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USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: USA 5 AIRFOIL (usa5-il)
Reynolds number: 50,000
Max Cl/Cd: 38.87 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa5-il-50000.txt
Download as CSV file: xf-usa5-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 5 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3453   0.11013   0.10340  -0.0216   1.0000   0.1148
  -8.250  -0.3508   0.10920   0.10259  -0.0226   1.0000   0.1177
  -8.000  -0.3616   0.10903   0.10257  -0.0233   1.0000   0.1187
  -7.750  -0.3454   0.10275   0.09625  -0.0218   1.0000   0.1228
  -7.500  -0.3438   0.10012   0.09370  -0.0210   1.0000   0.1271
  -7.250  -0.3510   0.09882   0.09253  -0.0208   1.0000   0.1304
  -7.000  -0.3601   0.09866   0.09250  -0.0234   1.0000   0.1324
  -6.750  -0.3523   0.09373   0.08764  -0.0212   1.0000   0.1353
  -6.500  -0.3478   0.09048   0.08445  -0.0199   1.0000   0.1403
  -6.250  -0.3500   0.08905   0.08310  -0.0214   1.0000   0.1451
  -6.000  -0.3504   0.08716   0.08128  -0.0235   1.0000   0.1475
  -5.750  -0.3439   0.08279   0.07697  -0.0199   1.0000   0.1525
  -5.500  -0.3414   0.08115   0.07535  -0.0217   1.0000   0.1593
  -5.000  -0.3321   0.07494   0.06924  -0.0200   1.0000   0.1706
  -4.750  -0.3258   0.07229   0.06659  -0.0211   1.0000   0.1771
  -4.500  -0.3147   0.07092   0.06512  -0.0240   1.0000   0.1885
  -4.250  -0.3115   0.06650   0.06084  -0.0198   1.0000   0.1944
  -4.000  -0.3023   0.06371   0.05803  -0.0200   1.0000   0.2064
  -3.750  -0.2939   0.06093   0.05525  -0.0192   1.0000   0.2226
  -3.500  -0.2848   0.05831   0.05261  -0.0189   1.0000   0.2463
  -3.250  -0.2778   0.05556   0.04985  -0.0172   1.0000   0.2746
  -3.000  -0.2716   0.05289   0.04722  -0.0147   1.0000   0.3053
  -2.750  -0.2678   0.05025   0.04466  -0.0115   1.0000   0.3481
  -2.500  -0.2679   0.04754   0.04207  -0.0068   1.0000   0.4025
  -2.250  -0.2666   0.04484   0.03945  -0.0023   1.0000   0.4557
  -2.000  -0.2626   0.04207   0.03676   0.0020   1.0000   0.4996
  -1.750  -0.2515   0.03956   0.03425   0.0042   1.0000   0.5358
  -1.500  -0.2370   0.03707   0.03174   0.0055   1.0000   0.5674
  -1.250  -0.2009   0.03477   0.02920   0.0008   1.0000   0.5582
  -1.000  -0.0493   0.03413   0.02540  -0.0271   1.0000   0.1734
  -0.750  -0.0294   0.03254   0.02361  -0.0264   1.0000   0.1801
  -0.500  -0.0066   0.03120   0.02188  -0.0257   1.0000   0.1815
  -0.250   0.0171   0.03006   0.02030  -0.0252   1.0000   0.1838
   0.000   0.0372   0.02945   0.01934  -0.0245   1.0000   0.2018
   0.250   0.0861   0.02841   0.01793  -0.0290   0.9909   0.2216
   0.500   0.1626   0.02759   0.01680  -0.0384   0.9741   0.2815
   0.750   0.2341   0.02706   0.01643  -0.0471   0.9559   0.3486
   1.000   0.3261   0.02520   0.01587  -0.0596   0.9377   1.0000
   1.250   0.3897   0.02567   0.01574  -0.0661   0.9141   1.0000
   1.500   0.4447   0.02587   0.01566  -0.0710   0.8882   1.0000
   1.750   0.4984   0.02588   0.01551  -0.0755   0.8629   1.0000
   2.000   0.5542   0.02564   0.01518  -0.0799   0.8392   1.0000
   2.250   0.6076   0.02523   0.01472  -0.0834   0.8179   1.0000
