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NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il)
Reynolds number: 200,000
Max Cl/Cd: 43.47 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20712-il-200000.txt
Download as CSV file: xf-sc20712-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0712 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7356   0.07449   0.06999  -0.0643   1.0000   0.0535
 -12.500  -0.7446   0.07031   0.06574  -0.0648   1.0000   0.0526
 -12.250  -0.7649   0.06568   0.06105  -0.0652   1.0000   0.0521
 -12.000  -0.7907   0.06166   0.05695  -0.0643   1.0000   0.0517
 -11.750  -0.8195   0.05865   0.05387  -0.0614   1.0000   0.0514
 -11.500  -0.8449   0.05533   0.05043  -0.0591   1.0000   0.0511
 -11.250  -0.8633   0.05134   0.04621  -0.0582   1.0000   0.0507
 -11.000  -0.8743   0.04723   0.04179  -0.0572   1.0000   0.0505
 -10.750  -0.8765   0.04324   0.03743  -0.0567   1.0000   0.0506
 -10.500  -0.8706   0.03965   0.03344  -0.0565   1.0000   0.0511
 -10.250  -0.8584   0.03666   0.03000  -0.0566   1.0000   0.0521
 -10.000  -0.8415   0.03419   0.02705  -0.0570   1.0000   0.0533
  -9.750  -0.8231   0.03197   0.02481  -0.0568   1.0000   0.0547
  -9.500  -0.8024   0.03072   0.02351  -0.0565   1.0000   0.0560
  -9.250  -0.7807   0.02935   0.02200  -0.0563   1.0000   0.0575
  -9.000  -0.7579   0.02795   0.02038  -0.0563   1.0000   0.0592
  -8.750  -0.7334   0.02693   0.01908  -0.0564   1.0000   0.0612
  -8.500  -0.7111   0.02530   0.01744  -0.0561   1.0000   0.0634
  -8.250  -0.6875   0.02450   0.01665  -0.0560   1.0000   0.0657
  -8.000  -0.6627   0.02369   0.01575  -0.0559   1.0000   0.0681
  -7.750  -0.6368   0.02308   0.01498  -0.0560   1.0000   0.0708
  -7.500  -0.6121   0.02192   0.01386  -0.0559   1.0000   0.0740
  -7.250  -0.5865   0.02131   0.01328  -0.0560   1.0000   0.0773
  -7.000  -0.5601   0.02077   0.01268  -0.0561   1.0000   0.0810
  -6.750  -0.5335   0.01995   0.01190  -0.0564   1.0000   0.0854
  -6.500  -0.5062   0.01943   0.01143  -0.0569   1.0000   0.0905
  -6.250  -0.4782   0.01901   0.01095  -0.0573   1.0000   0.0959
  -6.000  -0.4480   0.01829   0.01037  -0.0586   1.0000   0.1041
  -5.750  -0.4167   0.01773   0.00985  -0.0600   1.0000   0.1133
  -5.500  -0.3854   0.01734   0.00950  -0.0614   1.0000   0.1251
  -5.250  -0.3490   0.01668   0.00904  -0.0642   1.0000   0.1458
  -5.000  -0.3055   0.01578   0.00853  -0.0688   1.0000   0.2048
  -4.750  -0.2381   0.01401   0.00850  -0.0792   1.0000   0.5359
  -4.500  -0.2161   0.01447   0.00908  -0.0778   1.0000   0.5916
  -4.250  -0.1936   0.01494   0.00953  -0.0766   1.0000   0.6187
  -4.000  -0.1720   0.01543   0.01000  -0.0752   1.0000   0.6362
  -3.750  -0.1519   0.01595   0.01051  -0.0735   1.0000   0.6496
  -3.500  -0.1359   0.01654   0.01114  -0.0707   1.0000   0.6587
  -3.250  -0.1131   0.01700   0.01156  -0.0698   1.0000   0.6704
  -3.000  -0.0994   0.01762   0.01223  -0.0665   1.0000   0.6766
  -2.750  -0.0691   0.01812   0.01269  -0.0669   0.9976   0.6878
  -2.500  -0.0432   0.01897   0.01361  -0.0653   0.9937   0.6956
  -2.250  -0.0161   0.01958   0.01424  -0.0645   0.9887   0.7069
  -2.000   0.0080   0.02030   0.01500  -0.0626   0.9843   0.7152
  -1.750   0.0381   0.02080   0.01551  -0.0626   0.9806   0.7249
  -1.500   0.0612   0.02115   0.01589  -0.0610   0.9749   0.7308
