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USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 41 AIRFOIL (usa41-il)
Reynolds number: 50,000
Max Cl/Cd: 42.19 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa41-il-50000-n5.txt
Download as CSV file: xf-usa41-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 41 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3309   0.10094   0.09423  -0.0252   1.0000   0.1024
  -7.500  -0.3386   0.09993   0.09338  -0.0255   1.0000   0.1048
  -7.250  -0.3464   0.09933   0.09292  -0.0287   1.0000   0.1060
  -7.000  -0.3347   0.09401   0.08764  -0.0250   1.0000   0.1095
  -6.750  -0.3306   0.09131   0.08500  -0.0243   1.0000   0.1136
  -6.500  -0.3308   0.08932   0.08311  -0.0257   1.0000   0.1178
  -6.250  -0.3315   0.08824   0.08212  -0.0316   1.0000   0.1203
  -6.000  -0.3268   0.08464   0.07860  -0.0312   1.0000   0.1212
  -5.750  -0.3220   0.08109   0.07511  -0.0287   1.0000   0.1229
  -5.500  -0.3167   0.07817   0.07223  -0.0283   1.0000   0.1245
  -5.250  -0.3103   0.07533   0.06942  -0.0288   1.0000   0.1265
  -5.000  -0.2789   0.06752   0.06131  -0.0435   1.0000   0.0783
  -4.750  -0.2692   0.06433   0.05811  -0.0427   1.0000   0.0765
  -4.500  -0.2563   0.06089   0.05463  -0.0434   1.0000   0.0749
  -4.250  -0.2385   0.05698   0.05063  -0.0457   1.0000   0.0713
  -3.750  -0.1844   0.04773   0.04083  -0.0545   1.0000   0.0669
  -3.500  -0.1626   0.04510   0.03801  -0.0559   1.0000   0.0702
  -3.250  -0.1295   0.04117   0.03369  -0.0597   0.9984   0.0703
  -3.000  -0.0820   0.03663   0.02853  -0.0658   0.9921   0.0696
  -2.750  -0.0376   0.03338   0.02467  -0.0704   0.9852   0.0723
  -2.500   0.0062   0.03050   0.02099  -0.0743   0.9779   0.0763
  -2.250   0.0468   0.02819   0.01805  -0.0770   0.9697   0.0769
  -2.000   0.0872   0.02644   0.01579  -0.0795   0.9613   0.0781
  -1.750   0.1275   0.02520   0.01428  -0.0820   0.9527   0.0807
  -1.500   0.1648   0.02427   0.01310  -0.0837   0.9420   0.0843
  -1.250   0.2051   0.02351   0.01199  -0.0859   0.9319   0.0912
  -0.750   0.2883   0.02237   0.01084  -0.0909   0.9114   0.1261
  -0.500   0.3277   0.02191   0.01039  -0.0928   0.8994   0.1838
  -0.250   0.3668   0.02130   0.00992  -0.0951   0.8875   0.2664
   0.000   0.4042   0.02048   0.00966  -0.0970   0.8751   0.3721
   0.500   0.4753   0.01904   0.00906  -0.0987   0.8464   1.0000
   0.750   0.5076   0.01909   0.00888  -0.0991   0.8303   1.0000
   1.000   0.5392   0.01913   0.00872  -0.0992   0.8138   1.0000
   1.250   0.5704   0.01916   0.00858  -0.0993   0.7974   1.0000
   1.500   0.6012   0.01919   0.00847  -0.0992   0.7810   1.0000
   1.750   0.6291   0.01930   0.00848  -0.0987   0.7628   1.0000
   2.000   0.6573   0.01942   0.00849  -0.0983   0.7449   1.0000
   2.250   0.6859   0.01954   0.00852  -0.0978   0.7275   1.0000
   2.500   0.7143   0.01969   0.00859  -0.0974   0.7104   1.0000
   2.750   0.7425   0.01987   0.00871  -0.0969   0.6936   1.0000
   3.000   0.7693   0.02012   0.00891  -0.0963   0.6762   1.0000
