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NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il)
Reynolds number: 500,000
Max Cl/Cd: 62.65 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20610-il-500000-n5.txt
Download as CSV file: xf-sc20610-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0610 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.9850   0.07857   0.07535  -0.0396   1.0000   0.0133
 -15.500  -1.0245   0.06591   0.06240  -0.0485   1.0000   0.0132
 -15.250  -1.0453   0.05840   0.05469  -0.0535   1.0000   0.0132
 -15.000  -1.0595   0.05280   0.04891  -0.0568   1.0000   0.0133
 -14.750  -1.0691   0.04839   0.04434  -0.0589   1.0000   0.0133
 -14.500  -1.0753   0.04474   0.04054  -0.0603   1.0000   0.0134
 -14.250  -1.0789   0.04163   0.03728  -0.0610   1.0000   0.0135
 -14.000  -1.0806   0.03893   0.03444  -0.0613   1.0000   0.0136
 -13.750  -1.0808   0.03659   0.03196  -0.0611   1.0000   0.0137
 -13.500  -1.0805   0.03455   0.02980  -0.0603   1.0000   0.0138
 -13.250  -1.0811   0.03280   0.02793  -0.0588   1.0000   0.0139
 -13.000  -1.0837   0.03129   0.02631  -0.0564   1.0000   0.0140
 -12.750  -1.0780   0.02974   0.02464  -0.0554   1.0000   0.0142
 -12.500  -1.0686   0.02829   0.02307  -0.0548   1.0000   0.0144
 -12.250  -1.0562   0.02694   0.02158  -0.0544   1.0000   0.0145
 -12.000  -1.0414   0.02571   0.02021  -0.0541   1.0000   0.0148
 -11.750  -1.0250   0.02459   0.01897  -0.0537   1.0000   0.0150
 -11.500  -1.0072   0.02358   0.01784  -0.0532   1.0000   0.0152
 -11.250  -0.9880   0.02270   0.01684  -0.0528   1.0000   0.0154
 -11.000  -0.9688   0.02162   0.01569  -0.0526   1.0000   0.0157
 -10.750  -0.9481   0.02074   0.01475  -0.0525   1.0000   0.0161
 -10.500  -0.9261   0.02001   0.01397  -0.0524   1.0000   0.0165
 -10.250  -0.9035   0.01933   0.01322  -0.0523   1.0000   0.0168
 -10.000  -0.8753   0.01862   0.01244  -0.0533   0.9994   0.0173
  -9.750  -0.8448   0.01792   0.01167  -0.0547   0.9985   0.0178
  -9.500  -0.8139   0.01726   0.01094  -0.0562   0.9975   0.0183
  -9.250  -0.7825   0.01665   0.01025  -0.0576   0.9965   0.0188
  -9.000  -0.7509   0.01600   0.00955  -0.0592   0.9956   0.0195
  -8.750  -0.7191   0.01543   0.00896  -0.0607   0.9948   0.0204
  -8.500  -0.6869   0.01496   0.00846  -0.0623   0.9941   0.0214
  -8.250  -0.6557   0.01451   0.00796  -0.0635   0.9930   0.0226
  -8.000  -0.6242   0.01406   0.00748  -0.0648   0.9916   0.0240
  -7.750  -0.5926   0.01365   0.00708  -0.0661   0.9904   0.0259
  -7.500  -0.5607   0.01330   0.00670  -0.0674   0.9891   0.0279
  -7.250  -0.5284   0.01291   0.00631  -0.0688   0.9880   0.0302
  -7.000  -0.4958   0.01259   0.00599  -0.0702   0.9870   0.0328
  -6.750  -0.4628   0.01229   0.00567  -0.0716   0.9860   0.0354
  -6.500  -0.4294   0.01197   0.00537  -0.0732   0.9851   0.0387
  -6.250  -0.3959   0.01173   0.00511  -0.0747   0.9843   0.0420
  -6.000  -0.3620   0.01142   0.00485  -0.0764   0.9836   0.0467
  -5.750  -0.3313   0.01121   0.00463  -0.0772   0.9818   0.0507
  -5.500  -0.2996   0.01093   0.00439  -0.0784   0.9800   0.0568
  -5.250  -0.2674   0.01070   0.00418  -0.0796   0.9784   0.0629
  -5.000  -0.2343   0.01045   0.00397  -0.0810   0.9771   0.0712
  -4.750  -0.2005   0.01020   0.00378  -0.0825   0.9759   0.0822
  -4.500  -0.1664   0.00995   0.00360  -0.0841   0.9748   0.0979
  -4.250  -0.1316   0.00965   0.00341  -0.0860   0.9740   0.1217
  -4.000  -0.0963   0.00930   0.00324  -0.0880   0.9733   0.1623
  -3.750  -0.0600   0.00887   0.00306  -0.0904   0.9728   0.2233
  -3.500  -0.0221   0.00831   0.00285  -0.0933   0.9724   0.3150
  -3.250   0.0175   0.00763   0.00263  -0.0966   0.9721   0.4380
  -3.000   0.0556   0.00717   0.00260  -0.0993   0.9717   0.5512
  -2.750   0.0867   0.00710   0.00264  -0.1000   0.9689   0.5913
  -2.500   0.1180   0.00708   0.00266  -0.1007   0.9658   0.6126
  -2.250   0.1512   0.00703   0.00268  -0.1016   0.9626   0.6351
  -2.000   0.1882   0.00692   0.00259  -0.1033   0.9580   0.6482
  -1.750   0.2197   0.00684   0.00250  -0.1038   0.9476   0.6579
  -1.500   0.2516   0.00678   0.00248  -0.1043   0.9382   0.6649
