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SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)
Reynolds number: 200,000
Max Cl/Cd: 36.57 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nasasc2-0714-il-200000.txt
Download as CSV file: xf-nasasc2-0714-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SC(2)-0714 Supercritical airfoil (coordinates fr
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6348   0.09803   0.09364  -0.0545   1.0000   0.0646
 -13.250  -0.9228   0.06067   0.05512  -0.0687   1.0000   0.0550
 -13.000  -0.9511   0.05816   0.05248  -0.0650   1.0000   0.0550
 -12.750  -0.9790   0.05600   0.05020  -0.0606   1.0000   0.0550
 -12.500  -0.9982   0.05250   0.04652  -0.0585   1.0000   0.0552
 -12.250  -1.0046   0.04921   0.04309  -0.0570   1.0000   0.0557
 -12.000  -1.0011   0.04704   0.04086  -0.0558   1.0000   0.0563
 -11.750  -0.9936   0.04536   0.03913  -0.0547   1.0000   0.0570
 -11.500  -0.9850   0.04368   0.03736  -0.0536   1.0000   0.0577
 -11.250  -0.9767   0.04166   0.03518  -0.0527   1.0000   0.0585
 -11.000  -0.9663   0.03957   0.03288  -0.0521   1.0000   0.0593
 -10.750  -0.9534   0.03754   0.03061  -0.0516   1.0000   0.0604
 -10.500  -0.9379   0.03570   0.02849  -0.0514   1.0000   0.0618
 -10.250  -0.9196   0.03422   0.02667  -0.0516   1.0000   0.0631
 -10.000  -0.9015   0.03210   0.02445  -0.0510   1.0000   0.0645
  -9.750  -0.8812   0.03100   0.02336  -0.0505   1.0000   0.0659
  -9.500  -0.8597   0.03002   0.02232  -0.0503   1.0000   0.0674
  -9.250  -0.8376   0.02909   0.02129  -0.0501   1.0000   0.0692
  -9.000  -0.8144   0.02822   0.02027  -0.0500   1.0000   0.0713
  -8.750  -0.7901   0.02744   0.01930  -0.0501   1.0000   0.0730
  -8.500  -0.7695   0.02615   0.01809  -0.0491   1.0000   0.0751
  -8.250  -0.7464   0.02548   0.01744  -0.0488   1.0000   0.0771
  -8.000  -0.7224   0.02488   0.01681  -0.0487   1.0000   0.0797
  -7.750  -0.6975   0.02435   0.01619  -0.0487   1.0000   0.0825
  -7.500  -0.6743   0.02356   0.01538  -0.0482   1.0000   0.0851
  -7.250  -0.6503   0.02294   0.01486  -0.0480   1.0000   0.0881
  -7.000  -0.6250   0.02248   0.01440  -0.0481   1.0000   0.0916
  -6.750  -0.5985   0.02213   0.01397  -0.0484   1.0000   0.0954
  -6.500  -0.5728   0.02139   0.01338  -0.0486   1.0000   0.1004
  -6.250  -0.5451   0.02099   0.01301  -0.0493   1.0000   0.1060
  -6.000  -0.5157   0.02041   0.01251  -0.0504   1.0000   0.1132
  -5.750  -0.4856   0.02004   0.01216  -0.0516   1.0000   0.1229
  -5.500  -0.4517   0.01945   0.01170  -0.0540   1.0000   0.1376
  -5.250  -0.4134   0.01877   0.01125  -0.0575   1.0000   0.1617
  -5.000  -0.3667   0.01787   0.01076  -0.0631   1.0000   0.2236
  -4.750  -0.3001   0.01642   0.01111  -0.0734   1.0000   0.5237
  -4.500  -0.2781   0.01698   0.01173  -0.0721   1.0000   0.5799
  -4.250  -0.2584   0.01760   0.01235  -0.0703   1.0000   0.6025
  -4.000  -0.2385   0.01824   0.01296  -0.0686   1.0000   0.6187
  -3.750  -0.2075   0.01898   0.01365  -0.0689   0.9971   0.6336
  -3.500  -0.1829   0.02017   0.01490  -0.0668   0.9932   0.6407
  -3.250  -0.1552   0.02090   0.01560  -0.0662   0.9887   0.6523
  -3.000  -0.1342   0.02196   0.01671  -0.0634   0.9840   0.6574
  -2.750  -0.0942   0.02256   0.01725  -0.0658   0.9814   0.6685
  -2.500  -0.0764   0.02316   0.01789  -0.0627   0.9743   0.6715
  -2.250  -0.0501   0.02394   0.01868  -0.0612   0.9698   0.6763
  -2.000  -0.0198   0.02447   0.01920  -0.0613   0.9645   0.6873
  -1.750  -0.0049   0.02532   0.02012  -0.0565   0.9569   0.6931
  -1.500   0.0309   0.02587   0.02067  -0.0571   0.9521   0.7051
  -1.250   0.0461   0.02615   0.02100  -0.0533   0.9434   0.7100
