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SA7024 (sa7024-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 100,000
Max Cl/Cd: 59.8 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7024-il-100000.txt
Download as CSV file: xf-sa7024-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7024                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3168   0.10731   0.10254  -0.0250   1.0000   0.0664
  -9.250  -0.3244   0.10557   0.10086  -0.0272   1.0000   0.0671
  -9.000  -0.3316   0.10364   0.09901  -0.0293   1.0000   0.0674
  -8.750  -0.3156   0.09691   0.09229  -0.0271   1.0000   0.0691
  -8.500  -0.3044   0.09289   0.08828  -0.0256   1.0000   0.0720
  -8.250  -0.3019   0.08976   0.08519  -0.0256   1.0000   0.0746
  -8.000  -0.3030   0.08687   0.08236  -0.0261   1.0000   0.0775
  -7.750  -0.3119   0.08476   0.08034  -0.0275   1.0000   0.0798
  -7.500  -0.3245   0.08302   0.07871  -0.0286   1.0000   0.0805
  -7.250  -0.3393   0.08142   0.07723  -0.0296   1.0000   0.0808
  -7.000  -0.3095   0.07469   0.07045  -0.0251   1.0000   0.0874
  -6.750  -0.3169   0.07237   0.06822  -0.0242   1.0000   0.0906
  -6.500  -0.3284   0.07029   0.06624  -0.0247   1.0000   0.0927
  -6.250  -0.3397   0.06788   0.06391  -0.0305   1.0000   0.0942
  -6.000  -0.3379   0.06356   0.05967  -0.0273   1.0000   0.0966
  -5.750  -0.3334   0.06078   0.05693  -0.0239   1.0000   0.1007
  -5.500  -0.3345   0.05773   0.05390  -0.0267   1.0000   0.1059
  -5.250  -0.3441   0.06439   0.05994  -0.0431   1.0000   0.1090
  -5.000  -0.3414   0.06155   0.05727  -0.0374   1.0000   0.1117
  -4.750  -0.3210   0.05771   0.05322  -0.0439   1.0000   0.1231
  -4.500  -0.3152   0.05507   0.05068  -0.0400   1.0000   0.1267
  -4.250  -0.2965   0.05152   0.04701  -0.0430   1.0000   0.1387
  -4.000  -0.2783   0.04848   0.04386  -0.0447   1.0000   0.1521
  -3.750  -0.2604   0.04570   0.04101  -0.0454   1.0000   0.1661
  -3.500  -0.2427   0.04309   0.03836  -0.0456   1.0000   0.1811
  -3.250  -0.2242   0.04073   0.03596  -0.0456   1.0000   0.1979
  -3.000  -0.1604   0.03309   0.02703  -0.0560   1.0000   0.1371
  -2.750  -0.1068   0.02524   0.01779  -0.0583   1.0000   0.0615
  -2.500  -0.0747   0.02284   0.01463  -0.0584   1.0000   0.0561
  -2.250  -0.0488   0.02142   0.01302  -0.0583   1.0000   0.0587
  -2.000  -0.0236   0.02038   0.01176  -0.0579   1.0000   0.0630
  -1.750   0.0019   0.01927   0.01046  -0.0573   1.0000   0.0643
  -1.500   0.0262   0.01847   0.00954  -0.0566   1.0000   0.0669
  -1.250   0.0507   0.01755   0.00873  -0.0563   1.0000   0.0748
  -1.000   0.0755   0.01689   0.00812  -0.0560   1.0000   0.0975
  -0.750   0.0975   0.01369   0.00788  -0.0545   0.9998   1.0000
  -0.500   0.1475   0.01420   0.00789  -0.0593   0.9887   1.0000
  -0.250   0.1958   0.01463   0.00799  -0.0638   0.9775   1.0000
   0.000   0.2436   0.01497   0.00805  -0.0681   0.9662   1.0000
   0.250   0.2914   0.01519   0.00809  -0.0722   0.9546   1.0000
   0.500   0.3404   0.01531   0.00806  -0.0764   0.9432   1.0000
   0.750   0.3859   0.01531   0.00797  -0.0798   0.9303   1.0000
   1.000   0.4311   0.01523   0.00782  -0.0829   0.9174   1.0000
   1.250   0.4767   0.01507   0.00762  -0.0860   0.9046   1.0000
