   0.9602   0.02517   0.01581  -0.1071   0.5368   1.0000
   4.000   0.9799   0.02555   0.01611  -0.1059   0.5322   1.0000
   4.250   1.0095   0.02568   0.01611  -0.1062   0.5284   1.0000
   4.500   1.0480   0.02565   0.01593  -0.1079   0.5254   1.0000
   4.750   1.0444   0.02670   0.01705  -0.1032   0.5202   1.0000
   5.000   1.0547   0.02745   0.01780  -0.1008   0.5156   1.0000
   5.250   1.0769   0.02783   0.01812  -0.1001   0.5117   1.0000
   5.500   1.1085   0.02793   0.01813  -0.1007   0.5084   1.0000
   5.750   1.1414   0.02806   0.01816  -0.1016   0.5052   1.0000
   6.000   1.1269   0.02961   0.01985  -0.0957   0.4998   1.0000
   6.250   1.1339   0.03059   0.02085  -0.0931   0.4953   1.0000
   6.500   1.1567   0.03094   0.02116  -0.0925   0.4912   1.0000
   6.750   1.1921   0.03083   0.02096  -0.0936   0.4878   1.0000
   7.000   1.1957   0.03190   0.02208  -0.0906   0.4830   1.0000
   7.250   1.1790   0.03392   0.02422  -0.0853   0.4767   1.0000
   7.500   1.1957   0.03449   0.02478  -0.0840   0.4721   1.0000
   7.750   1.2318   0.03415   0.02435  -0.0850   0.4684   1.0000
   8.000   1.2383   0.03525   0.02549  -0.0827   0.4640   1.0000
   8.250   1.2032   0.03863   0.02906  -0.0762   0.4563   1.0000
   8.500   1.2229   0.03904   0.02945  -0.0754   0.4520   1.0000
   8.750   1.2572   0.03864   0.02900  -0.0760   0.4490   1.0000
   9.000   1.2322   0.04186   0.03236  -0.0713   0.4425   1.0000
   9.250   1.2076   0.04537   0.03600  -0.0672   0.4347   1.0000
   9.500   1.2399   0.04479   0.03538  -0.0673   0.4315   1.0000
   9.750   1.2826   0.04355   0.03406  -0.0684   0.4289   1.0000
  10.250   1.2276   0.05151   0.04229  -0.0607   0.4128   1.0000
  10.500   1.2692   0.04999   0.04072  -0.0613   0.4107   1.0000
  11.000   1.1662   0.06432   0.05538  -0.0538   0.3883   1.0000
  11.250   1.2601   0.05693   0.04784  -0.0558   0.3922   1.0000
  11.750   1.2033   0.06748   0.05863  -0.0515   0.3735   1.0000
  12.250   1.1749   0.07592   0.06723  -0.0493   0.3557   1.0000
  12.750   1.1817   0.08037   0.07177  -0.0480   0.3420   1.0000
  13.250   1.1762   0.08652   0.07804  -0.0469   0.3255   1.0000
  13.750   1.1769   0.09198   0.08361  -0.0461   0.3094   1.0000
  14.500   1.2136   0.09531   0.08700  -0.0450   0.2908   1.0000
  15.000   1.2176   0.10046   0.09224  -0.0446   0.2753   1.0000
  15.250   1.1978   0.10626   0.09814  -0.0449   0.2637   1.0000
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