  -1.250   0.1057   0.02125   0.01596  -0.0651   0.9718   0.7394
  -1.000   0.1322   0.02144   0.01620  -0.0641   0.9661   0.7428
  -0.750   0.1664   0.02149   0.01628  -0.0648   0.9588   0.7480
  -0.500   0.2171   0.02124   0.01602  -0.0695   0.9503   0.7546
  -0.250   0.2744   0.02052   0.01533  -0.0744   0.9410   0.7574
   0.000   0.3114   0.01997   0.01483  -0.0753   0.9291   0.7596
   0.250   0.3589   0.01922   0.01413  -0.0781   0.9193   0.7620
   0.500   0.4130   0.01829   0.01326  -0.0822   0.9111   0.7646
   0.750   0.4568   0.01759   0.01262  -0.0848   0.9011   0.7674
   1.000   0.5113   0.01662   0.01171  -0.0893   0.8915   0.7709
   1.250   0.5473   0.01596   0.01111  -0.0901   0.8739   0.7735
   1.500   0.5765   0.01541   0.01060  -0.0892   0.8489   0.7755
   1.750   0.6076   0.01493   0.01012  -0.0886   0.8078   0.7780
   2.000   0.6408   0.01474   0.00948  -0.0883   0.6840   0.7804
   2.250   0.6501   0.01630   0.00964  -0.0844   0.4323   0.7830
   2.500   0.6650   0.01788   0.01020  -0.0829   0.2490   0.7858
   2.750   0.6899   0.01893   0.01071  -0.0831   0.1699   0.7888
   3.000   0.7094   0.01951   0.01112  -0.0815   0.1424   0.7908
   3.250   0.7312   0.02012   0.01160  -0.0803   0.1253   0.7930
   3.500   0.7561   0.02064   0.01209  -0.0799   0.1128   0.7953
   3.750   0.7820   0.02127   0.01269  -0.0797   0.1030   0.7980
   4.000   0.8088   0.02215   0.01342  -0.0800   0.0948   0.8011
   4.250   0.8407   0.02268   0.01401  -0.0811   0.0887   0.8041
   4.500   0.8634   0.02331   0.01457  -0.0801   0.0836   0.8058
   4.750   0.8882   0.02407   0.01538  -0.0795   0.0794   0.8077
   5.000   0.9144   0.02471   0.01606  -0.0791   0.0756   0.8100
   5.250   0.9415   0.02563   0.01689  -0.0793   0.0721   0.8124
   5.500   0.9705   0.02663   0.01800  -0.0797   0.0689   0.8150
   5.750   1.0009   0.02753   0.01899  -0.0804   0.0660   0.8178
   6.000   1.0286   0.02838   0.01983  -0.0806   0.0634   0.8203
   6.250   1.0536   0.02997   0.02142  -0.0802   0.0609   0.8226
   6.500   1.0772   0.03078   0.02249  -0.0792   0.0589   0.8253
   6.750   1.1028   0.03201   0.02391  -0.0789   0.0570   0.8281
   7.000   1.1292   0.03324   0.02524  -0.0789   0.0553   0.8309
   7.250   1.1569   0.03470   0.02669  -0.0795   0.0536   0.8338
   7.500   1.1774   0.03690   0.02918  -0.0785   0.0521   0.8364
   7.750   1.1938   0.03859   0.03129  -0.0764   0.0508   0.8390
   8.000   1.2099   0.04091   0.03398  -0.0746   0.0497   0.8420
   8.250   1.2244   0.04361   0.03704  -0.0728   0.0490   0.8452
   8.500   1.2362   0.04676   0.04057  -0.0709   0.0484   0.8482
   8.750   1.2404   0.05058   0.04484  -0.0681   0.0482   0.8506
   9.000   1.2344   0.05510   0.04987  -0.0641   0.0484   0.8527
   9.250   1.2189   0.06038   0.05565  -0.0596   0.0488   0.8548
   9.500   1.1927   0.06618   0.06190  -0.0547   0.0497   0.8569
   9.750   1.1637   0.07075   0.06676  -0.0499   0.0503   0.8594
  10.000   1.1377   0.07565   0.07189  -0.0470   0.0509   0.8617
  10.250   1.1141   0.08082   0.07724  -0.0458   0.0515   0.8638
  10.500   1.0948   0.08587   0.08242  -0.0456   0.0519   0.8657
  10.750   1.0845   0.09067   0.08729  -0.0459   0.0523   0.8677
  11.000   0.9436   0.08985   0.08659  -0.0308   0.0526   0.8621
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