Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il)
Reynolds number: 1,000,000
Max Cl/Cd: 148.74 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s161-il-1000000.txt
Download as CSV file: xf-fx66s161-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-161 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6261   0.07463   0.07267  -0.0586   1.0000   0.0075
 -13.750  -0.6646   0.06352   0.06130  -0.0660   1.0000   0.0073
 -13.500  -0.6928   0.05572   0.05335  -0.0712   1.0000   0.0074
 -13.250  -0.6968   0.05195   0.04954  -0.0737   1.0000   0.0076
 -13.000  -0.7239   0.04529   0.04266  -0.0776   1.0000   0.0075
 -12.750  -0.7335   0.04133   0.03859  -0.0797   1.0000   0.0075
 -12.500  -0.7352   0.03612   0.03314  -0.0853   0.9603   0.0075
 -12.250  -0.6276   0.03136   0.02801  -0.1112   0.8981   0.0080
 -12.000  -0.6383   0.02828   0.02434  -0.1113   0.8122   0.0079
 -11.750  -0.6403   0.02677   0.02259  -0.1100   0.7755   0.0080
 -11.500  -0.6372   0.02590   0.02157  -0.1085   0.7492   0.0082
 -11.000  -0.6334   0.02368   0.01899  -0.1038   0.7148   0.0083
 -10.750  -0.6238   0.02246   0.01759  -0.1022   0.7016   0.0084
 -10.500  -0.6103   0.02144   0.01643  -0.1010   0.6900   0.0086
 -10.250  -0.5948   0.02051   0.01535  -0.0999   0.6794   0.0087
 -10.000  -0.5775   0.01969   0.01438  -0.0990   0.6694   0.0089
  -9.750  -0.5592   0.01882   0.01338  -0.0981   0.6602   0.0091
  -9.500  -0.5400   0.01802   0.01244  -0.0973   0.6519   0.0092
  -9.250  -0.5194   0.01732   0.01162  -0.0966   0.6441   0.0094
  -9.000  -0.4979   0.01669   0.01088  -0.0959   0.6372   0.0095
  -8.750  -0.4761   0.01603   0.01012  -0.0953   0.6306   0.0098
  -8.500  -0.4582   0.01492   0.00886  -0.0943   0.6243   0.0102
  -8.250  -0.4344   0.01441   0.00831  -0.0940   0.6185   0.0107
  -8.000  -0.4100   0.01401   0.00785  -0.0937   0.6124   0.0112
  -7.750  -0.3852   0.01362   0.00739  -0.0934   0.6070   0.0117
  -7.500  -0.3598   0.01324   0.00695  -0.0932   0.6014   0.0123
  -7.250  -0.3346   0.01289   0.00651  -0.0929   0.5961   0.0127
  -7.000  -0.3105   0.01229   0.00582  -0.0925   0.5914   0.0136
  -6.750  -0.2847   0.01190   0.00539  -0.0924   0.5866   0.0147
  -6.500  -0.2584   0.01165   0.00509  -0.0923   0.5820   0.0159
  -6.250  -0.2313   0.01146   0.00484  -0.0922   0.5778   0.0171
  -6.000  -0.2055   0.01100   0.00435  -0.0920   0.5737   0.0199
  -5.750  -0.1782   0.01081   0.00412  -0.0920   0.5695   0.0219
  -5.500  -0.1518   0.01053   0.00378  -0.0919   0.5654   0.0252
  -5.250  -0.1241   0.01035   0.00358  -0.0920   0.5621   0.0282
  -5.000  -0.0968   0.01009   0.00332  -0.0920   0.5588   0.0333
  -4.750  -0.0692   0.00988   0.00309  -0.0920   0.5552   0.0403
  -4.500  -0.0422   0.00963   0.00288  -0.0920   0.5515   0.0559
  -4.250  -0.0153   0.00933   0.00267  -0.0921   0.5482   0.0866
  -4.000   0.0114   0.00888   0.00244  -0.0922   0.5454   0.1445
  -3.750   0.0373   0.00828   0.00216  -0.0923   0.5427   0.2366
