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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 200,000
Max Cl/Cd: 67.75 at α=-0.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc21010-il-200000-n5.txt
Download as CSV file: xf-sc21010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-1010 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7426   0.05697   0.05240  -0.0692   0.9999   0.0230
 -13.750  -0.7696   0.05231   0.04764  -0.0703   0.9999   0.0230
 -13.500  -0.7973   0.04914   0.04439  -0.0687   0.9999   0.0229
 -13.250  -0.8161   0.04493   0.03994  -0.0703   0.9999   0.0230
 -13.000  -0.8213   0.04094   0.03563  -0.0724   0.9999   0.0231
 -12.750  -0.8137   0.03838   0.03290  -0.0732   0.9999   0.0234
 -12.500  -0.8009   0.03628   0.03064  -0.0739   0.9999   0.0237
 -12.250  -0.7786   0.03415   0.02830  -0.0762   0.9989   0.0242
 -12.000  -0.7495   0.03192   0.02580  -0.0796   0.9970   0.0248
 -11.750  -0.7191   0.02978   0.02336  -0.0827   0.9954   0.0255
 -11.500  -0.6874   0.02791   0.02117  -0.0856   0.9940   0.0267
 -11.250  -0.6564   0.02623   0.01911  -0.0880   0.9924   0.0279
 -11.000  -0.6261   0.02485   0.01765  -0.0900   0.9906   0.0288
 -10.750  -0.5945   0.02379   0.01651  -0.0919   0.9888   0.0298
 -10.500  -0.5621   0.02274   0.01533  -0.0939   0.9872   0.0309
 -10.250  -0.5293   0.02171   0.01415  -0.0959   0.9858   0.0323
 -10.000  -0.4959   0.02083   0.01308  -0.0978   0.9846   0.0339
  -9.750  -0.4621   0.01998   0.01226  -0.1001   0.9836   0.0358
  -9.500  -0.4306   0.01933   0.01155  -0.1016   0.9815   0.0380
  -9.250  -0.3987   0.01866   0.01076  -0.1030   0.9792   0.0401
  -9.000  -0.3652   0.01790   0.01000  -0.1050   0.9774   0.0425
  -8.750  -0.3315   0.01741   0.00948  -0.1069   0.9757   0.0459
  -8.500  -0.2971   0.01692   0.00891  -0.1088   0.9743   0.0493
  -8.250  -0.2618   0.01636   0.00838  -0.1111   0.9732   0.0537
  -8.000  -0.2265   0.01598   0.00794  -0.1131   0.9720   0.0589
  -7.750  -0.1902   0.01548   0.00746  -0.1156   0.9712   0.0659
  -7.500  -0.1585   0.01511   0.00711  -0.1169   0.9687   0.0749
  -7.250  -0.1259   0.01476   0.00680  -0.1184   0.9662   0.0874
  -7.000  -0.0914   0.01440   0.00650  -0.1203   0.9641   0.1066
  -6.750  -0.0556   0.01402   0.00622  -0.1225   0.9624   0.1338
  -6.500  -0.0186   0.01359   0.00597  -0.1250   0.9610   0.1764
  -6.250   0.0195   0.01309   0.00575  -0.1279   0.9601   0.2478
  -6.000   0.0575   0.01264   0.00564  -0.1307   0.9592   0.3353
  -5.750   0.0944   0.01236   0.00562  -0.1331   0.9583   0.4108
  -5.500   0.1305   0.01223   0.00561  -0.1350   0.9574   0.4567
  -5.250   0.1577   0.01223   0.00569  -0.1349   0.9529   0.4875
  -5.000   0.1895   0.01219   0.00573  -0.1358   0.9500   0.5165
  -4.750   0.2228   0.01217   0.00575  -0.1370   0.9478   0.5379
  -4.500   0.2565   0.01214   0.00579  -0.1382   0.9461   0.5598
  -4.250   0.2906   0.01212   0.00583  -0.1395   0.9446   0.5834
  -4.000   0.3249   0.01210   0.00586  -0.1408   0.9431   0.6024
  -3.750   0.3515   0.01218   0.00601  -0.1404   0.9385   0.6152
  -3.500   0.3816   0.01222   0.00610  -0.1408   0.9351   0.6274
  -3.250   0.4138   0.01223   0.00615  -0.1417   0.9325   0.6396
  -3.000   0.4465   0.01223   0.00622  -0.1426   0.9305   0.6505
  -2.750   0.4802   0.01221   0.00626  -0.1437   0.9287   0.6612
  -2.500   0.5081   0.01230   0.00640  -0.1436   0.9238   0.6724
