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NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il)
Reynolds number: 200,000
Max Cl/Cd: 41.29 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20410-il-200000-n5.txt
Download as CSV file: xf-sc20410-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0410 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8627   0.06882   0.06446  -0.0343   1.0000   0.0213
 -12.000  -0.9052   0.05885   0.05419  -0.0405   1.0000   0.0211
 -11.750  -0.9303   0.05286   0.04792  -0.0428   1.0000   0.0212
 -11.500  -0.9477   0.04841   0.04321  -0.0433   1.0000   0.0213
 -11.250  -0.9611   0.04483   0.03936  -0.0427   1.0000   0.0215
 -11.000  -0.9658   0.04134   0.03554  -0.0427   1.0000   0.0219
 -10.750  -0.9636   0.03813   0.03193  -0.0423   1.0000   0.0222
 -10.500  -0.9558   0.03526   0.02868  -0.0418   1.0000   0.0226
 -10.250  -0.9435   0.03279   0.02585  -0.0413   1.0000   0.0230
 -10.000  -0.9278   0.03079   0.02358  -0.0408   1.0000   0.0234
  -9.750  -0.9095   0.02937   0.02208  -0.0404   1.0000   0.0239
  -9.500  -0.8899   0.02817   0.02080  -0.0400   1.0000   0.0244
  -9.250  -0.8695   0.02701   0.01952  -0.0397   1.0000   0.0250
  -9.000  -0.8487   0.02584   0.01822  -0.0392   1.0000   0.0258
  -8.750  -0.8273   0.02469   0.01691  -0.0388   1.0000   0.0268
  -8.500  -0.8053   0.02364   0.01568  -0.0383   1.0000   0.0281
  -8.250  -0.7833   0.02267   0.01466  -0.0379   1.0000   0.0292
  -8.000  -0.7604   0.02193   0.01391  -0.0376   1.0000   0.0305
  -7.750  -0.7373   0.02112   0.01303  -0.0373   1.0000   0.0321
  -7.500  -0.7139   0.02029   0.01208  -0.0369   1.0000   0.0339
  -7.250  -0.6904   0.01945   0.01122  -0.0366   1.0000   0.0356
  -7.000  -0.6662   0.01883   0.01060  -0.0365   1.0000   0.0377
  -6.750  -0.6416   0.01827   0.00997  -0.0362   1.0000   0.0406
  -6.500  -0.6169   0.01764   0.00934  -0.0362   1.0000   0.0436
  -6.250  -0.5918   0.01716   0.00885  -0.0361   1.0000   0.0469
  -6.000  -0.5664   0.01673   0.00836  -0.0359   1.0000   0.0504
  -5.750  -0.5409   0.01614   0.00782  -0.0361   1.0000   0.0545
  -5.500  -0.5151   0.01576   0.00740  -0.0360   1.0000   0.0592
  -5.250  -0.4888   0.01523   0.00690  -0.0362   1.0000   0.0639
  -5.000  -0.4624   0.01483   0.00651  -0.0364   1.0000   0.0694
  -4.750  -0.4354   0.01441   0.00608  -0.0366   1.0000   0.0751
  -4.500  -0.4083   0.01402   0.00571  -0.0369   1.0000   0.0830
  -4.250  -0.3806   0.01363   0.00538  -0.0373   1.0000   0.0935
  -4.000  -0.3526   0.01325   0.00508  -0.0379   1.0000   0.1091
  -3.750  -0.3237   0.01280   0.00479  -0.0387   1.0000   0.1405
  -3.500  -0.2927   0.01219   0.00451  -0.0402   1.0000   0.2087
  -3.250  -0.2578   0.01131   0.00419  -0.0429   1.0000   0.3298
  -3.000  -0.2205   0.01032   0.00418  -0.0458   1.0000   0.5294
  -2.750  -0.1949   0.01044   0.00453  -0.0452   1.0000   0.6123
  -2.500  -0.1650   0.01057   0.00468  -0.0456   0.9983   0.6399
  -2.250  -0.1303   0.01069   0.00480  -0.0469   0.9950   0.6596
  -2.000  -0.0969   0.01088   0.00500  -0.0478   0.9909   0.6799
  -1.750  -0.0639   0.01114   0.00529  -0.0485   0.9864   0.6989
  -1.500  -0.0300   0.01133   0.00551  -0.0495   0.9828   0.7109
  -1.250   0.0033   0.01143   0.00559  -0.0505   0.9776   0.7210
  -1.000   0.0361   0.01155   0.00577  -0.0512   0.9733   0.7272