  -3.500   0.0637   0.00783   0.00200  -0.0924   0.5399   0.3271
  -3.250   0.0912   0.00766   0.00191  -0.0924   0.5371   0.3697
  -3.000   0.1191   0.00756   0.00188  -0.0925   0.5342   0.4053
  -2.750   0.1478   0.00751   0.00186  -0.0927   0.5319   0.4292
  -2.500   0.1766   0.00748   0.00185  -0.0929   0.5295   0.4471
  -2.250   0.2053   0.00749   0.00185  -0.0931   0.5271   0.4597
  -2.000   0.2340   0.00752   0.00185  -0.0932   0.5248   0.4720
  -1.750   0.2626   0.00758   0.00187  -0.0934   0.5224   0.4832
  -1.500   0.2910   0.00764   0.00191  -0.0935   0.5198   0.4927
  -1.250   0.3200   0.00767   0.00192  -0.0937   0.5180   0.5007
  -1.000   0.3487   0.00765   0.00192  -0.0939   0.5159   0.5072
  -0.750   0.3775   0.00768   0.00193  -0.0941   0.5135   0.5125
  -0.500   0.4062   0.00770   0.00192  -0.0943   0.5112   0.5165
  -0.250   0.4346   0.00772   0.00193  -0.0945   0.5087   0.5203
   0.000   0.4628   0.00780   0.00197  -0.0946   0.5060   0.5240
   0.250   0.4916   0.00783   0.00199  -0.0948   0.5043   0.5276
   0.500   0.5204   0.00785   0.00201  -0.0951   0.5026   0.5310
   0.750   0.5490   0.00785   0.00204  -0.0953   0.5008   0.5349
   1.000   0.5776   0.00787   0.00207  -0.0955   0.4987   0.5390
   1.250   0.6062   0.00791   0.00210  -0.0957   0.4967   0.5430
   1.500   0.6346   0.00795   0.00214  -0.0959   0.4947   0.5470
   1.750   0.6627   0.00801   0.00219  -0.0960   0.4924   0.5511
   2.000   0.6908   0.00811   0.00228  -0.0962   0.4900   0.5554
   2.250   0.7195   0.00813   0.00233  -0.0964   0.4886   0.5596
   2.500   0.7479   0.00814   0.00238  -0.0966   0.4869   0.5644
   2.750   0.7763   0.00816   0.00244  -0.0968   0.4850   0.5694
   3.000   0.8046   0.00820   0.00250  -0.0970   0.4831   0.5746
   3.250   0.8328   0.00823   0.00257  -0.0972   0.4811   0.5805
   3.500   0.8607   0.00829   0.00265  -0.0973   0.4789   0.5874
   3.750   0.8884   0.00839   0.00276  -0.0974   0.4762   0.5945
   4.000   0.9164   0.00842   0.00285  -0.0976   0.4741   0.6034
   4.250   0.9445   0.00843   0.00293  -0.0977   0.4719   0.6130
   4.500   0.9724   0.00845   0.00302  -0.0979   0.4694   0.6246
   4.750   1.0002   0.00848   0.00311  -0.0980   0.4669   0.6383
   5.000   1.0276   0.00853   0.00321  -0.0981   0.4645   0.6532
   5.250   1.0546   0.00862   0.00335  -0.0981   0.4617   0.6707
   5.500   1.0820   0.00864   0.00349  -0.0982   0.4595   0.6925
   5.750   1.1093   0.00863   0.00362  -0.0982   0.4572   0.7201
   6.000   1.1360   0.00861   0.00375  -0.0981   0.4544   0.7590
   6.250   1.1613   0.00855   0.00389  -0.0977   0.4514   0.8174
   6.500   1.1901   0.00838   0.00403  -0.0980   0.4483   1.0000
   6.750   1.2171   0.00847   0.00415  -0.0980   0.4440   1.0000
   7.000   1.2441   0.00851   0.00423  -0.0980   0.4376   1.0000
   7.250   1.2699   0.00861   0.00433  -0.0978   0.4287   1.0000
   7.500   1.2955   0.00871   0.00440  -0.0976   0.4132   1.0000
