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NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il)
Reynolds number: 1,000,000
Max Cl/Cd: 68.03 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20706-il-1000000-n5.txt
Download as CSV file: xf-sc20706-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0706 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6400   0.08436   0.08274  -0.0161   1.0000   0.0045
 -10.000  -0.6517   0.07921   0.07762  -0.0178   1.0000   0.0046
  -9.750  -0.6726   0.07419   0.07266  -0.0183   1.0000   0.0046
  -9.500  -0.6933   0.06254   0.06099  -0.0318   1.0000   0.0045
  -9.250  -0.7016   0.02491   0.02179  -0.0608   0.9977   0.0052
  -9.000  -0.6722   0.02078   0.01715  -0.0640   0.9976   0.0055
  -8.750  -0.6421   0.01835   0.01436  -0.0660   0.9974   0.0057
  -8.500  -0.6119   0.01655   0.01228  -0.0676   0.9973   0.0059
  -8.250  -0.5818   0.01536   0.01090  -0.0689   0.9971   0.0060
  -8.000  -0.5520   0.01457   0.00997  -0.0699   0.9969   0.0062
  -7.750  -0.5218   0.01367   0.00891  -0.0710   0.9967   0.0064
  -7.500  -0.4913   0.01280   0.00790  -0.0721   0.9965   0.0065
  -7.250  -0.4592   0.01143   0.00632  -0.0737   0.9967   0.0069
  -7.000  -0.4279   0.01069   0.00549  -0.0749   0.9966   0.0075
  -6.750  -0.3973   0.01028   0.00504  -0.0758   0.9964   0.0080
  -6.500  -0.3668   0.00995   0.00464  -0.0767   0.9962   0.0085
  -6.250  -0.3362   0.00961   0.00426  -0.0776   0.9960   0.0090
  -6.000  -0.3055   0.00930   0.00390  -0.0785   0.9958   0.0095
  -5.750  -0.2748   0.00902   0.00358  -0.0794   0.9957   0.0099
  -5.500  -0.2440   0.00879   0.00331  -0.0802   0.9954   0.0105
  -5.250  -0.2127   0.00851   0.00300  -0.0812   0.9953   0.0127
  -5.000  -0.1817   0.00832   0.00282  -0.0820   0.9951   0.0159
  -4.750  -0.1511   0.00817   0.00266  -0.0828   0.9949   0.0187
  -4.500  -0.1203   0.00800   0.00252  -0.0836   0.9947   0.0238
  -4.250  -0.0898   0.00789   0.00241  -0.0844   0.9945   0.0276
  -4.000  -0.0596   0.00775   0.00230  -0.0850   0.9942   0.0372
  -3.750  -0.0290   0.00754   0.00221  -0.0859   0.9940   0.0646
  -3.500   0.0024   0.00731   0.00213  -0.0869   0.9937   0.1065
  -3.250   0.0348   0.00705   0.00205  -0.0882   0.9933   0.1601
  -3.000   0.0696   0.00673   0.00194  -0.0900   0.9921   0.2259
  -2.750   0.1107   0.00609   0.00179  -0.0936   0.9905   0.3743
  -2.500   0.1565   0.00546   0.00161  -0.0980   0.9871   0.5183
  -2.250   0.2017   0.00512   0.00142  -0.1020   0.9838   0.5686
  -2.000   0.2325   0.00498   0.00138  -0.1026   0.9793   0.5988
  -1.750   0.2704   0.00480   0.00125  -0.1048   0.9734   0.6157
  -1.500   0.3043   0.00468   0.00120  -0.1061   0.9648   0.6310
  -1.250   0.3340   0.00585   0.00109  -0.1060   0.6292   0.6442
  -1.000   0.3578   0.00664   0.00126  -0.1054   0.4538   0.6558
  -0.750   0.3827   0.00737   0.00143  -0.1050   0.2909   0.6656
  -0.500   0.4091   0.00787   0.00157  -0.1049   0.1833   0.6749
  -0.250   0.4362   0.00820   0.00172  -0.1048   0.1195   0.6839
   0.000   0.4634   0.00853   0.00186  -0.1048   0.0671   0.6923
   0.250   0.4909   0.00878   0.00201  -0.1047   0.0381   0.6999
   0.500   0.5187   0.00895   0.00215  -0.1047   0.0286   0.7065
   0.750   0.5465   0.00911   0.00233  -0.1046   0.0237   0.7131
   1.000   0.5743   0.00927   0.00250  -0.1046   0.0199   0.7196
   1.250   0.6018   0.00948   0.00271  -0.1045   0.0153   0.7266
   1.500   0.6294   0.00967   0.00291  -0.1044   0.0129   0.7327
   1.750   0.6567   0.00994   0.00319  -0.1042   0.0105   0.7390
   2.000   0.6837   0.01030   0.00364  -0.1039   0.0094   0.7447
   2.250   0.7109   0.01056   0.00394  -0.1037   0.0091   0.7506
   2.500   0.7379   0.01087   0.00430  -0.1035   0.0087   0.7562
   2.750   0.7647   0.01124   0.00474  -0.1032   0.0084   0.7620
   3.000   0.7913   0.01165   0.00522  -0.1028   0.0081   0.7683
   3.250   0.8177   0.01208   0.00574  -0.1025   0.0078   0.7736
   3.500   0.8439   0.01253   0.00627  -0.1021   0.0075   0.7794
   3.750   0.8701   0.01298   0.00678  -0.1017   0.0072   0.7848
   4.000   0.8962   0.01344   0.00732  -0.1013   0.0068   0.7902
   4.250   0.9220   0.01401   0.00796  -0.1008   0.0065   0.7956
   4.500   0.9461   0.01513   0.00925  -0.1000   0.0060   0.8006
   4.750   0.9685   0.01709   0.01154  -0.0987   0.0057   0.8061
   5.000   0.9938   0.01786   0.01244  -0.0982   0.0056   0.8115
   5.250   1.0187   0.01860   0.01333  -0.0976   0.0055   0.8160
   5.500   1.0428   0.01968   0.01459  -0.0969   0.0053   0.8209
   5.750   1.0651   0.02138   0.01657  -0.0958   0.0052   0.8254
   6.000   1.0857   0.02352   0.01905  -0.0944   0.0050   0.8299
   6.250   1.1023   0.02695   0.02296  -0.0923   0.0048   0.8348
   6.500   1.0623   0.05185   0.04946  -0.0818   0.0041   0.8374
   6.750   1.0607   0.05995   0.05789  -0.0796   0.0039   0.8417
   7.000   1.0585   0.06714   0.06530  -0.0785   0.0037   0.8467
   7.250   1.0528   0.07442   0.07277  -0.0784   0.0037   0.8517
   7.500   1.0431   0.08167   0.08017  -0.0793   0.0036   0.8565
   7.750   1.0283   0.08917   0.08778  -0.0816   0.0036   0.8622
   8.000   1.0055   0.09601   0.09468  -0.0844   0.0037   0.8689
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