   1.500   0.5209   0.01485   0.00738  -0.0886   0.8914   1.0000
   1.750   0.5631   0.01458   0.00713  -0.0906   0.8774   1.0000
   2.000   0.6032   0.01429   0.00685  -0.0920   0.8624   1.0000
   2.250   0.6371   0.01410   0.00667  -0.0923   0.8436   1.0000
   2.500   0.6701   0.01391   0.00653  -0.0923   0.8237   1.0000
   2.750   0.7005   0.01380   0.00641  -0.0918   0.8019   1.0000
   3.000   0.7302   0.01374   0.00631  -0.0911   0.7793   1.0000
   3.250   0.7567   0.01379   0.00635  -0.0900   0.7536   1.0000
   3.500   0.7829   0.01389   0.00641  -0.0889   0.7269   1.0000
   3.750   0.8084   0.01403   0.00656  -0.0877   0.6987   1.0000
   4.000   0.8334   0.01423   0.00669  -0.0864   0.6693   1.0000
   4.250   0.8575   0.01448   0.00689  -0.0850   0.6380   1.0000
   4.500   0.8811   0.01478   0.00714  -0.0837   0.6056   1.0000
   4.750   0.9047   0.01513   0.00740  -0.0824   0.5733   1.0000
   5.000   0.9276   0.01553   0.00781  -0.0810   0.5392   1.0000
   5.250   0.9502   0.01598   0.00819  -0.0796   0.5047   1.0000
   5.500   0.9721   0.01647   0.00863  -0.0783   0.4685   1.0000
   5.750   0.9934   0.01701   0.00907  -0.0768   0.4313   1.0000
   6.000   1.0140   0.01761   0.00957  -0.0753   0.3932   1.0000
   6.250   1.0342   0.01827   0.01023  -0.0738   0.3542   1.0000
   6.500   1.0538   0.01901   0.01090  -0.0723   0.3154   1.0000
   6.750   1.0728   0.01988   0.01168  -0.0708   0.2769   1.0000
   7.000   1.0907   0.02086   0.01256  -0.0692   0.2372   1.0000
   7.250   1.1075   0.02204   0.01359  -0.0675   0.1975   1.0000
   7.500   1.1231   0.02345   0.01480  -0.0658   0.1603   1.0000
   7.750   1.1386   0.02489   0.01621  -0.0640   0.1255   1.0000
   8.000   1.1516   0.02627   0.01755  -0.0622   0.0899   1.0000
   8.250   1.1610   0.02846   0.01955  -0.0600   0.0584   1.0000
   8.500   1.1720   0.03151   0.02253  -0.0575   0.0449   1.0000
   8.750   1.1907   0.03402   0.02529  -0.0557   0.0390   1.0000
   9.000   1.2093   0.03701   0.02834  -0.0545   0.0358   1.0000
   9.250   1.2287   0.04184   0.03343  -0.0535   0.0341   1.0000
   9.500   1.2420   0.04531   0.03738  -0.0516   0.0336   1.0000
   9.750   1.2497   0.04906   0.04163  -0.0493   0.0332   1.0000
  10.000   1.2515   0.05270   0.04578  -0.0467   0.0327   1.0000
  10.250   1.2484   0.05648   0.05000  -0.0441   0.0324   1.0000
  10.500   1.2398   0.06024   0.05416  -0.0413   0.0322   1.0000
  10.750   1.2253   0.06374   0.05797  -0.0382   0.0320   1.0000
  11.000   1.2080   0.06751   0.06200  -0.0360   0.0321   1.0000
  11.250   1.1892   0.07179   0.06653  -0.0350   0.0323   1.0000
  11.500   1.1693   0.07662   0.07157  -0.0353   0.0326   1.0000
  11.750   1.1493   0.08219   0.07732  -0.0370   0.0330   1.0000
  12.000   1.1293   0.08848   0.08376  -0.0398   0.0334   1.0000
  12.250   1.1107   0.09556   0.09094  -0.0433   0.0339   1.0000
  12.500   1.0542   0.11252   0.10833  -0.0585   0.0383   1.0000
  12.750   1.0201   0.12901   0.12480  -0.0694   0.0409   1.0000
  13.000   1.0085   0.13854   0.13429  -0.0744   0.0426   1.0000
  13.250   1.0034   0.14581   0.14151  -0.0777   0.0438   1.0000
  13.500   1.0037   0.15128   0.14698  -0.0793   0.0451   1.0000
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