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davissm (davissm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 50,000
Max Cl/Cd: 45.7 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davissm-il-50000-n5.txt
Download as CSV file: xf-davissm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: davissm                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3332   0.12152   0.11454  -0.0336   1.0000   0.0618
  -8.250  -0.3423   0.12106   0.11422  -0.0324   1.0000   0.0620
  -8.000  -0.3484   0.12034   0.11362  -0.0322   1.0000   0.0622
  -7.750  -0.3521   0.11947   0.11284  -0.0330   1.0000   0.0623
  -7.500  -0.3467   0.11360   0.10703  -0.0297   1.0000   0.0631
  -7.250  -0.3417   0.10911   0.10256  -0.0269   1.0000   0.0647
  -7.000  -0.3420   0.10660   0.10011  -0.0254   1.0000   0.0661
  -6.750  -0.3430   0.10445   0.09803  -0.0243   1.0000   0.0676
  -6.500  -0.3435   0.10238   0.09602  -0.0238   1.0000   0.0692
  -6.250  -0.3428   0.10033   0.09403  -0.0239   1.0000   0.0710
  -6.000  -0.3400   0.09833   0.09209  -0.0250   1.0000   0.0732
  -5.750  -0.3310   0.09689   0.09066  -0.0297   1.0000   0.0755
  -5.500  -0.3085   0.09570   0.08942  -0.0395   1.0000   0.0765
  -5.250  -0.3144   0.09080   0.08465  -0.0329   1.0000   0.0780
  -5.000  -0.3115   0.08766   0.08152  -0.0303   1.0000   0.0813
  -4.750  -0.2968   0.08504   0.07889  -0.0333   0.9998   0.0872
  -4.500  -0.2537   0.08068   0.07443  -0.0446   0.9951   0.0926
  -4.250  -0.2303   0.07673   0.07044  -0.0470   0.9906   0.0979
  -3.750  -0.1537   0.06883   0.06233  -0.0621   0.9810   0.1122
  -3.500  -0.1070   0.06487   0.05819  -0.0714   0.9767   0.1231
  -3.250  -0.0700   0.06149   0.05469  -0.0773   0.9715   0.1381
  -3.000  -0.0239   0.05832   0.05136  -0.0854   0.9673   0.1649
  -2.750   0.0089   0.05516   0.04814  -0.0889   0.9626   0.1823
  -2.250   0.1512   0.04471   0.03637  -0.1123   0.9558   0.0733
  -2.000   0.2041   0.04170   0.03284  -0.1190   0.9528   0.0746
  -1.750   0.2453   0.03926   0.03004  -0.1229   0.9477   0.0733
  -1.500   0.2891   0.03701   0.02732  -0.1270   0.9432   0.0718
  -1.250   0.3354   0.03501   0.02479  -0.1311   0.9397   0.0716
  -1.000   0.3750   0.03378   0.02290  -0.1336   0.9342   0.0761
  -0.750   0.4124   0.03249   0.02137  -0.1359   0.9286   0.0791
  -0.500   0.4551   0.03138   0.01992  -0.1390   0.9247   0.0815
  -0.250   0.4883   0.03077   0.01898  -0.1400   0.9175   0.0851
   0.000   0.5275   0.03015   0.01808  -0.1423   0.9121   0.0951
   0.250   0.5639   0.02966   0.01738  -0.1439   0.9060   0.1025
   0.500   0.5994   0.02923   0.01687  -0.1454   0.8990   0.1113
   0.750   0.6432   0.02867   0.01634  -0.1486   0.8948   0.1396
   1.000   0.6737   0.02834   0.01634  -0.1494   0.8854   0.2008
   1.250   0.7064   0.02681   0.01604  -0.1503   0.8788   1.0000
   1.500   0.7359   0.02708   0.01608  -0.1506   0.8691   1.0000
   1.750   0.7646   0.02736   0.01622  -0.1508   0.8593   1.0000
   2.000   0.8014   0.02737   0.01611  -0.1523   0.8525   1.0000
