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NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il)
Reynolds number: 200,000
Max Cl/Cd: 43.12 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20610-il-200000-n5.txt
Download as CSV file: xf-sc20610-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7273   0.08578   0.08161  -0.0357   1.0000   0.0228
 -12.500  -0.8075   0.06322   0.05872  -0.0529   1.0000   0.0221
 -12.250  -0.8398   0.05583   0.05107  -0.0569   1.0000   0.0220
 -12.000  -0.8652   0.05065   0.04566  -0.0580   1.0000   0.0220
 -11.750  -0.8875   0.04692   0.04172  -0.0567   1.0000   0.0220
 -11.500  -0.9040   0.04348   0.03803  -0.0555   1.0000   0.0222
 -11.250  -0.9101   0.03996   0.03417  -0.0552   1.0000   0.0224
 -11.000  -0.9084   0.03687   0.03070  -0.0545   1.0000   0.0227
 -10.750  -0.9006   0.03417   0.02763  -0.0539   1.0000   0.0230
 -10.500  -0.8881   0.03190   0.02501  -0.0533   1.0000   0.0234
 -10.250  -0.8724   0.03018   0.02316  -0.0528   1.0000   0.0238
 -10.000  -0.8545   0.02889   0.02176  -0.0524   1.0000   0.0243
  -9.750  -0.8354   0.02771   0.02049  -0.0520   1.0000   0.0248
  -9.500  -0.8154   0.02655   0.01921  -0.0516   1.0000   0.0255
  -9.250  -0.7946   0.02547   0.01798  -0.0512   1.0000   0.0264
  -9.000  -0.7731   0.02441   0.01674  -0.0509   1.0000   0.0276
  -8.750  -0.7510   0.02338   0.01552  -0.0505   1.0000   0.0286
  -8.500  -0.7287   0.02242   0.01456  -0.0503   1.0000   0.0297
  -8.250  -0.7054   0.02164   0.01375  -0.0502   1.0000   0.0308
  -8.000  -0.6817   0.02086   0.01289  -0.0500   1.0000   0.0322
  -7.750  -0.6573   0.02009   0.01202  -0.0499   1.0000   0.0339
  -7.500  -0.6323   0.01930   0.01119  -0.0501   1.0000   0.0356
  -7.250  -0.6069   0.01877   0.01067  -0.0503   1.0000   0.0379
  -7.000  -0.5811   0.01827   0.01010  -0.0504   1.0000   0.0409
  -6.750  -0.5544   0.01766   0.00948  -0.0509   1.0000   0.0439
  -6.500  -0.5276   0.01721   0.00902  -0.0512   1.0000   0.0473
  -6.250  -0.5005   0.01680   0.00855  -0.0516   1.0000   0.0512
  -6.000  -0.4723   0.01631   0.00810  -0.0523   1.0000   0.0559
  -5.750  -0.4443   0.01600   0.00773  -0.0528   1.0000   0.0610
  -5.500  -0.4145   0.01553   0.00732  -0.0539   1.0000   0.0672
  -5.250  -0.3818   0.01518   0.00694  -0.0554   0.9991   0.0746
  -5.000  -0.3476   0.01479   0.00660  -0.0572   0.9980   0.0842
  -4.750  -0.3131   0.01443   0.00629  -0.0591   0.9969   0.0977
  -4.500  -0.2777   0.01404   0.00599  -0.0613   0.9958   0.1178
  -4.000  -0.2029   0.01290   0.00546  -0.0670   0.9947   0.2471
  -3.750  -0.1612   0.01192   0.00521  -0.0713   0.9953   0.4087
  -3.500  -0.1260   0.01158   0.00558  -0.0731   0.9947   0.5619
  -3.250  -0.0937   0.01169   0.00574  -0.0739   0.9924   0.6089
  -3.000  -0.0621   0.01181   0.00587  -0.0746   0.9897   0.6324
  -2.750  -0.0306   0.01198   0.00607  -0.0752   0.9871   0.6524
  -2.500   0.0024   0.01221   0.00628  -0.0762   0.9849   0.6738
  -2.250   0.0324   0.01247   0.00658  -0.0763   0.9818   0.6875
  -2.000   0.0597   0.01272   0.00687  -0.0758   0.9778   0.6975
  -1.750   0.0916   0.01289   0.00703  -0.0765   0.9751   0.7074
  -1.500   0.1228   0.01306   0.00724  -0.0769   0.9726   0.7129
