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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 200,000
Max Cl/Cd: 69.32 at α=0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc21010-il-200000.txt
Download as CSV file: xf-sc21010-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5055   0.08878   0.08503  -0.0386   0.9999   0.0785
 -11.250  -0.5298   0.08465   0.08100  -0.0391   0.9999   0.0806
 -10.750  -0.6646   0.04461   0.03970  -0.0684   0.9999   0.0482
 -10.500  -0.6469   0.03915   0.03387  -0.0717   0.9999   0.0472
 -10.250  -0.6212   0.03428   0.02845  -0.0755   0.9999   0.0470
 -10.000  -0.5920   0.03119   0.02480  -0.0782   0.9999   0.0482
  -9.750  -0.5623   0.02910   0.02221  -0.0802   0.9999   0.0490
  -9.500  -0.5308   0.02564   0.01846  -0.0828   0.9999   0.0502
  -9.250  -0.5022   0.02418   0.01691  -0.0839   0.9999   0.0518
  -9.000  -0.4736   0.02316   0.01577  -0.0848   0.9999   0.0540
  -8.750  -0.4448   0.02237   0.01481  -0.0856   0.9999   0.0571
  -8.500  -0.4139   0.02111   0.01338  -0.0868   0.9999   0.0599
  -8.250  -0.3843   0.02015   0.01246  -0.0878   0.9999   0.0633
  -8.000  -0.3555   0.01964   0.01188  -0.0885   0.9999   0.0677
  -7.750  -0.3240   0.01881   0.01102  -0.0898   0.9999   0.0728
  -7.500  -0.2937   0.01832   0.01058  -0.0909   0.9999   0.0787
  -7.250  -0.2613   0.01774   0.01000  -0.0925   0.9999   0.0867
  -7.000  -0.2302   0.01741   0.00966  -0.0937   0.9999   0.0964
  -6.750  -0.1942   0.01683   0.00919  -0.0961   0.9999   0.1142
  -6.500  -0.1548   0.01617   0.00876  -0.0994   0.9999   0.1520
  -6.250  -0.1054   0.01514   0.00844  -0.1053   0.9999   0.2902
  -6.000  -0.0673   0.01482   0.00860  -0.1083   0.9999   0.4224
  -5.750  -0.0379   0.01491   0.00885  -0.1090   0.9999   0.4798
  -5.500  -0.0105   0.01511   0.00911  -0.1092   0.9999   0.5198
  -5.250   0.0173   0.01535   0.00941  -0.1095   0.9994   0.5536
  -5.000   0.0513   0.01554   0.00967  -0.1109   0.9971   0.5817
  -4.750   0.0862   0.01578   0.00991  -0.1125   0.9952   0.6063
  -4.500   0.1194   0.01603   0.01023  -0.1136   0.9932   0.6268
  -4.250   0.1504   0.01626   0.01049  -0.1143   0.9897   0.6439
  -4.000   0.1852   0.01650   0.01077  -0.1158   0.9865   0.6611
  -3.750   0.2210   0.01680   0.01111  -0.1173   0.9840   0.6793
  -3.500   0.2492   0.01707   0.01143  -0.1174   0.9803   0.6944
  -3.250   0.2805   0.01730   0.01168  -0.1182   0.9765   0.7078
  -3.000   0.3157   0.01749   0.01192  -0.1197   0.9734   0.7192
  -2.750   0.3547   0.01766   0.01215  -0.1218   0.9710   0.7295
  -2.500   0.3818   0.01778   0.01231  -0.1218   0.9638   0.7405
  -2.250   0.4187   0.01786   0.01246  -0.1234   0.9598   0.7502
  -2.000   0.4574   0.01790   0.01257  -0.1255   0.9563   0.7600
  -1.750   0.4882   0.01789   0.01261  -0.1259   0.9479   0.7705
  -1.500   0.5345   0.01720   0.01202  -0.1284   0.9369   0.7781
  -1.250   0.5991   0.01572   0.01061  -0.1338   0.9247   0.7880
  -1.000   0.6470   0.01464   0.00965  -0.1361   0.9146   0.7954
  -0.750   0.6890   0.01354   0.00862  -0.1371   0.8997   0.8043
  -0.500   0.7201   0.01292   0.00809  -0.1363   0.8845   0.8120
  -0.250   0.7496   0.01244   0.00768  -0.1354   0.8651   0.8201
   0.000   0.7777   0.01201   0.00728  -0.1341   0.8380   0.8280
   0.250   0.8034   0.01173   0.00699  -0.1324   0.7935   0.8361
   0.500   0.8249   0.01190   0.00655  -0.1294   0.6404   0.8449
   0.750   0.8232   0.01416   0.00718  -0.1233   0.3542   0.8526
   1.000   0.8318   0.01632   0.00812  -0.1203   0.1494   0.8616
   1.250   0.8481   0.01733   0.00882  -0.1180   0.1076   0.8692
   1.500   0.8700   0.01808   0.00952  -0.1168   0.0919   0.8779
   1.750   0.8894   0.01875   0.01015  -0.1150   0.0824   0.8866
   2.000   0.9105   0.01938   0.01082  -0.1135   0.0756   0.8956
   2.250   0.9325   0.02012   0.01152  -0.1123   0.0701   0.9051
   2.500   0.9518   0.02096   0.01239  -0.1104   0.0657   0.9144
   2.750   0.9737   0.02153   0.01301  -0.1091   0.0616   0.9244
   3.000   0.9948   0.02234   0.01379  -0.1077   0.0585   0.9358
   3.250   1.0161   0.02360   0.01508  -0.1062   0.0557   0.9491
   3.500   1.0375   0.02417   0.01580  -0.1046   0.0529   0.9716
   3.750   1.0671   0.02527   0.01696  -0.1051   0.0502   1.0001
   4.000   1.0984   0.02688   0.01855  -0.1060   0.0482   1.0001
   4.250   1.1306   0.02979   0.02161  -0.1070   0.0467   1.0001
   4.500   1.1586   0.03130   0.02343  -0.1069   0.0454   1.0001
   4.750   1.1852   0.03314   0.02557  -0.1066   0.0437   1.0001
   5.000   1.2101   0.03558   0.02833  -0.1061   0.0428   1.0001
   5.250   1.2320   0.03873   0.03189  -0.1051   0.0426   1.0001
   5.500   1.2483   0.04288   0.03655  -0.1032   0.0432   1.0001
   5.750   1.2594   0.04780   0.04195  -0.1008   0.0445   1.0001
   6.000   1.2680   0.05278   0.04726  -0.0987   0.0458   1.0001
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