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USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 35 AIRFOIL (usa35-il)
Reynolds number: 500,000
Max Cl/Cd: 97.69 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35-il-500000.txt
Download as CSV file: xf-usa35-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0077   0.10106   0.09803  -0.0826   0.8377   0.0455
 -10.000   0.0002   0.09846   0.09540  -0.0837   0.8268   0.0462
  -9.750  -0.0278   0.08951   0.08639  -0.0919   0.8183   0.0487
  -9.500  -0.0146   0.08771   0.08456  -0.0915   0.8082   0.0489
  -9.250  -0.0018   0.08603   0.08282  -0.0913   0.7978   0.0491
  -9.000   0.0107   0.08421   0.08099  -0.0915   0.7879   0.0494
  -8.750   0.0215   0.08224   0.07896  -0.0920   0.7774   0.0498
  -8.500   0.0308   0.07988   0.07658  -0.0931   0.7674   0.0504
  -8.250  -0.1918   0.02360   0.01813  -0.1344   0.7663   0.0435
  -8.000  -0.1720   0.02196   0.01608  -0.1339   0.7569   0.0440
  -7.750  -0.1498   0.02054   0.01447  -0.1335   0.7476   0.0444
  -7.500  -0.1248   0.01984   0.01370  -0.1332   0.7372   0.0448
  -7.250  -0.0990   0.01932   0.01310  -0.1330   0.7266   0.0453
  -7.000  -0.0733   0.01881   0.01249  -0.1326   0.7145   0.0458
  -6.750  -0.0475   0.01825   0.01181  -0.1323   0.7022   0.0465
  -6.500  -0.0220   0.01767   0.01104  -0.1319   0.6897   0.0472
  -6.250   0.0040   0.01707   0.01025  -0.1315   0.6763   0.0480
  -6.000   0.0303   0.01665   0.00961  -0.1311   0.6634   0.0487
  -5.500   0.0828   0.01577   0.00864  -0.1306   0.6382   0.0503
  -5.250   0.1096   0.01558   0.00834  -0.1303   0.6271   0.0513
  -5.000   0.1367   0.01530   0.00795  -0.1300   0.6167   0.0525
  -4.750   0.1638   0.01509   0.00756  -0.1297   0.6078   0.0535
  -4.500   0.1907   0.01460   0.00708  -0.1295   0.5995   0.0546
  -4.250   0.2176   0.01444   0.00686  -0.1292   0.5909   0.0557
  -4.000   0.2453   0.01424   0.00661  -0.1291   0.5832   0.0571
  -3.750   0.2729   0.01408   0.00634  -0.1288   0.5759   0.0586
  -3.500   0.2996   0.01381   0.00602  -0.1286   0.5695   0.0601
  -3.250   0.3278   0.01367   0.00590  -0.1285   0.5647   0.0618
  -3.000   0.3560   0.01356   0.00574  -0.1284   0.5598   0.0639
  -2.750   0.3834   0.01332   0.00549  -0.1283   0.5549   0.0658
  -2.500   0.4111   0.01325   0.00538  -0.1281   0.5503   0.0678
  -2.250   0.4394   0.01318   0.00526  -0.1281   0.5466   0.0700
  -2.000   0.4673   0.01295   0.00508  -0.1280   0.5429   0.0725
  -1.750   0.4955   0.01287   0.00500  -0.1280   0.5389   0.0753
  -1.500   0.5234   0.01277   0.00487  -0.1279   0.5348   0.0782
  -1.250   0.5510   0.01271   0.00479  -0.1278   0.5306   0.0812
  -1.000   0.5794   0.01272   0.00476  -0.1278   0.5269   0.0847
  -0.750   0.6074   0.01254   0.00466  -0.1278   0.5238   0.0889
  -0.500   0.6356   0.01247   0.00460  -0.1277   0.5204   0.0934
  -0.250   0.6635   0.01239   0.00455  -0.1277   0.5168   0.0993
   0.000   0.6914   0.01234   0.00451  -0.1276   0.5131   0.1070
   0.250   0.7193   0.01236   0.00452  -0.1276   0.5088   0.1197
   0.500   0.7470   0.01217   0.00454  -0.1276   0.5055   0.1657
   0.750   0.7743   0.01193   0.00460  -0.1276   0.5019   0.2514
   1.000   0.8015   0.01172   0.00466  -0.1276   0.4982   0.3439
   1.250   0.8281   0.01146   0.00477  -0.1276   0.4944   0.4770
   1.500   0.8532   0.01115   0.00492  -0.1272   0.4905   0.6492
   1.750   0.8706   0.01075   0.00515  -0.1245   0.4868   0.8721
   2.000   0.9104   0.01069   0.00519  -0.1267   0.4830   1.0000
   2.250   0.9368   0.01079   0.00524  -0.1263   0.4789   1.0000
   2.500   0.9630   0.01090   0.00530  -0.1260   0.4746   1.0000
   2.750   0.9890   0.01109   0.00538  -0.1256   0.4699   1.0000
   3.000   1.0151   0.01121   0.00548  -0.1253   0.4655   1.0000
   3.250   1.0410   0.01130   0.00556  -0.1249   0.4607   1.0000
   3.500   1.0663   0.01142   0.00563  -0.1244   0.4553   1.0000
