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USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 35 AIRFOIL (usa35-il)
Reynolds number: 100,000
Max Cl/Cd: 35.44 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35-il-100000.txt
Download as CSV file: xf-usa35-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.0650   0.10212   0.09716  -0.0974   0.9220   0.1273
  -8.500   0.0512   0.10035   0.09540  -0.1040   0.9089   0.1330
  -8.250   0.0767   0.09564   0.09069  -0.1052   0.9015   0.1347
  -8.000   0.1046   0.09227   0.08730  -0.1053   0.8933   0.1375
  -7.750   0.1154   0.08968   0.08470  -0.1063   0.8816   0.1420
  -7.500   0.0731   0.08837   0.08342  -0.1118   0.8625   0.1467
  -7.250   0.1214   0.08399   0.07899  -0.1091   0.8590   0.1491
  -7.000   0.1337   0.08199   0.07698  -0.1078   0.8455   0.1526
  -6.500   0.1172   0.07726   0.07223  -0.1116   0.8210   0.1626
  -6.250   0.1410   0.07524   0.07018  -0.1084   0.8118   0.1666
  -6.000   0.1187   0.07231   0.06714  -0.1184   0.7992   0.1774
  -5.750   0.1420   0.07018   0.06506  -0.1132   0.7906   0.1797
  -5.500   0.1583   0.06842   0.06330  -0.1113   0.7814   0.1843
  -5.250   0.1606   0.06481   0.05951  -0.1183   0.7751   0.1963
  -5.000   0.1709   0.06355   0.05834  -0.1149   0.7637   0.1991
  -4.750   0.1792   0.06077   0.05533  -0.1206   0.7567   0.2147
  -4.500   0.1953   0.05884   0.05347  -0.1176   0.7492   0.2176
  -4.250   0.2093   0.05742   0.05206  -0.1162   0.7409   0.2240
  -4.000   0.2249   0.04176   0.03476  -0.1324   0.7362   0.1351
  -3.750   0.2499   0.03892   0.03160  -0.1328   0.7310   0.1283
  -3.500   0.2642   0.03602   0.02774  -0.1318   0.7220   0.1215
  -3.250   0.2925   0.03447   0.02621  -0.1321   0.7166   0.1241
  -3.000   0.3259   0.03300   0.02448  -0.1328   0.7125   0.1268
  -2.750   0.3399   0.03259   0.02391  -0.1310   0.7031   0.1281
  -2.500   0.3694   0.03137   0.02236  -0.1309   0.6969   0.1305
  -2.250   0.4047   0.03003   0.02068  -0.1316   0.6925   0.1350
  -2.000   0.4218   0.02995   0.02066  -0.1301   0.6842   0.1384
  -1.750   0.4486   0.02940   0.01997  -0.1296   0.6776   0.1432
  -1.500   0.4826   0.02846   0.01889  -0.1301   0.6731   0.1496
  -1.250   0.5070   0.02829   0.01870  -0.1295   0.6671   0.1559
  -1.000   0.5267   0.02829   0.01870  -0.1282   0.6596   0.1627
  -0.750   0.5579   0.02774   0.01816  -0.1283   0.6545   0.1728
  -0.500   0.5933   0.02701   0.01742  -0.1290   0.6507   0.1866
  -0.250   0.6050   0.02754   0.01811  -0.1268   0.6424   0.1983
   0.000   0.6313   0.02721   0.01791  -0.1263   0.6363   0.2219
   0.250   0.6648   0.02621   0.01723  -0.1267   0.6320   0.2945
   0.500   0.6775   0.02507   0.01767  -0.1237   0.6264   0.6624
   0.750   0.7101   0.02506   0.01807  -0.1236   0.6187   1.0000
   1.000   0.7422   0.02505   0.01776  -0.1239   0.6135   1.0000
   1.250   0.7808   0.02488   0.01725  -0.1251   0.6095   1.0000
   1.500   0.7844   0.02610   0.01852  -0.1218   0.6001   1.0000
   1.750   0.8145   0.02617   0.01839  -0.1219   0.5943   1.0000
   2.000   0.8530   0.02599   0.01794  -0.1231   0.5900   1.0000
   2.250   0.8588   0.02723   0.01924  -0.1202   0.5814   1.0000
   2.500   0.8850   0.02752   0.01941  -0.1198   0.5750   1.0000
   2.750   0.9234   0.02733   0.01899  -0.1210   0.5705   1.0000
   3.000   0.9321   0.02849   0.02018  -0.1185   0.5622   1.0000
   3.250   0.9556   0.02889   0.02050  -0.1177   0.5553   1.0000
   3.500   0.9941   0.02871   0.02010  -0.1190   0.5506   1.0000
   3.750   1.0040   0.02991   0.02134  -0.1166   0.5431   1.0000
   4.000   1.0205   0.03071   0.02212  -0.1151   0.5359   1.0000
   4.250   1.0571   0.03063   0.02189  -0.1161   0.5312   1.0000
   4.500   1.0797   0.03133   0.02252  -0.1155   0.5255   1.0000
   4.750   1.0797   0.03286   0.02416  -0.1119   0.5169   1.0000
   5.000   1.1141   0.03285   0.02401  -0.1126   0.5120   1.0000
   5.250   1.1576   0.03266   0.02363  -0.1147   0.5084   1.0000
   5.500   1.1266   0.03579   0.02705  -0.1075   0.4989   1.0000
   5.750   1.1504   0.03630   0.02752  -0.1070   0.4937   1.0000
   6.000   1.1949   0.03587   0.02694  -0.1090   0.4902   1.0000
   6.250   1.1729   0.03876   0.03000  -0.1032   0.4826   1.0000
   6.500   1.1481   0.04166   0.03302  -0.0972   0.4751   1.0000
   6.750   1.2015   0.04058   0.03181  -0.1000   0.4720   1.0000
   7.000   1.2750   0.03859   0.02958  -0.1052   0.4691   1.0000
   7.250   1.0831   0.05301   0.04458  -0.0858   0.4522   1.0000
   7.500   1.1928   0.04600   0.03734  -0.0903   0.4528   1.0000
   7.750   1.3057   0.04092   0.03196  -0.0984   0.4508   1.0000
   8.000   1.0907   0.05957   0.05116  -0.0815   0.4321   1.0000
   8.250   1.1696   0.05399   0.04545  -0.0827   0.4325   1.0000
   8.500   1.2577   0.04885   0.04015  -0.0857   0.4324   1.0000
   8.750   1.3578   0.04435   0.03542  -0.0917   0.4311   1.0000
   9.000   0.8717   0.10094   0.09298  -0.0807   0.3812   1.0000
   9.250   0.9136   0.09879   0.09078  -0.0796   0.3793   1.0000
   9.500   0.8671   0.10818   0.10027  -0.0805   0.3660   1.0000
   9.750   0.9029   0.10673   0.09878  -0.0794   0.3633   1.0000
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