  -1.250   0.1560   0.01311   0.00730  -0.0781   0.9694   0.7188
  -1.000   0.1895   0.01308   0.00728  -0.0792   0.9638   0.7235
  -0.750   0.2295   0.01297   0.00722  -0.0814   0.9589   0.7260
  -0.500   0.2679   0.01273   0.00701  -0.0832   0.9490   0.7284
  -0.250   0.3127   0.01232   0.00664  -0.0861   0.9381   0.7308
   0.000   0.3527   0.01190   0.00624  -0.0879   0.9205   0.7333
   0.250   0.3926   0.01150   0.00583  -0.0897   0.8938   0.7361
   0.500   0.4295   0.01126   0.00556  -0.0910   0.8621   0.7392
   0.750   0.4620   0.01115   0.00541  -0.0913   0.8154   0.7408
   1.000   0.4904   0.01139   0.00515  -0.0903   0.6851   0.7426
   1.250   0.5058   0.01262   0.00536  -0.0874   0.4802   0.7446
   1.500   0.5256   0.01366   0.00571  -0.0861   0.3304   0.7470
   1.750   0.5490   0.01446   0.00603  -0.0855   0.2259   0.7497
   2.000   0.5749   0.01509   0.00631  -0.0855   0.1565   0.7525
   2.250   0.6026   0.01559   0.00659  -0.0858   0.1194   0.7553
   2.500   0.6282   0.01600   0.00692  -0.0853   0.0997   0.7570
   2.750   0.6540   0.01638   0.00728  -0.0849   0.0865   0.7589
   3.000   0.6801   0.01676   0.00766  -0.0845   0.0771   0.7610
   3.250   0.7061   0.01722   0.00807  -0.0842   0.0695   0.7634
   3.500   0.7331   0.01759   0.00849  -0.0840   0.0632   0.7661
   3.750   0.7597   0.01812   0.00897  -0.0840   0.0578   0.7688
   4.000   0.7877   0.01851   0.00940  -0.0841   0.0528   0.7715
   4.250   0.8122   0.01907   0.00994  -0.0835   0.0485   0.7730
   4.500   0.8377   0.01950   0.01047  -0.0830   0.0449   0.7748
   4.750   0.8629   0.02001   0.01102  -0.0825   0.0419   0.7768
   5.000   0.8874   0.02069   0.01170  -0.0819   0.0393   0.7792
   5.250   0.9130   0.02127   0.01238  -0.0815   0.0365   0.7819
   5.500   0.9389   0.02182   0.01295  -0.0813   0.0342   0.7848
   5.750   0.9640   0.02264   0.01379  -0.0810   0.0325   0.7874
   6.000   0.9878   0.02345   0.01474  -0.0801   0.0310   0.7892
   6.250   1.0116   0.02429   0.01570  -0.0794   0.0296   0.7912
   6.500   1.0354   0.02512   0.01660  -0.0787   0.0285   0.7935
   6.750   1.0590   0.02603   0.01756  -0.0781   0.0276   0.7960
   7.000   1.0824   0.02723   0.01887  -0.0775   0.0268   0.7987
   7.250   1.1065   0.02844   0.02031  -0.0770   0.0257   0.8015
   7.500   1.1287   0.02961   0.02169  -0.0761   0.0247   0.8037
   7.750   1.1498   0.03073   0.02298  -0.0751   0.0239   0.8058
   8.000   1.1703   0.03195   0.02438  -0.0740   0.0233   0.8082
   8.250   1.1902   0.03321   0.02578  -0.0729   0.0228   0.8110
   8.500   1.2092   0.03466   0.02736  -0.0719   0.0224   0.8141
   8.750   1.2259   0.03671   0.02965  -0.0706   0.0221   0.8171
   9.000   1.2377   0.03927   0.03268  -0.0684   0.0217   0.8193
   9.250   1.2448   0.04235   0.03625  -0.0658   0.0214   0.8216
   9.500   1.2457   0.04602   0.04044  -0.0627   0.0211   0.8240
   9.750   1.2389   0.05029   0.04521  -0.0591   0.0208   0.8266
  10.000   1.2233   0.05500   0.05039  -0.0551   0.0206   0.8294
  10.250   1.1967   0.05958   0.05534  -0.0503   0.0205   0.8325
  10.500   1.1641   0.06514   0.06125  -0.0471   0.0205   0.8348
  10.750   1.1239   0.07264   0.06910  -0.0469   0.0206   0.8370
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