   2.500   0.6457   0.02516   0.01465  -0.0844   0.7940   1.0000
   2.750   0.6901   0.02482   0.01427  -0.0860   0.7746   1.0000
   3.000   0.7184   0.02507   0.01452  -0.0854   0.7522   1.0000
   3.250   0.7545   0.02497   0.01440  -0.0857   0.7341   1.0000
   3.500   0.7789   0.02539   0.01489  -0.0845   0.7133   1.0000
   3.750   0.8083   0.02552   0.01502  -0.0838   0.6948   1.0000
   4.000   0.8368   0.02566   0.01516  -0.0828   0.6764   1.0000
   4.250   0.8592   0.02610   0.01564  -0.0812   0.6563   1.0000
   4.500   0.8861   0.02631   0.01587  -0.0799   0.6381   1.0000
   4.750   0.9116   0.02671   0.01638  -0.0787   0.6210   1.0000
   5.000   0.9327   0.02749   0.01729  -0.0774   0.6048   1.0000
   5.250   0.9546   0.02828   0.01822  -0.0761   0.5891   1.0000
   5.500   0.9765   0.02906   0.01914  -0.0748   0.5730   1.0000
   5.750   0.9992   0.02975   0.01999  -0.0734   0.5564   1.0000
   6.000   1.0237   0.03035   0.02080  -0.0721   0.5395   1.0000
   6.250   1.0436   0.03075   0.02134  -0.0698   0.5159   1.0000
   6.500   1.0694   0.02967   0.02008  -0.0667   0.4818   1.0000
   6.750   1.0902   0.02962   0.02005  -0.0642   0.4544   1.0000
   7.000   1.1085   0.02978   0.02032  -0.0617   0.4278   1.0000
   7.250   1.1254   0.03013   0.02093  -0.0591   0.4031   1.0000
   7.500   1.1398   0.02984   0.02068  -0.0557   0.3723   1.0000
   7.750   1.1456   0.02955   0.02053  -0.0513   0.3361   1.0000
   8.000   1.1448   0.02945   0.02049  -0.0461   0.2880   1.0000
   8.250   1.1412   0.03022   0.02101  -0.0411   0.2000   1.0000
   8.500   1.1344   0.03299   0.02301  -0.0367   0.1283   1.0000
   8.750   1.1336   0.03556   0.02522  -0.0333   0.0997   1.0000
   9.000   1.1327   0.03787   0.02744  -0.0298   0.0897   1.0000
   9.250   1.1318   0.04012   0.02970  -0.0264   0.0839   1.0000
   9.500   1.1325   0.04238   0.03201  -0.0234   0.0789   1.0000
   9.750   1.1353   0.04485   0.03446  -0.0208   0.0742   1.0000
  10.000   1.1460   0.04709   0.03692  -0.0186   0.0692   1.0000
  10.250   1.1693   0.04950   0.03951  -0.0171   0.0660   1.0000
  10.500   1.2260   0.05416   0.04432  -0.0190   0.0637   1.0000
  10.750   1.2473   0.05831   0.04887  -0.0182   0.0637   1.0000
  11.000   1.2523   0.06201   0.05302  -0.0160   0.0640   1.0000
  11.250   1.2461   0.06530   0.05674  -0.0130   0.0646   1.0000
  11.500   1.2330   0.06871   0.06054  -0.0101   0.0653   1.0000
  11.750   1.2135   0.07262   0.06482  -0.0079   0.0660   1.0000
  12.000   1.1895   0.07690   0.06941  -0.0070   0.0666   1.0000
  12.250   1.1621   0.08218   0.07497  -0.0077   0.0672   1.0000
  12.500   1.1339   0.08825   0.08128  -0.0100   0.0679   1.0000
  12.750   1.1025   0.09577   0.08898  -0.0143   0.0687   1.0000
  13.000   1.0691   0.10492   0.09826  -0.0203   0.0697   1.0000
  13.250   1.0373   0.11549   0.10889  -0.0273   0.0712   1.0000
  13.500   1.0131   0.12590   0.11928  -0.0335   0.0729   1.0000
  13.750   1.0010   0.13409   0.12744  -0.0374   0.0743   1.0000
  14.000   0.9979   0.14043   0.13376  -0.0394   0.0754   1.0000
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