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NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il)
Reynolds number: 100,000
Max Cl/Cd: 16.29 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20402-il-100000.txt
Download as CSV file: xf-sc20402-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0402 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6827   0.10404   0.09939   0.0275   1.0000   0.0469
  -8.000  -0.6789   0.10035   0.09574   0.0252   1.0000   0.0487
  -7.750  -0.6738   0.09656   0.09199   0.0215   1.0000   0.0505
  -7.500  -0.6629   0.09236   0.08780   0.0137   1.0000   0.0524
  -7.250  -0.6438   0.08806   0.08342   0.0012   1.0000   0.0534
  -7.000  -0.6241   0.08447   0.07957  -0.0079   1.0000   0.0539
  -6.750  -0.6285   0.07765   0.07306   0.0017   1.0000   0.0577
  -6.500  -0.6130   0.07316   0.06851  -0.0020   1.0000   0.0619
  -6.250  -0.5762   0.07004   0.06479  -0.0157   1.0000   0.0669
  -6.000  -0.5733   0.06311   0.05818  -0.0120   1.0000   0.0705
  -5.750  -0.5410   0.05898   0.05308  -0.0199   1.0000   0.0805
  -5.500  -0.5299   0.05401   0.04834  -0.0184   1.0000   0.0869
  -5.250  -0.5058   0.04971   0.04384  -0.0214   1.0000   0.0985
  -5.000  -0.4562   0.03093   0.02532  -0.0231   1.0000   0.1222
  -4.750  -0.4578   0.04215   0.03593  -0.0256   1.0000   0.1387
  -4.500  -0.4350   0.03878   0.03244  -0.0270   1.0000   0.1753
  -3.500  -0.2873   0.02535   0.01663  -0.0321   1.0000   0.0907
  -3.250  -0.2515   0.02322   0.01374  -0.0306   1.0000   0.0530
  -3.000  -0.2205   0.02132   0.01140  -0.0298   1.0000   0.0412
  -2.750  -0.1923   0.01856   0.00856  -0.0295   1.0000   0.0363
  -2.500  -0.1640   0.01686   0.00668  -0.0288   1.0000   0.0326
  -2.250  -0.1364   0.01546   0.00524  -0.0282   1.0000   0.0310
  -1.750  -0.0793   0.01297   0.00260  -0.0278   1.0000   0.0514
  -1.500  -0.0731   0.00935   0.00210  -0.0223   1.0000   0.8796
  -1.250  -0.0457   0.00906   0.00135  -0.0211   1.0000   1.0000
  -1.000  -0.0179   0.00905   0.00111  -0.0212   1.0000   1.0000
  -0.750   0.0096   0.00905   0.00097  -0.0212   1.0000   1.0000
  -0.500   0.0370   0.00906   0.00091  -0.0212   1.0000   1.0000
  -0.250   0.0643   0.00907   0.00093  -0.0212   1.0000   1.0000
   0.000   0.0915   0.00909   0.00102  -0.0211   1.0000   1.0000
   0.250   0.1187   0.00913   0.00119  -0.0210   1.0000   1.0000
   0.500   0.1459   0.00916   0.00149  -0.0209   1.0000   1.0000
   0.750   0.1945   0.01302   0.00268  -0.0241   0.0498   1.0000
   1.250   0.2485   0.01553   0.00534  -0.0228   0.0308   1.0000
   1.500   0.2760   0.01696   0.00681  -0.0221   0.0324   1.0000
   1.750   0.3047   0.01870   0.00871  -0.0214   0.0361   1.0000
   2.000   0.3330   0.02161   0.01169  -0.0210   0.0409   1.0000
   2.250   0.3641   0.02327   0.01379  -0.0199   0.0526   1.0000
   2.500   0.3997   0.02523   0.01652  -0.0180   0.0892   1.0000
   3.750   0.5579   0.04085   0.03461  -0.0179   0.1496   1.0000
   4.000   0.5787   0.04426   0.03813  -0.0182   0.1228   1.0000
   4.250   0.5975   0.04851   0.04237  -0.0184   0.1071   1.0000
   4.500   0.6171   0.05283   0.04680  -0.0191   0.0936   1.0000
   4.750   0.6405   0.05611   0.05046  -0.0208   0.0815   1.0000
   5.000   0.6656   0.06061   0.05579  -0.0242   0.0721   1.0000
   5.250   0.6743   0.06656   0.06157  -0.0227   0.0673   1.0000
   5.500   0.7037   0.07014   0.06568  -0.0296   0.0623   1.0000
   5.750   0.7202   0.07460   0.07026  -0.0322   0.0575   1.0000
   6.000   0.7218   0.08122   0.07664  -0.0279   0.0540   1.0000
   6.250   0.7381   0.08580   0.08143  -0.0329   0.0532   1.0000
   6.500   0.7594   0.08964   0.08549  -0.0429   0.0514   1.0000
   6.750   0.7715   0.09429   0.09019  -0.0489   0.0491   1.0000
   7.000   0.7798   0.09888   0.09478  -0.0534   0.0472   1.0000
   7.250   0.7856   0.10328   0.09918  -0.0568   0.0454   1.0000
   7.500   0.7893   0.10749   0.10337  -0.0588   0.0438   1.0000
   7.750   0.7929   0.11610   0.11194  -0.0472   0.0407   1.0000
   8.000   0.7991   0.12016   0.11601  -0.0531   0.0406   1.0000
   8.250   0.8011   0.12380   0.11961  -0.0581   0.0404   1.0000
   8.500   0.8025   0.12717   0.12293  -0.0624   0.0403   1.0000
   8.750   0.8038   0.13035   0.12607  -0.0663   0.0400   1.0000
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