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FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-120 (fx79l120-il)
Reynolds number: 200,000
Max Cl/Cd: 52.57 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l120-il-200000.txt
Download as CSV file: xf-fx79l120-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.9384   0.06707   0.06244  -0.0320   1.0000   0.0378
 -12.500  -0.9579   0.06209   0.05728  -0.0335   1.0000   0.0376
 -12.250  -0.9824   0.05770   0.05265  -0.0340   1.0000   0.0377
 -12.000  -0.9979   0.05406   0.04879  -0.0332   1.0000   0.0377
 -11.750  -1.0146   0.05110   0.04558  -0.0307   1.0000   0.0378
 -11.500  -1.0291   0.04766   0.04186  -0.0279   1.0000   0.0381
 -11.250  -1.0282   0.04408   0.03816  -0.0266   1.0000   0.0390
 -11.000  -1.0177   0.04240   0.03644  -0.0255   1.0000   0.0401
 -10.750  -1.0069   0.04076   0.03471  -0.0242   1.0000   0.0411
 -10.500  -0.9995   0.03852   0.03223  -0.0224   1.0000   0.0423
 -10.250  -0.9907   0.03610   0.02951  -0.0206   1.0000   0.0431
 -10.000  -0.9794   0.03398   0.02706  -0.0188   1.0000   0.0444
  -9.750  -0.9661   0.03266   0.02539  -0.0170   1.0000   0.0458
  -9.500  -0.9488   0.02985   0.02249  -0.0162   1.0000   0.0477
  -9.250  -0.9294   0.02865   0.02126  -0.0153   1.0000   0.0497
  -9.000  -0.9098   0.02741   0.01989  -0.0143   1.0000   0.0518
  -8.750  -0.8897   0.02626   0.01856  -0.0131   1.0000   0.0541
  -8.500  -0.8693   0.02462   0.01677  -0.0122   1.0000   0.0568
  -8.250  -0.8484   0.02349   0.01569  -0.0113   1.0000   0.0598
  -8.000  -0.8271   0.02257   0.01471  -0.0103   1.0000   0.0629
  -7.750  -0.8056   0.02193   0.01391  -0.0092   1.0000   0.0663
  -7.500  -0.7859   0.02043   0.01251  -0.0082   1.0000   0.0705
  -7.250  -0.7651   0.01967   0.01173  -0.0070   1.0000   0.0749
  -7.000  -0.7446   0.01885   0.01085  -0.0058   1.0000   0.0797
  -6.750  -0.7259   0.01794   0.01004  -0.0044   1.0000   0.0855
  -6.500  -0.7050   0.01736   0.00937  -0.0032   1.0000   0.0916
  -6.250  -0.6878   0.01641   0.00856  -0.0015   1.0000   0.0994
  -6.000  -0.6693   0.01568   0.00787   0.0001   1.0000   0.1094
  -5.750  -0.6509   0.01500   0.00725   0.0016   1.0000   0.1221
  -5.500  -0.6342   0.01422   0.00663   0.0034   1.0000   0.1417
  -5.250  -0.6194   0.01336   0.00602   0.0054   1.0000   0.1778
  -5.000  -0.6101   0.01233   0.00549   0.0081   1.0000   0.2504
  -4.750  -0.6008   0.01141   0.00519   0.0105   0.9968   0.3595
  -4.500  -0.5593   0.01092   0.00510   0.0072   0.9821   0.4651
  -4.250  -0.5161   0.01082   0.00508   0.0041   0.9690   0.5141
  -4.000  -0.4724   0.01081   0.00508   0.0010   0.9555   0.5471
  -3.750  -0.4295   0.01083   0.00502  -0.0019   0.9403   0.5725
  -3.500  -0.3882   0.01084   0.00502  -0.0044   0.9243   0.5918
  -3.250  -0.3508   0.01088   0.00501  -0.0060   0.9067   0.6089
  -3.000  -0.3182   0.01095   0.00501  -0.0066   0.8888   0.6246
  -2.750  -0.2894   0.01104   0.00504  -0.0064   0.8719   0.6396
  -2.500  -0.2625   0.01114   0.00506  -0.0058   0.8565   0.6540
  -2.250  -0.2358   0.01121   0.00512  -0.0051   0.8425   0.6663
  -2.000  -0.2094   0.01127   0.00514  -0.0044   0.8301   0.6778
  -1.750  -0.1837   0.01130   0.00510  -0.0037   0.8181   0.6889
  -1.500  -0.1578   0.01131   0.00509  -0.0030   0.8063   0.6985
  -1.250  -0.1315   0.01131   0.00505  -0.0025   0.7961   0.7070
  -1.000  -0.1053   0.01132   0.00501  -0.0019   0.7861   0.7164
  -0.750  -0.0791   0.01130   0.00499  -0.0014   0.7762   0.7243
  -0.500  -0.0525   0.01132   0.00494  -0.0009   0.7680   0.7333
