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FX 84-W-150 (fx84w150-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-150 (fx84w150-il)
Reynolds number: 200,000
Max Cl/Cd: 77.41 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w150-il-200000-n5.txt
Download as CSV file: xf-fx84w150-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-150                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4008   0.06216   0.05824  -0.1002   0.9068   0.0247
 -11.500  -0.4949   0.04418   0.03968  -0.1147   0.8877   0.0237
 -11.250  -0.5190   0.04035   0.03556  -0.1147   0.8763   0.0239
 -11.000  -0.5378   0.03757   0.03248  -0.1124   0.8664   0.0241
 -10.750  -0.5476   0.03525   0.02985  -0.1101   0.8578   0.0245
 -10.500  -0.5498   0.03289   0.02709  -0.1081   0.8510   0.0251
 -10.250  -0.5464   0.03063   0.02437  -0.1064   0.8447   0.0257
 -10.000  -0.5328   0.02933   0.02296  -0.1054   0.8386   0.0262
  -9.750  -0.5166   0.02836   0.02187  -0.1044   0.8337   0.0268
  -9.500  -0.4992   0.02737   0.02074  -0.1036   0.8284   0.0275
  -9.250  -0.4812   0.02633   0.01951  -0.1028   0.8228   0.0284
  -9.000  -0.4626   0.02522   0.01813  -0.1019   0.8180   0.0297
  -8.750  -0.4429   0.02412   0.01678  -0.1011   0.8135   0.0309
  -8.500  -0.4213   0.02342   0.01606  -0.1007   0.8080   0.0319
  -8.250  -0.3993   0.02270   0.01523  -0.1001   0.8033   0.0330
  -8.000  -0.3768   0.02190   0.01425  -0.0995   0.7996   0.0343
  -7.750  -0.3536   0.02114   0.01330  -0.0991   0.7943   0.0359
  -7.500  -0.3306   0.02047   0.01261  -0.0986   0.7893   0.0374
  -7.250  -0.3065   0.01998   0.01203  -0.0983   0.7852   0.0393
  -7.000  -0.2821   0.01940   0.01132  -0.0979   0.7813   0.0413
  -6.750  -0.2579   0.01880   0.01064  -0.0975   0.7761   0.0432
  -6.500  -0.2334   0.01834   0.01015  -0.0972   0.7715   0.0455
  -6.250  -0.2082   0.01790   0.00960  -0.0968   0.7678   0.0482
  -6.000  -0.1832   0.01742   0.00905  -0.0965   0.7633   0.0508
  -5.750  -0.1583   0.01701   0.00864  -0.0963   0.7585   0.0539
  -5.500  -0.1326   0.01664   0.00819  -0.0960   0.7542   0.0574
  -5.250  -0.1071   0.01621   0.00770  -0.0957   0.7507   0.0611
  -5.000  -0.0816   0.01590   0.00739  -0.0955   0.7456   0.0657
  -4.750  -0.0558   0.01557   0.00702  -0.0953   0.7410   0.0707
  -4.500  -0.0298   0.01525   0.00667  -0.0951   0.7370   0.0769
  -4.250  -0.0035   0.01496   0.00634  -0.0949   0.7331   0.0841
  -4.000   0.0226   0.01472   0.00609  -0.0948   0.7279   0.0928
  -3.750   0.0488   0.01444   0.00584  -0.0946   0.7234   0.1037
  -3.500   0.0755   0.01418   0.00557  -0.0945   0.7195   0.1173
  -3.250   0.1017   0.01396   0.00538  -0.0944   0.7148   0.1344
  -3.000   0.1280   0.01373   0.00521  -0.0943   0.7098   0.1558
  -2.750   0.1545   0.01348   0.00503  -0.0942   0.7056   0.1848
  -2.500   0.1812   0.01320   0.00483  -0.0942   0.7020   0.2229
  -2.250   0.2065   0.01291   0.00475  -0.0941   0.6968   0.2751
  -2.000   0.2316   0.01252   0.00464  -0.0939   0.6921   0.3535
  -1.750   0.2562   0.01205   0.00454  -0.0935   0.6882   0.4624
  -1.500   0.2800   0.01171   0.00458  -0.0928   0.6840   0.5722
  -1.250   0.3041   0.01157   0.00469  -0.0919   0.6789   0.6484
  -1.000   0.3293   0.01153   0.00474  -0.0911   0.6745   0.7001
  -0.750   0.3554   0.01152   0.00474  -0.0905   0.6709   0.7368
  -0.500   0.3805   0.01157   0.00484  -0.0898   0.6659   0.7653
  -0.250   0.4056   0.01162   0.00490  -0.0890   0.6610   0.7894
   0.000   0.4313   0.01165   0.00491  -0.0884   0.6568   0.8109
   0.250   0.4565   0.01171   0.00494  -0.0877   0.6526   0.8306
   0.500   0.4794   0.01179   0.00506  -0.0864   0.6474   0.8514
   0.750   0.5015   0.01184   0.00512  -0.0848   0.6428   0.8750
   1.000   0.5253   0.01187   0.00510  -0.0836   0.6389   0.8942
   1.250   0.5493   0.01194   0.00519  -0.0828   0.6334   0.9063
   1.500   0.5754   0.01198   0.00521  -0.0824   0.6283   0.9173
