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NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il)
Reynolds number: 200,000
Max Cl/Cd: 44.09 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20710-il-200000.txt
Download as CSV file: xf-sc20710-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0710 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5937   0.09407   0.09015  -0.0414   1.0000   0.0748
 -10.750  -0.6335   0.08606   0.08214  -0.0477   1.0000   0.0750
 -10.500  -0.6637   0.08219   0.07828  -0.0476   1.0000   0.0750
 -10.250  -0.6925   0.07859   0.07463  -0.0479   1.0000   0.0751
 -10.000  -0.7146   0.07511   0.07097  -0.0487   1.0000   0.0753
  -9.750  -0.7187   0.06734   0.06331  -0.0487   1.0000   0.0767
  -9.500  -0.7046   0.06508   0.06115  -0.0468   1.0000   0.0780
  -9.250  -0.7025   0.06229   0.05834  -0.0461   1.0000   0.0792
  -9.000  -0.7393   0.03497   0.02853  -0.0560   1.0000   0.0441
  -8.750  -0.7175   0.03184   0.02507  -0.0567   1.0000   0.0444
  -8.500  -0.6942   0.02952   0.02253  -0.0572   1.0000   0.0451
  -8.250  -0.6701   0.02787   0.02074  -0.0575   1.0000   0.0463
  -8.000  -0.6451   0.02661   0.01933  -0.0578   1.0000   0.0484
  -7.750  -0.6185   0.02514   0.01758  -0.0581   1.0000   0.0505
  -7.500  -0.5912   0.02395   0.01610  -0.0584   1.0000   0.0521
  -7.250  -0.5654   0.02184   0.01394  -0.0586   1.0000   0.0548
  -7.000  -0.5388   0.02099   0.01307  -0.0588   1.0000   0.0579
  -6.750  -0.5113   0.02041   0.01236  -0.0590   1.0000   0.0622
  -6.500  -0.4832   0.01920   0.01117  -0.0596   1.0000   0.0669
  -6.250  -0.4550   0.01863   0.01059  -0.0600   1.0000   0.0721
  -6.000  -0.4256   0.01782   0.00977  -0.0607   1.0000   0.0780
  -5.750  -0.3962   0.01729   0.00930  -0.0615   1.0000   0.0850
  -5.500  -0.3645   0.01659   0.00862  -0.0628   1.0000   0.0929
  -5.250  -0.3336   0.01618   0.00821  -0.0639   1.0000   0.1030
  -5.000  -0.2963   0.01535   0.00754  -0.0667   1.0000   0.1213
  -4.750  -0.2539   0.01441   0.00695  -0.0708   1.0000   0.1752
  -4.500  -0.1881   0.01241   0.00688  -0.0809   1.0000   0.5642
  -4.250  -0.1652   0.01277   0.00732  -0.0794   1.0000   0.6213
  -4.000  -0.1433   0.01319   0.00774  -0.0778   1.0000   0.6504
  -3.750  -0.1242   0.01370   0.00826  -0.0755   1.0000   0.6699
  -3.500  -0.1061   0.01424   0.00880  -0.0729   1.0000   0.6850
  -3.250  -0.0861   0.01470   0.00923  -0.0709   1.0000   0.6974
  -3.000  -0.0646   0.01512   0.00963  -0.0693   1.0000   0.7089
  -2.750  -0.0508   0.01565   0.01021  -0.0658   1.0000   0.7165
  -2.500  -0.0321   0.01614   0.01070  -0.0635   1.0000   0.7286
  -2.250  -0.0192   0.01669   0.01129  -0.0597   1.0000   0.7382
  -2.000  -0.0047   0.01715   0.01179  -0.0564   1.0000   0.7480
  -1.750   0.0198   0.01748   0.01210  -0.0558   1.0000   0.7589
  -1.500   0.0327   0.01778   0.01245  -0.0523   1.0000   0.7643
  -1.250   0.0609   0.01806   0.01272  -0.0528   1.0000   0.7744
  -1.000   0.0753   0.01826   0.01297  -0.0498   1.0000   0.7789
  -0.750   0.0984   0.01848   0.01322  -0.0492   1.0000   0.7853
  -0.500   0.1297   0.01866   0.01341  -0.0505   0.9992   0.7910
  -0.250   0.1723   0.01879   0.01359  -0.0534   0.9935   0.7945
   0.000   0.2218   0.01880   0.01364  -0.0578   0.9849   0.7984
   0.250   0.2901   0.01838   0.01326  -0.0655   0.9699   0.8018
   0.500   0.3535   0.01763   0.01257  -0.0721   0.9528   0.8052
   0.750   0.4021   0.01682   0.01186  -0.0752   0.9391   0.8070
   1.000   0.4534   0.01591   0.01106  -0.0788   0.9262   0.8091
   1.250   0.4997   0.01488   0.01014  -0.0810   0.9057   0.8116
   1.500   0.5416   0.01401   0.00935  -0.0825   0.8736   0.8141
   1.750   0.5952   0.01350   0.00805  -0.0852   0.6521   0.8161
   2.000   0.6033   0.01571   0.00858  -0.0818   0.3349   0.8197
   2.250   0.6174   0.01727   0.00912  -0.0797   0.1580   0.8221
   2.500   0.6390   0.01800   0.00961  -0.0785   0.1209   0.8244
   2.750   0.6633   0.01862   0.01016  -0.0779   0.1044   0.8270
   3.000   0.6887   0.01935   0.01081  -0.0776   0.0939   0.8301
   3.250   0.7175   0.01998   0.01140  -0.0781   0.0853   0.8335
   3.500   0.7444   0.02073   0.01217  -0.0780   0.0787   0.8364
   3.750   0.7684   0.02122   0.01264  -0.0772   0.0728   0.8387
   4.000   0.7939   0.02220   0.01362  -0.0768   0.0675   0.8411
   4.250   0.8215   0.02286   0.01433  -0.0768   0.0627   0.8437
   4.500   0.8500   0.02430   0.01571  -0.0773   0.0584   0.8463
   4.750   0.8804   0.02521   0.01680  -0.0778   0.0548   0.8490
   5.000   0.9079   0.02604   0.01771  -0.0778   0.0514   0.8513
   5.250   0.9327   0.02722   0.01892  -0.0772   0.0492   0.8538
   5.500   0.9583   0.02966   0.02155  -0.0768   0.0475   0.8566
   5.750   0.9838   0.03128   0.02352  -0.0761   0.0465   0.8597
   6.000   1.0091   0.03344   0.02607  -0.0756   0.0454   0.8627
   6.250   1.0319   0.03561   0.02860  -0.0747   0.0441   0.8656
   6.500   1.0500   0.03785   0.03119  -0.0730   0.0431   0.8683
   6.750   1.0634   0.04181   0.03570  -0.0706   0.0436   0.8709
   7.000   1.0722   0.04674   0.04117  -0.0679   0.0451   0.8735
   7.250   1.0802   0.05164   0.04641  -0.0659   0.0466   0.8760
   8.250   1.0471   0.08575   0.08213  -0.0560   0.0695   0.8842
   8.500   1.0202   0.08876   0.08552  -0.0530   0.0691   0.8869
   8.750   0.9823   0.09279   0.08980  -0.0508   0.0687   0.8897
   9.000   0.9461   0.09955   0.09675  -0.0537   0.0684   0.8922
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