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NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il)
Reynolds number: 100,000
Max Cl/Cd: 28.81 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20614-il-100000.txt
Download as CSV file: xf-sc20614-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0614 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7085   0.07960   0.07334  -0.0618   1.0000   0.1014
 -11.750  -0.7239   0.07444   0.06815  -0.0623   1.0000   0.1005
 -11.500  -0.7526   0.06944   0.06310  -0.0621   1.0000   0.0995
 -11.250  -0.7876   0.06545   0.05903  -0.0599   1.0000   0.0984
 -11.000  -0.8214   0.06157   0.05502  -0.0577   1.0000   0.0974
 -10.750  -0.8444   0.05765   0.05088  -0.0561   1.0000   0.0970
 -10.500  -0.8577   0.05404   0.04701  -0.0545   1.0000   0.0972
 -10.250  -0.8630   0.05063   0.04330  -0.0532   1.0000   0.0978
 -10.000  -0.8621   0.04735   0.03967  -0.0522   1.0000   0.0986
  -9.750  -0.8557   0.04423   0.03615  -0.0515   1.0000   0.0996
  -9.500  -0.8443   0.04138   0.03286  -0.0511   1.0000   0.1008
  -9.250  -0.8292   0.03881   0.02986  -0.0509   1.0000   0.1026
  -9.000  -0.8115   0.03684   0.02796  -0.0502   1.0000   0.1054
  -8.750  -0.7923   0.03551   0.02659  -0.0495   1.0000   0.1087
  -8.500  -0.7719   0.03388   0.02470  -0.0492   1.0000   0.1122
  -8.250  -0.7497   0.03238   0.02280  -0.0491   1.0000   0.1154
  -8.000  -0.7298   0.03083   0.02141  -0.0483   1.0000   0.1196
  -7.750  -0.7077   0.02982   0.02033  -0.0478   1.0000   0.1246
  -7.500  -0.6838   0.02885   0.01908  -0.0477   1.0000   0.1296
  -7.250  -0.6631   0.02761   0.01805  -0.0467   1.0000   0.1351
  -7.000  -0.6395   0.02681   0.01717  -0.0464   1.0000   0.1416
  -6.750  -0.6165   0.02584   0.01624  -0.0458   1.0000   0.1483
  -6.500  -0.5930   0.02513   0.01559  -0.0454   1.0000   0.1563
  -6.250  -0.5696   0.02433   0.01486  -0.0449   1.0000   0.1650
  -6.000  -0.5450   0.02373   0.01428  -0.0447   1.0000   0.1762
  -5.750  -0.5211   0.02299   0.01376  -0.0444   1.0000   0.1896
  -5.500  -0.4955   0.02231   0.01327  -0.0444   1.0000   0.2092
  -5.250  -0.4674   0.02142   0.01277  -0.0453   1.0000   0.2437
  -5.000  -0.4259   0.01943   0.01258  -0.0499   1.0000   0.4443
  -4.750  -0.4175   0.02082   0.01443  -0.0440   1.0000   0.5634
  -4.500  -0.4012   0.02204   0.01559  -0.0406   1.0000   0.6016
  -4.250  -0.3888   0.02327   0.01678  -0.0362   1.0000   0.6221
  -4.000  -0.3771   0.02444   0.01793  -0.0317   1.0000   0.6384
  -3.750  -0.3655   0.02553   0.01898  -0.0273   1.0000   0.6527
  -3.500  -0.3533   0.02650   0.01992  -0.0231   1.0000   0.6667
  -3.250  -0.3392   0.02729   0.02068  -0.0196   1.0000   0.6804
  -3.000  -0.3233   0.02796   0.02131  -0.0168   1.0000   0.6942
  -2.750  -0.3163   0.02868   0.02203  -0.0113   1.0000   0.7036
  -2.500  -0.3043   0.02922   0.02256  -0.0075   1.0000   0.7159
  -2.250  -0.2913   0.02969   0.02302  -0.0040   1.0000   0.7297
  -2.000  -0.2787   0.03012   0.02345  -0.0005   1.0000   0.7445
  -1.750  -0.2642   0.03049   0.02379   0.0023   1.0000   0.7595
  -1.500  -0.2548   0.03069   0.02401   0.0064   1.0000   0.7724
  -1.250  -0.2458   0.03078   0.02411   0.0106   1.0000   0.7860
  -1.000  -0.2342   0.03081   0.02414   0.0139   1.0000   0.8002