   1.750   0.6028   0.01201   0.00517  -0.0823   0.6240   0.9281
   2.000   0.6317   0.01207   0.00524  -0.0826   0.6189   0.9374
   2.250   0.6616   0.01214   0.00530  -0.0831   0.6136   0.9471
   2.500   0.6936   0.01219   0.00531  -0.0841   0.6092   0.9565
   2.750   0.7280   0.01228   0.00538  -0.0857   0.6043   0.9643
   3.000   0.7617   0.01238   0.00550  -0.0872   0.5986   0.9732
   3.250   0.7972   0.01246   0.00556  -0.0890   0.5940   0.9815
   3.500   0.8333   0.01256   0.00564  -0.0910   0.5891   0.9897
   3.750   0.8662   0.01269   0.00581  -0.0925   0.5830   1.0000
   4.000   0.8865   0.01281   0.00589  -0.0914   0.5781   1.0000
   4.250   0.9086   0.01295   0.00602  -0.0906   0.5728   1.0000
   4.500   0.9310   0.01311   0.00621  -0.0898   0.5666   1.0000
   4.750   0.9560   0.01325   0.00631  -0.0895   0.5613   1.0000
   5.000   0.9795   0.01344   0.00653  -0.0890   0.5552   1.0000
   5.250   1.0036   0.01361   0.00673  -0.0886   0.5490   1.0000
   5.500   1.0294   0.01378   0.00686  -0.0884   0.5440   1.0000
   5.750   1.0521   0.01400   0.00716  -0.0878   0.5372   1.0000
   6.000   1.0766   0.01419   0.00736  -0.0874   0.5312   1.0000
   6.250   1.0997   0.01441   0.00760  -0.0868   0.5240   1.0000
   6.500   1.1223   0.01461   0.00782  -0.0861   0.5158   1.0000
   6.750   1.1445   0.01485   0.00810  -0.0854   0.5080   1.0000
   7.000   1.1665   0.01509   0.00838  -0.0846   0.5005   1.0000
   7.250   1.1882   0.01535   0.00868  -0.0838   0.4932   1.0000
   7.500   1.2086   0.01562   0.00899  -0.0828   0.4850   1.0000
   7.750   1.2280   0.01592   0.00934  -0.0816   0.4763   1.0000
   8.000   1.2431   0.01623   0.00964  -0.0797   0.4630   1.0000
   8.250   1.2519   0.01661   0.00999  -0.0766   0.4465   1.0000
   8.500   1.2599   0.01710   0.01045  -0.0736   0.4292   1.0000
   8.750   1.2690   0.01767   0.01100  -0.0710   0.4129   1.0000
   9.000   1.2777   0.01833   0.01164  -0.0685   0.3960   1.0000
   9.250   1.2851   0.01910   0.01237  -0.0660   0.3780   1.0000
   9.500   1.2908   0.02001   0.01323  -0.0634   0.3591   1.0000
   9.750   1.2951   0.02108   0.01423  -0.0608   0.3385   1.0000
  10.000   1.2988   0.02226   0.01537  -0.0584   0.3171   1.0000
  10.250   1.2994   0.02370   0.01672  -0.0558   0.2941   1.0000
  10.500   1.2992   0.02530   0.01823  -0.0533   0.2705   1.0000
  10.750   1.2972   0.02712   0.01995  -0.0509   0.2467   1.0000
  11.000   1.2945   0.02911   0.02184  -0.0486   0.2227   1.0000
  11.250   1.2913   0.03125   0.02387  -0.0466   0.1995   1.0000
  11.500   1.2872   0.03357   0.02610  -0.0447   0.1772   1.0000
  11.750   1.2849   0.03588   0.02833  -0.0431   0.1553   1.0000
  12.000   1.2812   0.03842   0.03078  -0.0416   0.1349   1.0000
  12.250   1.2791   0.04094   0.03322  -0.0404   0.1163   1.0000
  12.500   1.2772   0.04353   0.03576  -0.0393   0.1006   1.0000
  12.750   1.2764   0.04612   0.03831  -0.0385   0.0880   1.0000
  13.000   1.2771   0.04867   0.04085  -0.0378   0.0783   1.0000
  13.250   1.2777   0.05128   0.04347  -0.0372   0.0704   1.0000
  13.500   1.2790   0.05391   0.04612  -0.0368   0.0638   1.0000
  13.750   1.2812   0.05650   0.04876  -0.0364   0.0583   1.0000
  14.000   1.2820   0.05930   0.05159  -0.0362   0.0540   1.0000
  14.250   1.2842   0.06202   0.05438  -0.0361   0.0504   1.0000
  14.500   1.2861   0.06481   0.05724  -0.0360   0.0473   1.0000
  15.000   1.2883   0.07081   0.06337  -0.0362   0.0423   1.0000
  15.250   1.2901   0.07379   0.06644  -0.0365   0.0401   1.0000
  15.500   1.2899   0.07708   0.06978  -0.0368   0.0383   1.0000
  15.750   1.2896   0.08046   0.07323  -0.0373   0.0368   1.0000
  16.000   1.2923   0.08347   0.07636  -0.0377   0.0352   1.0000
  16.250   1.2940   0.08664   0.07963  -0.0383   0.0338   1.0000
  16.500   1.2944   0.09005   0.08311  -0.0390   0.0325   1.0000
  16.750   1.2929   0.09376   0.08686  -0.0399   0.0314   1.0000
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