  -0.250  -0.0264   0.01129   0.00495  -0.0005   0.7581   0.7410
   0.000   0.0000   0.01131   0.00492   0.0000   0.7500   0.7503
   0.250   0.0264   0.01129   0.00494   0.0005   0.7408   0.7581
   0.500   0.0526   0.01132   0.00494   0.0010   0.7333   0.7679
   0.750   0.0791   0.01130   0.00499   0.0014   0.7243   0.7762
   1.000   0.1054   0.01132   0.00501   0.0019   0.7164   0.7862
   1.250   0.1315   0.01131   0.00505   0.0025   0.7071   0.7961
   1.500   0.1578   0.01131   0.00509   0.0031   0.6984   0.8063
   1.750   0.1838   0.01130   0.00510   0.0037   0.6889   0.8181
   2.000   0.2094   0.01127   0.00514   0.0044   0.6778   0.8301
   2.250   0.2359   0.01121   0.00512   0.0051   0.6663   0.8424
   2.500   0.2626   0.01114   0.00506   0.0058   0.6539   0.8564
   2.750   0.2894   0.01104   0.00503   0.0064   0.6394   0.8720
   3.000   0.3182   0.01095   0.00502   0.0066   0.6246   0.8890
   3.250   0.3509   0.01088   0.00501   0.0060   0.6088   0.9069
   3.500   0.3882   0.01084   0.00502   0.0044   0.5917   0.9244
   3.750   0.4296   0.01083   0.00502   0.0019   0.5726   0.9403
   4.000   0.4725   0.01081   0.00507  -0.0010   0.5471   0.9555
   4.250   0.5162   0.01082   0.00509  -0.0041   0.5144   0.9690
   4.500   0.5595   0.01092   0.00510  -0.0072   0.4649   0.9822
   4.750   0.6009   0.01143   0.00519  -0.0105   0.3578   0.9971
   5.000   0.6099   0.01235   0.00549  -0.0080   0.2490   1.0000
   5.250   0.6195   0.01336   0.00602  -0.0054   0.1776   1.0000
   5.500   0.6343   0.01421   0.00662  -0.0034   0.1419   1.0000
   5.750   0.6510   0.01499   0.00725  -0.0016   0.1223   1.0000
   6.000   0.6693   0.01569   0.00788   0.0000   0.1092   1.0000
   6.250   0.6878   0.01642   0.00857   0.0015   0.0995   1.0000
   6.500   0.7049   0.01738   0.00939   0.0032   0.0915   1.0000
   6.750   0.7260   0.01794   0.01004   0.0044   0.0854   1.0000
   7.000   0.7444   0.01890   0.01089   0.0058   0.0795   1.0000
   7.250   0.7652   0.01967   0.01174   0.0070   0.0748   1.0000
   7.500   0.7860   0.02041   0.01248   0.0082   0.0703   1.0000
   7.750   0.8056   0.02186   0.01385   0.0093   0.0661   1.0000
   8.000   0.8272   0.02257   0.01470   0.0103   0.0629   1.0000
   8.250   0.8485   0.02351   0.01571   0.0113   0.0598   1.0000
   8.500   0.8694   0.02463   0.01678   0.0122   0.0568   1.0000
   8.750   0.8898   0.02629   0.01859   0.0131   0.0542   1.0000
   9.000   0.9098   0.02741   0.01990   0.0143   0.0517   1.0000
   9.250   0.9296   0.02871   0.02133   0.0153   0.0498   1.0000
   9.500   0.9489   0.02994   0.02260   0.0162   0.0478   1.0000
   9.750   0.9661   0.03269   0.02542   0.0170   0.0457   1.0000
  10.000   0.9793   0.03398   0.02708   0.0188   0.0443   1.0000
  10.250   0.9909   0.03616   0.02957   0.0206   0.0432   1.0000
  10.500   1.0000   0.03845   0.03215   0.0224   0.0422   1.0000
  10.750   1.0068   0.04082   0.03478   0.0242   0.0412   1.0000
  11.000   1.0208   0.04205   0.03603   0.0252   0.0398   1.0000
  11.250   1.0308   0.04383   0.03784   0.0264   0.0388   1.0000
  11.500   1.0291   0.04781   0.04201   0.0279   0.0380   1.0000
  11.750   1.0145   0.05098   0.04547   0.0308   0.0377   1.0000
  12.000   0.9977   0.05394   0.04868   0.0332   0.0376   1.0000
  12.250   0.9772   0.05765   0.05265   0.0340   0.0375   1.0000
  12.500   0.9610   0.06200   0.05717   0.0335   0.0377   1.0000
  12.750   0.9365   0.06715   0.06254   0.0316   0.0377   1.0000
  13.000   0.6565   0.13672   0.13285  -0.0141   0.0731   1.0000
  13.250   0.5426   0.12584   0.12233   0.0029   0.0785   1.0000
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