  -1.250   0.2830   0.00675   0.00241  -0.1047   0.9246   0.6727
  -1.000   0.3122   0.00672   0.00237  -0.1045   0.9014   0.6783
  -0.750   0.3402   0.00677   0.00233  -0.1040   0.8678   0.6828
  -0.500   0.3675   0.00689   0.00229  -0.1035   0.8215   0.6872
  -0.250   0.3924   0.00723   0.00228  -0.1024   0.7373   0.6907
   0.000   0.4120   0.00818   0.00248  -0.1006   0.5679   0.6932
   0.250   0.4348   0.00903   0.00272  -0.0997   0.4229   0.6952
   0.500   0.4598   0.00967   0.00293  -0.0993   0.3178   0.6975
   0.750   0.4860   0.01019   0.00311  -0.0991   0.2370   0.6999
   1.000   0.5126   0.01064   0.00329  -0.0990   0.1743   0.7025
   1.250   0.5400   0.01101   0.00346  -0.0990   0.1311   0.7050
   1.500   0.5673   0.01129   0.00365  -0.0989   0.1071   0.7069
   1.750   0.5946   0.01156   0.00384  -0.0987   0.0877   0.7088
   2.000   0.6222   0.01180   0.00404  -0.0986   0.0758   0.7106
   2.250   0.6498   0.01205   0.00424  -0.0985   0.0669   0.7126
   2.500   0.6772   0.01232   0.00447  -0.0984   0.0591   0.7147
   2.750   0.7049   0.01254   0.00469  -0.0984   0.0538   0.7173
   3.000   0.7323   0.01283   0.00493  -0.0982   0.0484   0.7199
   3.250   0.7602   0.01305   0.00517  -0.0982   0.0451   0.7221
   3.500   0.7871   0.01332   0.00542  -0.0980   0.0410   0.7238
   3.750   0.8141   0.01358   0.00571  -0.0977   0.0379   0.7255
   4.000   0.8410   0.01386   0.00599  -0.0975   0.0349   0.7274
   4.250   0.8677   0.01419   0.00632  -0.0972   0.0323   0.7294
   4.500   0.8946   0.01448   0.00664  -0.0970   0.0300   0.7315
   4.750   0.9211   0.01483   0.00698  -0.0967   0.0278   0.7337
   5.000   0.9476   0.01520   0.00738  -0.0964   0.0261   0.7361
   5.250   0.9741   0.01557   0.00777  -0.0961   0.0245   0.7386
   5.500   0.9999   0.01596   0.00818  -0.0957   0.0230   0.7405
   5.750   1.0253   0.01641   0.00868  -0.0952   0.0218   0.7424
   6.000   1.0509   0.01682   0.00915  -0.0947   0.0207   0.7443
   6.250   1.0763   0.01726   0.00963  -0.0942   0.0198   0.7465
   6.500   1.1015   0.01773   0.01014  -0.0937   0.0191   0.7487
   6.750   1.1260   0.01830   0.01074  -0.0931   0.0184   0.7511
   7.000   1.1502   0.01893   0.01142  -0.0924   0.0179   0.7534
   7.250   1.1747   0.01950   0.01207  -0.0918   0.0174   0.7557
   7.500   1.1983   0.02011   0.01277  -0.0911   0.0170   0.7575
   7.750   1.2217   0.02075   0.01351  -0.0902   0.0166   0.7594
   8.000   1.2448   0.02141   0.01427  -0.0894   0.0163   0.7616
   8.250   1.2677   0.02210   0.01504  -0.0886   0.0159   0.7639
   8.500   1.2902   0.02282   0.01584  -0.0877   0.0156   0.7663
   8.750   1.3122   0.02357   0.01668  -0.0867   0.0153   0.7688
   9.000   1.3336   0.02438   0.01755  -0.0858   0.0150   0.7712
   9.250   1.3532   0.02535   0.01862  -0.0845   0.0147   0.7731
   9.500   1.3718   0.02645   0.01984  -0.0831   0.0144   0.7751
   9.750   1.3913   0.02737   0.02093  -0.0818   0.0142   0.7774
  10.000   1.4095   0.02841   0.02213  -0.0803   0.0140   0.7799
  10.250   1.4266   0.02955   0.02343  -0.0787   0.0138   0.7825
  10.500   1.4425   0.03078   0.02482  -0.0770   0.0136   0.7851
  10.750   1.4570   0.03208   0.02629  -0.0751   0.0134   0.7874
  11.000   1.4694   0.03345   0.02785  -0.0730   0.0133   0.7894
  11.250   1.4799   0.03491   0.02950  -0.0706   0.0131   0.7916
  11.500   1.4882   0.03643   0.03121  -0.0680   0.0130   0.7941
  11.750   1.4926   0.03803   0.03299  -0.0649   0.0128   0.7969
  12.000   1.4913   0.03963   0.03475  -0.0609   0.0127   0.7998
  12.250   1.4898   0.04152   0.03681  -0.0575   0.0126   0.8025
  12.500   1.4866   0.04361   0.03910  -0.0542   0.0125   0.8046
  12.750   1.4818   0.04595   0.04162  -0.0513   0.0124   0.8068
  13.000   1.4737   0.04879   0.04466  -0.0487   0.0124   0.8092
  13.250   1.4638   0.05202   0.04808  -0.0468   0.0123   0.8117
  13.500   1.4504   0.05601   0.05227  -0.0458   0.0123   0.8141
  13.750   1.4337   0.06089   0.05737  -0.0460   0.0122   0.8164
  14.000   1.4097   0.06774   0.06445  -0.0483   0.0122   0.8182
  14.250   1.3745   0.07852   0.07555  -0.0552   0.0123   0.8195
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