   3.750   1.0907   0.01163   0.00574  -0.1238   0.4493   1.0000
   4.000   1.1160   0.01171   0.00585  -0.1233   0.4438   1.0000
   4.250   1.1404   0.01185   0.00595  -0.1227   0.4374   1.0000
   4.500   1.1634   0.01207   0.00609  -0.1218   0.4313   1.0000
   4.750   1.1879   0.01220   0.00623  -0.1212   0.4248   1.0000
   5.000   1.2103   0.01239   0.00637  -0.1203   0.4173   1.0000
   5.250   1.2316   0.01262   0.00655  -0.1192   0.4101   1.0000
   5.500   1.2524   0.01282   0.00674  -0.1179   0.4027   1.0000
   5.750   1.2708   0.01314   0.00698  -0.1163   0.3957   1.0000
   6.000   1.2924   0.01338   0.00722  -0.1153   0.3889   1.0000
   6.250   1.3115   0.01372   0.00751  -0.1139   0.3817   1.0000
   6.500   1.3308   0.01408   0.00782  -0.1126   0.3751   1.0000
   6.750   1.3509   0.01442   0.00815  -0.1115   0.3685   1.0000
   7.000   1.3682   0.01489   0.00855  -0.1100   0.3621   1.0000
   7.250   1.3886   0.01526   0.00892  -0.1090   0.3568   1.0000
   7.500   1.4083   0.01566   0.00931  -0.1079   0.3518   1.0000
   7.750   1.4259   0.01616   0.00977  -0.1066   0.3471   1.0000
   8.000   1.4439   0.01667   0.01026  -0.1053   0.3428   1.0000
   8.250   1.4642   0.01707   0.01069  -0.1045   0.3389   1.0000
   8.500   1.4827   0.01757   0.01119  -0.1034   0.3347   1.0000
   8.750   1.4994   0.01816   0.01175  -0.1021   0.3306   1.0000
   9.000   1.5152   0.01882   0.01239  -0.1007   0.3266   1.0000
   9.250   1.5348   0.01929   0.01291  -0.0999   0.3232   1.0000
   9.500   1.5524   0.01986   0.01350  -0.0989   0.3194   1.0000
   9.750   1.5682   0.02054   0.01418  -0.0977   0.3156   1.0000
  10.000   1.5823   0.02135   0.01496  -0.0963   0.3118   1.0000
  10.250   1.5989   0.02203   0.01567  -0.0953   0.3086   1.0000
  10.500   1.6163   0.02267   0.01637  -0.0944   0.3054   1.0000
  10.750   1.6315   0.02344   0.01718  -0.0933   0.3018   1.0000
  11.000   1.6449   0.02435   0.01807  -0.0921   0.2981   1.0000
  11.250   1.6560   0.02541   0.01911  -0.0907   0.2941   1.0000
  11.500   1.6721   0.02619   0.01998  -0.0899   0.2911   1.0000
  11.750   1.6861   0.02711   0.02096  -0.0890   0.2874   1.0000
  12.000   1.6978   0.02820   0.02206  -0.0878   0.2833   1.0000
  12.250   1.7056   0.02958   0.02342  -0.0864   0.2791   1.0000
  12.500   1.7186   0.03065   0.02458  -0.0856   0.2752   1.0000
  12.750   1.7298   0.03188   0.02586  -0.0846   0.2707   1.0000
  13.000   1.7374   0.03340   0.02739  -0.0835   0.2660   1.0000
  13.250   1.7438   0.03506   0.02906  -0.0823   0.2615   1.0000
  13.500   1.7539   0.03650   0.03059  -0.0816   0.2564   1.0000
  13.750   1.7586   0.03841   0.03251  -0.0805   0.2509   1.0000
  14.000   1.7620   0.04048   0.03461  -0.0795   0.2452   1.0000
  14.250   1.7658   0.04260   0.03678  -0.0787   0.2385   1.0000
  14.500   1.7635   0.04531   0.03948  -0.0776   0.2320   1.0000
  14.750   1.7658   0.04767   0.04190  -0.0769   0.2249   1.0000
  15.000   1.7598   0.05087   0.04508  -0.0759   0.2184   1.0000
  15.250   1.7599   0.05354   0.04781  -0.0753   0.2122   1.0000
  15.500   1.7522   0.05704   0.05130  -0.0745   0.2064   1.0000
  15.750   1.7521   0.05979   0.05410  -0.0740   0.2015   1.0000
  16.000   1.7479   0.06298   0.05732  -0.0734   0.1968   1.0000
  16.250   1.7397   0.06662   0.06095  -0.0729   0.1925   1.0000
  16.500   1.7419   0.06917   0.06357  -0.0726   0.1894   1.0000
  16.750   1.7405   0.07214   0.06659  -0.0723   0.1861   1.0000
  17.000   1.7372   0.07531   0.06977  -0.0720   0.1831   1.0000
  17.250   1.7331   0.07849   0.07294  -0.0716   0.1801   1.0000
  17.500   1.7361   0.08100   0.07554  -0.0715   0.1779   1.0000
  17.750   1.7366   0.08380   0.07841  -0.0715   0.1757   1.0000
  18.000   1.7376   0.08652   0.08117  -0.0714   0.1734   1.0000
  18.250   1.7374   0.08936   0.08404  -0.0714   0.1713   1.0000
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