  -0.750   0.0708   0.01159   0.00583  -0.0525   0.9685   0.7330
  -0.500   0.1088   0.01150   0.00573  -0.0546   0.9623   0.7376
  -0.250   0.1482   0.01136   0.00560  -0.0569   0.9547   0.7398
   0.000   0.1862   0.01118   0.00545  -0.0585   0.9410   0.7418
   0.250   0.2221   0.01101   0.00530  -0.0596   0.9208   0.7440
   0.500   0.2569   0.01087   0.00516  -0.0606   0.8997   0.7461
   0.750   0.2895   0.01076   0.00499  -0.0609   0.8664   0.7482
   1.000   0.3192   0.01072   0.00487  -0.0607   0.8233   0.7503
   1.250   0.3476   0.01078   0.00477  -0.0604   0.7722   0.7526
   1.750   0.3968   0.01157   0.00470  -0.0581   0.5644   0.7569
   2.000   0.4172   0.01257   0.00492  -0.0568   0.3941   0.7585
   2.250   0.4409   0.01337   0.00519  -0.0563   0.2765   0.7604
   2.500   0.4661   0.01403   0.00546  -0.0562   0.1914   0.7625
   2.750   0.4929   0.01450   0.00574  -0.0562   0.1446   0.7647
   3.000   0.5204   0.01492   0.00601  -0.0563   0.1156   0.7669
   3.250   0.5484   0.01530   0.00629  -0.0565   0.0964   0.7692
   3.500   0.5768   0.01566   0.00661  -0.0568   0.0851   0.7715
   3.750   0.6032   0.01605   0.00699  -0.0565   0.0770   0.7730
   4.000   0.6296   0.01643   0.00738  -0.0562   0.0701   0.7748
   4.250   0.6559   0.01689   0.00786  -0.0559   0.0649   0.7770
   4.500   0.6827   0.01727   0.00828  -0.0558   0.0596   0.7794
   4.750   0.7090   0.01780   0.00878  -0.0557   0.0549   0.7819
   5.000   0.7365   0.01818   0.00922  -0.0557   0.0505   0.7844
   5.250   0.7632   0.01872   0.00973  -0.0557   0.0466   0.7869
   5.500   0.7888   0.01921   0.01032  -0.0552   0.0435   0.7887
   5.750   0.8142   0.01973   0.01090  -0.0548   0.0407   0.7907
   6.000   0.8390   0.02041   0.01158  -0.0544   0.0381   0.7930
   6.250   0.8648   0.02100   0.01230  -0.0541   0.0355   0.7955
   6.500   0.8907   0.02157   0.01291  -0.0539   0.0332   0.7983
   6.750   0.9157   0.02238   0.01371  -0.0537   0.0316   0.8013
   7.000   0.9399   0.02325   0.01477  -0.0530   0.0301   0.8036
   7.250   0.9636   0.02417   0.01583  -0.0523   0.0288   0.8061
   7.500   0.9874   0.02507   0.01684  -0.0517   0.0277   0.8091
   7.750   1.0111   0.02598   0.01784  -0.0512   0.0269   0.8122
   8.000   1.0342   0.02712   0.01902  -0.0507   0.0261   0.8155
   8.250   1.0565   0.02847   0.02064  -0.0499   0.0253   0.8181
   8.500   1.0776   0.02986   0.02232  -0.0489   0.0243   0.8207
   8.750   1.0982   0.03120   0.02389  -0.0480   0.0235   0.8238
   9.000   1.1184   0.03256   0.02547  -0.0472   0.0228   0.8272
   9.250   1.1378   0.03402   0.02712  -0.0463   0.0224   0.8309
   9.500   1.1552   0.03547   0.02875  -0.0452   0.0220   0.8340
   9.750   1.1710   0.03708   0.03053  -0.0439   0.0216   0.8376
  10.000   1.1838   0.03926   0.03296  -0.0424   0.0213   0.8417
  10.250   1.1893   0.04260   0.03681  -0.0403   0.0211   0.8460
  10.500   1.1861   0.04654   0.04129  -0.0375   0.0208   0.8495
  10.750   1.1734   0.05117   0.04644  -0.0343   0.0206   0.8535
  11.000   1.1501   0.05580   0.05149  -0.0306   0.0206   0.8584
  11.250   1.1207   0.06107   0.05710  -0.0283   0.0206   0.8632
  11.500   1.0873   0.06776   0.06412  -0.0292   0.0206   0.8676
  11.750   1.0477   0.07803   0.07467  -0.0359   0.0208   0.8720
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