  -1.000   0.0993   0.02616   0.02096  -0.0595   0.9403   0.7203
  -0.750   0.1201   0.02609   0.02094  -0.0571   0.9324   0.7227
  -0.500   0.1544   0.02587   0.02074  -0.0577   0.9261   0.7253
  -0.250   0.2009   0.02554   0.02043  -0.0608   0.9226   0.7283
   0.000   0.2359   0.02504   0.01994  -0.0621   0.9108   0.7324
   0.250   0.3039   0.02384   0.01873  -0.0697   0.8996   0.7378
   0.500   0.3444   0.02291   0.01786  -0.0703   0.8925   0.7400
   0.750   0.3737   0.02235   0.01736  -0.0694   0.8828   0.7430
   1.000   0.4262   0.02116   0.01621  -0.0727   0.8757   0.7457
   1.250   0.4663   0.02026   0.01537  -0.0744   0.8628   0.7480
   1.500   0.5093   0.01944   0.01459  -0.0769   0.8494   0.7506
   1.750   0.5561   0.01876   0.01394  -0.0807   0.8291   0.7541
   2.000   0.5932   0.01804   0.01322  -0.0816   0.7980   0.7559
   2.250   0.6362   0.01741   0.01235  -0.0832   0.7200   0.7572
   2.500   0.6575   0.01798   0.01203  -0.0810   0.5570   0.7587
   2.750   0.6637   0.01909   0.01232  -0.0770   0.4104   0.7603
   3.000   0.6744   0.02021   0.01273  -0.0744   0.2804   0.7619
   3.250   0.6924   0.02115   0.01315  -0.0732   0.1990   0.7636
   3.500   0.7154   0.02186   0.01358  -0.0729   0.1598   0.7653
   3.750   0.7408   0.02253   0.01406  -0.0730   0.1390   0.7674
   4.000   0.7713   0.02313   0.01458  -0.0743   0.1255   0.7702
   4.250   0.8001   0.02373   0.01511  -0.0751   0.1163   0.7721
   4.500   0.8213   0.02413   0.01546  -0.0738   0.1098   0.7734
   4.750   0.8431   0.02472   0.01604  -0.0727   0.1045   0.7750
   5.000   0.8669   0.02513   0.01647  -0.0720   0.0994   0.7769
   5.250   0.8923   0.02595   0.01718  -0.0719   0.0945   0.7788
   5.500   0.9202   0.02651   0.01781  -0.0721   0.0908   0.7808
   5.750   0.9490   0.02708   0.01840  -0.0726   0.0868   0.7826
   6.000   0.9795   0.02795   0.01917  -0.0737   0.0831   0.7840
   6.250   1.0112   0.02883   0.02012  -0.0748   0.0799   0.7854
   6.500   1.0432   0.02963   0.02099  -0.0761   0.0768   0.7869
   6.750   1.0729   0.03040   0.02175  -0.0769   0.0743   0.7882
   7.000   1.1019   0.03195   0.02322  -0.0774   0.0716   0.7894
   7.250   1.1246   0.03255   0.02405  -0.0765   0.0697   0.7906
   7.500   1.1492   0.03346   0.02510  -0.0760   0.0676   0.7920
   7.750   1.1744   0.03449   0.02623  -0.0758   0.0658   0.7935
   8.000   1.1998   0.03557   0.02735  -0.0757   0.0643   0.7955
   8.250   1.2284   0.03755   0.02932  -0.0765   0.0626   0.7976
   8.500   1.2496   0.03922   0.03130  -0.0758   0.0613   0.7996
   8.750   1.2698   0.04079   0.03318  -0.0749   0.0599   0.8014
   9.000   1.2904   0.04267   0.03532  -0.0744   0.0586   0.8031
   9.250   1.3061   0.04450   0.03739  -0.0729   0.0576   0.8044
   9.500   1.3199   0.04626   0.03935  -0.0710   0.0568   0.8058
   9.750   1.3347   0.04800   0.04123  -0.0695   0.0560   0.8073
  10.000   1.3483   0.04990   0.04325  -0.0679   0.0553   0.8089
  10.250   1.3604   0.05236   0.04584  -0.0665   0.0546   0.8106
  10.500   1.3625   0.05672   0.05046  -0.0644   0.0540   0.8122
  10.750   1.3518   0.05936   0.05349  -0.0599   0.0537   0.8138
  11.000   1.3340   0.06212   0.05659  -0.0548   0.0535   0.8154
  11.250   1.3133   0.06553   0.06033  -0.0502   0.0533   0.8171
  11.500   1.2909   0.06962   0.06471  -0.0467   0.0533   0.8187
  11.750   1.2650   0.07409   0.06947  -0.0437   0.0533   0.8199
  12.000   1.2378   0.07906   0.07469  -0.0418   0.0535   0.8209
  12.250   1.2116   0.08465   0.08049  -0.0412   0.0536   0.8218
  12.500   1.1886   0.09084   0.08685  -0.0417   0.0539   0.8228
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