  -2.250   0.5377   0.01227   0.00646  -0.1436   0.9183   0.6810
  -2.000   0.5751   0.01191   0.00614  -0.1449   0.9113   0.6910
  -1.750   0.6058   0.01144   0.00572  -0.1443   0.8929   0.6995
  -1.500   0.6365   0.01109   0.00539  -0.1439   0.8713   0.7085
  -1.250   0.6656   0.01090   0.00522  -0.1433   0.8494   0.7165
  -1.000   0.6938   0.01076   0.00503  -0.1425   0.8139   0.7246
  -0.750   0.7213   0.01075   0.00492  -0.1416   0.7667   0.7316
  -0.500   0.7466   0.01102   0.00479  -0.1402   0.6653   0.7393
  -0.250   0.7583   0.01238   0.00513  -0.1364   0.4747   0.7450
   0.000   0.7734   0.01375   0.00572  -0.1341   0.3210   0.7527
   0.250   0.7923   0.01479   0.00625  -0.1326   0.2145   0.7594
   0.500   0.8135   0.01564   0.00675  -0.1314   0.1414   0.7667
   0.750   0.8368   0.01628   0.00720  -0.1306   0.1045   0.7736
   1.000   0.8602   0.01684   0.00766  -0.1297   0.0834   0.7798
   1.250   0.8851   0.01736   0.00814  -0.1291   0.0703   0.7873
   1.500   0.9086   0.01783   0.00863  -0.1280   0.0624   0.7929
   1.750   0.9324   0.01840   0.00916  -0.1272   0.0562   0.8000
   2.000   0.9563   0.01886   0.00969  -0.1263   0.0516   0.8059
   2.250   0.9792   0.01947   0.01029  -0.1253   0.0478   0.8124
   2.500   1.0027   0.02007   0.01094  -0.1244   0.0448   0.8190
   2.750   1.0254   0.02061   0.01154  -0.1232   0.0418   0.8253
   3.000   1.0483   0.02133   0.01226  -0.1223   0.0394   0.8327
   3.250   1.0695   0.02207   0.01307  -0.1209   0.0377   0.8384
   3.500   1.0925   0.02276   0.01384  -0.1200   0.0357   0.8449
   3.750   1.1150   0.02342   0.01453  -0.1189   0.0338   0.8503
   4.000   1.1362   0.02423   0.01536  -0.1177   0.0322   0.8561
   4.250   1.1585   0.02514   0.01636  -0.1167   0.0310   0.8627
   4.500   1.1797   0.02602   0.01737  -0.1153   0.0298   0.8690
   4.750   1.2019   0.02698   0.01843  -0.1142   0.0287   0.8763
   5.000   1.2225   0.02787   0.01941  -0.1129   0.0278   0.8827
   5.250   1.2436   0.02879   0.02037  -0.1117   0.0269   0.8899
   5.500   1.2632   0.02996   0.02159  -0.1104   0.0261   0.8966
   5.750   1.2840   0.03108   0.02296  -0.1090   0.0251   0.9045
   6.000   1.3029   0.03229   0.02440  -0.1074   0.0243   0.9131
   6.250   1.3208   0.03359   0.02590  -0.1056   0.0236   0.9240
   6.500   1.3364   0.03483   0.02734  -0.1035   0.0230   0.9436
   6.750   1.3531   0.03617   0.02885  -0.1018   0.0226   1.0001
   7.000   1.3708   0.03768   0.03049  -0.1005   0.0221   1.0001
   7.250   1.3869   0.03932   0.03226  -0.0991   0.0218   1.0001
   7.500   1.4004   0.04145   0.03455  -0.0973   0.0214   1.0001
   7.750   1.4075   0.04415   0.03769  -0.0945   0.0211   1.0001
   8.000   1.4087   0.04717   0.04116  -0.0911   0.0206   1.0001
   8.250   1.4032   0.05025   0.04464  -0.0869   0.0202   1.0001
   8.500   1.3932   0.05332   0.04804  -0.0824   0.0199   1.0001
   8.750   1.3804   0.05668   0.05173  -0.0782   0.0196   1.0001
   9.000   1.3647   0.06041   0.05576  -0.0746   0.0194   1.0001
   9.250   1.3451   0.06473   0.06038  -0.0716   0.0192   1.0001
   9.500   1.3201   0.07002   0.06597  -0.0695   0.0191   1.0001
   9.750   1.2898   0.07655   0.07281  -0.0691   0.0191   1.0001
  10.000   1.2514   0.08532   0.08190  -0.0713   0.0192   1.0001
  10.250   1.1950   0.10027   0.09722  -0.0804   0.0195   1.0001
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