  -0.750  -0.2195   0.03079   0.02412   0.0161   1.0000   0.8137
  -0.500  -0.1862   0.03104   0.02433   0.0139   0.9967   0.8240
  -0.250  -0.1503   0.03103   0.02431   0.0120   0.9887   0.8305
   0.000  -0.1030   0.03138   0.02463   0.0074   0.9805   0.8371
   0.250  -0.0602   0.03149   0.02475   0.0032   0.9705   0.8422
   0.500  -0.0261   0.03138   0.02465   0.0015   0.9603   0.8467
   0.750   0.0188   0.03151   0.02480  -0.0026   0.9509   0.8511
   1.000   0.0665   0.03162   0.02493  -0.0073   0.9395   0.8554
   1.250   0.1180   0.03131   0.02466  -0.0117   0.9236   0.8588
   1.500   0.1728   0.03069   0.02409  -0.0160   0.9066   0.8610
   1.750   0.2207   0.03004   0.02351  -0.0193   0.8907   0.8631
   2.000   0.2677   0.02927   0.02282  -0.0221   0.8747   0.8660
   2.250   0.3224   0.02807   0.02171  -0.0256   0.8573   0.8686
   2.500   0.3809   0.02658   0.02033  -0.0293   0.8399   0.8707
   2.750   0.4354   0.02500   0.01887  -0.0321   0.8227   0.8731
   3.000   0.4841   0.02313   0.01712  -0.0332   0.8015   0.8754
   3.250   0.5189   0.02182   0.01588  -0.0326   0.7682   0.8772
   3.500   0.5494   0.02081   0.01489  -0.0314   0.7126   0.8790
   3.750   0.5871   0.02038   0.01342  -0.0306   0.4959   0.8807
   4.000   0.5933   0.02205   0.01385  -0.0272   0.3204   0.8830
   4.250   0.6098   0.02344   0.01453  -0.0260   0.2465   0.8855
   4.500   0.6343   0.02453   0.01526  -0.0261   0.2104   0.8876
   4.750   0.6585   0.02523   0.01583  -0.0258   0.1892   0.8895
   5.000   0.6856   0.02604   0.01649  -0.0260   0.1744   0.8914
   5.250   0.7149   0.02695   0.01720  -0.0267   0.1623   0.8934
   5.500   0.7454   0.02774   0.01808  -0.0275   0.1526   0.8956
   5.750   0.7785   0.02898   0.01915  -0.0290   0.1444   0.8978
   6.000   0.8091   0.02985   0.02017  -0.0298   0.1370   0.9003
   6.250   0.8423   0.03132   0.02144  -0.0314   0.1304   0.9030
   6.500   0.8665   0.03205   0.02246  -0.0308   0.1253   0.9060
   6.750   0.8938   0.03305   0.02353  -0.0310   0.1200   0.9088
   7.000   0.9244   0.03484   0.02524  -0.0322   0.1153   0.9114
   7.250   0.9498   0.03625   0.02706  -0.0321   0.1116   0.9144
   7.500   0.9756   0.03769   0.02869  -0.0322   0.1077   0.9174
   7.750   1.0004   0.03905   0.03002  -0.0323   0.1042   0.9207
   8.000   1.0212   0.04144   0.03271  -0.0319   0.1016   0.9236
   8.250   1.0384   0.04385   0.03562  -0.0307   0.0999   0.9264
   8.500   1.0537   0.04661   0.03883  -0.0297   0.0982   0.9291
   8.750   1.0656   0.04924   0.04184  -0.0282   0.0965   0.9320
   9.000   1.0768   0.05159   0.04445  -0.0267   0.0947   0.9357
   9.250   1.0923   0.05389   0.04689  -0.0261   0.0931   0.9398
   9.500   1.0897   0.05803   0.05152  -0.0236   0.0933   0.9433
   9.750   1.0597   0.06413   0.05834  -0.0191   0.0956   0.9464
  10.000   1.0280   0.06959   0.06424  -0.0154   0.0977   0.9496
  10.250   1.0020   0.07488   0.06982  -0.0134   0.0995   0.9531
  10.500   0.9869   0.08017   0.07527  -0.0131   0.1010   0.9565
  10.750   0.9986   0.08490   0.08002  -0.0135   0.1023   0.9608
  11.000   0.7440   0.13761   0.13341  -0.0529   0.1657   0.9500
  11.250   0.7696   0.14020   0.13604  -0.0510   0.1631   0.9545
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