   7.750   1.3196   0.00892   0.00455  -0.0972   0.3949   1.0000
   8.000   1.3423   0.00923   0.00480  -0.0965   0.3774   1.0000
   8.250   1.3640   0.00960   0.00510  -0.0957   0.3578   1.0000
   8.500   1.3822   0.01014   0.00551  -0.0943   0.3290   1.0000
   8.750   1.3985   0.01078   0.00602  -0.0926   0.3025   1.0000
   9.000   1.4082   0.01172   0.00672  -0.0899   0.2585   1.0000
   9.250   1.4048   0.01314   0.00780  -0.0852   0.2006   1.0000
   9.500   1.3934   0.01445   0.00886  -0.0789   0.1573   1.0000
   9.750   1.3811   0.01586   0.01007  -0.0729   0.1220   1.0000
  10.000   1.3683   0.01747   0.01155  -0.0677   0.0916   1.0000
  10.250   1.3561   0.01939   0.01335  -0.0634   0.0674   1.0000
  10.500   1.3482   0.02145   0.01536  -0.0603   0.0504   1.0000
  10.750   1.3408   0.02381   0.01767  -0.0579   0.0356   1.0000
  11.000   1.3363   0.02622   0.02006  -0.0562   0.0259   1.0000
  11.250   1.3342   0.02859   0.02243  -0.0549   0.0198   1.0000
  11.500   1.3350   0.03080   0.02467  -0.0539   0.0165   1.0000
  11.750   1.3344   0.03320   0.02711  -0.0529   0.0143   1.0000
  12.000   1.3381   0.03525   0.02922  -0.0521   0.0131   1.0000
  12.250   1.3392   0.03757   0.03158  -0.0514   0.0122   1.0000
  12.500   1.3348   0.04044   0.03451  -0.0505   0.0106   1.0000
  12.750   1.3379   0.04265   0.03679  -0.0500   0.0103   1.0000
  13.000   1.3407   0.04494   0.03915  -0.0496   0.0095   1.0000
  13.250   1.3415   0.04751   0.04176  -0.0492   0.0089   1.0000
  13.500   1.3399   0.05039   0.04470  -0.0488   0.0083   1.0000
  13.750   1.3378   0.05343   0.04781  -0.0486   0.0076   1.0000
  14.000   1.3415   0.05588   0.05032  -0.0485   0.0070   1.0000
  14.250   1.3440   0.05851   0.05301  -0.0485   0.0069   1.0000
  14.500   1.3458   0.06127   0.05583  -0.0485   0.0066   1.0000
  14.750   1.3469   0.06417   0.05878  -0.0486   0.0063   1.0000
  15.000   1.3461   0.06735   0.06201  -0.0488   0.0059   1.0000
  15.250   1.3387   0.07142   0.06617  -0.0491   0.0056   1.0000
  15.500   1.3432   0.07405   0.06887  -0.0495   0.0054   1.0000
  15.750   1.3439   0.07723   0.07213  -0.0499   0.0053   1.0000
  16.000   1.3461   0.08024   0.07521  -0.0504   0.0051   1.0000
  16.250   1.3481   0.08332   0.07835  -0.0509   0.0049   1.0000
  16.500   1.3479   0.08676   0.08186  -0.0516   0.0048   1.0000
  16.750   1.3493   0.09001   0.08518  -0.0523   0.0047   1.0000
  17.000   1.3498   0.09345   0.08868  -0.0531   0.0045   1.0000
  17.250   1.3507   0.09685   0.09214  -0.0540   0.0044   1.0000
  17.500   1.3510   0.10038   0.09574  -0.0549   0.0043   1.0000
  17.750   1.3493   0.10427   0.09970  -0.0560   0.0042   1.0000
  18.000   1.3485   0.10806   0.10356  -0.0572   0.0042   1.0000
  18.250   1.3393   0.11320   0.10879  -0.0589   0.0040   1.0000
  18.500   1.3337   0.11776   0.11345  -0.0604   0.0039   1.0000
<< Back to FX 66-S-161 AIRFOIL (fx66s161-il)

Polar data table (+)

Polar graphs


<< Back to FX 66-S-161 AIRFOIL (fx66s161-il)