   2.250   0.8269   0.02771   0.01640  -0.1518   0.8412   1.0000
   2.500   0.8551   0.02794   0.01664  -0.1518   0.8308   1.0000
   2.750   0.8915   0.02785   0.01654  -0.1530   0.8235   1.0000
   3.000   0.9164   0.02815   0.01688  -0.1524   0.8114   1.0000
   3.250   0.9425   0.02840   0.01720  -0.1519   0.7999   1.0000
   3.500   0.9709   0.02855   0.01747  -0.1517   0.7891   1.0000
   3.750   1.0053   0.02840   0.01743  -0.1524   0.7805   1.0000
   4.000   1.0301   0.02865   0.01781  -0.1516   0.7678   1.0000
   4.250   1.0555   0.02888   0.01818  -0.1508   0.7551   1.0000
   4.500   1.0816   0.02908   0.01855  -0.1501   0.7425   1.0000
   4.750   1.1083   0.02923   0.01896  -0.1495   0.7298   1.0000
   5.000   1.1368   0.02894   0.01886  -0.1485   0.7133   1.0000
   5.250   1.1637   0.02827   0.01834  -0.1465   0.6885   1.0000
   5.500   1.1883   0.02763   0.01783  -0.1440   0.6577   1.0000
   5.750   1.2119   0.02727   0.01765  -0.1416   0.6251   1.0000
   6.000   1.2318   0.02713   0.01755  -0.1386   0.5819   1.0000
   6.250   1.2477   0.02730   0.01767  -0.1351   0.5259   1.0000
   6.500   1.2559   0.02803   0.01796  -0.1303   0.4298   1.0000
   6.750   1.2502   0.03021   0.01908  -0.1244   0.2707   1.0000
   7.000   1.2369   0.03380   0.02136  -0.1190   0.1355   1.0000
   7.250   1.2365   0.03635   0.02359  -0.1151   0.1090   1.0000
   7.500   1.2383   0.03860   0.02589  -0.1115   0.0973   1.0000
   7.750   1.2411   0.04080   0.02818  -0.1082   0.0881   1.0000
   8.000   1.2454   0.04293   0.03045  -0.1052   0.0798   1.0000
   8.250   1.2497   0.04521   0.03278  -0.1023   0.0736   1.0000
   8.500   1.2633   0.04709   0.03487  -0.1000   0.0687   1.0000
   8.750   1.2817   0.04887   0.03676  -0.0983   0.0618   1.0000
   9.000   1.3211   0.05078   0.03879  -0.0987   0.0556   1.0000
   9.250   1.3679   0.05335   0.04167  -0.1007   0.0501   1.0000
   9.500   1.4015   0.05670   0.04510  -0.1019   0.0455   1.0000
   9.750   1.4243   0.05996   0.04891  -0.1008   0.0436   1.0000
  10.000   1.4403   0.06358   0.05303  -0.0992   0.0424   1.0000
  10.250   1.4484   0.06725   0.05716  -0.0967   0.0416   1.0000
  10.500   1.4491   0.07074   0.06108  -0.0936   0.0407   1.0000
  10.750   1.4441   0.07400   0.06474  -0.0900   0.0397   1.0000
  11.000   1.4357   0.07717   0.06820  -0.0864   0.0387   1.0000
  11.250   1.4266   0.08047   0.07176  -0.0832   0.0378   1.0000
  11.500   1.4192   0.08393   0.07541  -0.0807   0.0369   1.0000
  11.750   1.4071   0.08775   0.07946  -0.0783   0.0363   1.0000
  12.000   1.3923   0.09195   0.08389  -0.0763   0.0360   1.0000
  12.250   1.3754   0.09645   0.08864  -0.0749   0.0358   1.0000
  12.500   1.3555   0.10128   0.09375  -0.0741   0.0359   1.0000
  12.750   1.3343   0.10658   0.09930  -0.0743   0.0359   1.0000
  13.000   1.3105   0.11256   0.10555  -0.0756   0.0362   1.0000
  13.250   1.2681   0.12216   0.11552  -0.0808   0.0378   1.0000
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