   3.250   0.7955   0.02041   0.00918  -0.0957   0.6587   1.0000
   3.500   0.8217   0.02073   0.00952  -0.0950   0.6419   1.0000
   3.750   0.8478   0.02107   0.00986  -0.0944   0.6257   1.0000
   4.000   0.8738   0.02144   0.01024  -0.0938   0.6099   1.0000
   4.250   0.8996   0.02184   0.01071  -0.0931   0.5945   1.0000
   4.500   0.9252   0.02226   0.01120  -0.0925   0.5794   1.0000
   4.750   0.9506   0.02273   0.01173  -0.0918   0.5646   1.0000
   5.000   0.9757   0.02322   0.01232  -0.0911   0.5500   1.0000
   5.250   1.0004   0.02375   0.01301  -0.0903   0.5356   1.0000
   5.500   1.0249   0.02430   0.01371  -0.0896   0.5213   1.0000
   5.750   1.0490   0.02489   0.01446  -0.0888   0.5072   1.0000
   6.000   1.0729   0.02550   0.01526  -0.0879   0.4933   1.0000
   6.250   1.0964   0.02614   0.01617  -0.0870   0.4794   1.0000
   6.500   1.1197   0.02681   0.01708  -0.0860   0.4657   1.0000
   6.750   1.1424   0.02747   0.01802  -0.0850   0.4514   1.0000
   7.000   1.1632   0.02792   0.01870  -0.0833   0.4320   1.0000
   7.250   1.1729   0.02780   0.01857  -0.0796   0.3891   1.0000
   7.500   1.1761   0.02805   0.01865  -0.0754   0.3276   1.0000
   7.750   1.1816   0.02901   0.01944  -0.0721   0.2571   1.0000
   8.000   1.1794   0.03130   0.02093  -0.0686   0.1422   1.0000
   8.250   1.1738   0.03470   0.02361  -0.0654   0.0839   1.0000
   8.500   1.1733   0.03739   0.02624  -0.0625   0.0684   1.0000
   8.750   1.1712   0.03985   0.02872  -0.0594   0.0609   1.0000
   9.000   1.1711   0.04212   0.03114  -0.0568   0.0546   1.0000
   9.250   1.1673   0.04477   0.03385  -0.0544   0.0506   1.0000
   9.500   1.1681   0.04722   0.03649  -0.0524   0.0473   1.0000
   9.750   1.1695   0.04978   0.03924  -0.0506   0.0450   1.0000
  10.000   1.1722   0.05236   0.04195  -0.0490   0.0428   1.0000
  10.250   1.1754   0.05505   0.04469  -0.0476   0.0405   1.0000
  10.500   1.1865   0.05742   0.04728  -0.0459   0.0378   1.0000
  10.750   1.2003   0.05980   0.05002  -0.0443   0.0355   1.0000
  11.000   1.2163   0.06244   0.05292  -0.0428   0.0341   1.0000
  11.250   1.2279   0.06557   0.05632  -0.0416   0.0330   1.0000
  11.500   1.2331   0.06900   0.05999  -0.0407   0.0321   1.0000
  11.750   1.2356   0.07280   0.06395  -0.0401   0.0311   1.0000
  12.000   1.2333   0.07715   0.06850  -0.0398   0.0304   1.0000
  12.250   1.2220   0.08170   0.07338  -0.0402   0.0302   1.0000
  12.500   1.2092   0.08669   0.07867  -0.0413   0.0300   1.0000
  12.750   1.1950   0.09215   0.08440  -0.0431   0.0299   1.0000
  13.000   1.1805   0.09802   0.09051  -0.0455   0.0300   1.0000
  13.250   1.1650   0.10439   0.09710  -0.0486   0.0300   1.0000
  13.500   1.1495   0.11118   0.10407  -0.0523   0.0301   1.0000
  13.750   1.1344   0.11831   0.11135  -0.0564   0.0303   1.0000
  14.000   1.1197   0.12583   0.11900  -0.0609   0.0304   1.0000
  14.250   1.0744   0.14410   0.13765  -0.0745   0.0338   1.0000
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