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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 100,000
Max Cl/Cd: 52.25 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61147-il-100000-n5.txt
Download as CSV file: xf-fx61147-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-147 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3699   0.09963   0.09475  -0.0501   1.0000   0.0223
 -10.250  -0.3730   0.09559   0.09077  -0.0509   1.0000   0.0221
 -10.000  -0.3781   0.09110   0.08634  -0.0521   1.0000   0.0219
  -9.750  -0.3862   0.08587   0.08118  -0.0540   1.0000   0.0216
  -9.500  -0.3971   0.08058   0.07595  -0.0561   1.0000   0.0213
  -9.250  -0.4148   0.07543   0.07083  -0.0579   1.0000   0.0210
  -9.000  -0.4383   0.07104   0.06647  -0.0586   1.0000   0.0208
  -8.750  -0.4625   0.06804   0.06349  -0.0574   1.0000   0.0205
  -8.500  -0.4925   0.06587   0.06134  -0.0545   1.0000   0.0205
  -8.250  -0.5051   0.06148   0.05682  -0.0576   0.9949   0.0203
  -8.000  -0.4973   0.05509   0.05004  -0.0642   0.9839   0.0201
  -7.750  -0.4836   0.04957   0.04408  -0.0689   0.9744   0.0200
  -7.500  -0.4673   0.04469   0.03871  -0.0718   0.9643   0.0202
  -7.250  -0.4469   0.04055   0.03406  -0.0739   0.9549   0.0204
  -7.000  -0.4174   0.03646   0.02937  -0.0766   0.9489   0.0210
  -6.750  -0.3914   0.03358   0.02582  -0.0774   0.9394   0.0226
  -6.500  -0.3599   0.03138   0.02351  -0.0796   0.9334   0.0245
  -6.000  -0.2964   0.02755   0.01914  -0.0817   0.9189   0.0284
  -5.750  -0.2665   0.02596   0.01738  -0.0821   0.9103   0.0315
  -5.500  -0.2342   0.02453   0.01593  -0.0831   0.9032   0.0343
  -5.250  -0.2024   0.02332   0.01460  -0.0838   0.8947   0.0378
  -5.000  -0.1720   0.02216   0.01340  -0.0844   0.8852   0.0422
  -4.750  -0.1358   0.02101   0.01221  -0.0864   0.8776   0.0472
  -4.500  -0.1043   0.02006   0.01118  -0.0875   0.8662   0.0553
  -4.250  -0.0690   0.01910   0.01016  -0.0894   0.8557   0.0696
  -4.000  -0.0298   0.01767   0.00910  -0.0926   0.8466   0.1401
  -3.750   0.0011   0.01575   0.00898  -0.0949   0.8346   0.5027
  -3.500   0.0289   0.01629   0.00963  -0.0933   0.8214   0.5894
  -3.250   0.0592   0.01718   0.01036  -0.0921   0.8080   0.6416
  -3.000   0.0829   0.01812   0.01121  -0.0890   0.7943   0.6652
  -2.750   0.1145   0.01828   0.01114  -0.0892   0.7807   0.6763
  -2.500   0.1497   0.01820   0.01079  -0.0907   0.7670   0.6860
  -2.250   0.1790   0.01826   0.01066  -0.0905   0.7532   0.6908
  -2.000   0.2106   0.01823   0.01043  -0.0912   0.7396   0.6975
  -1.750   0.2424   0.01819   0.01017  -0.0921   0.7261   0.7037
  -1.500   0.2711   0.01821   0.01002  -0.0921   0.7133   0.7085
  -1.250   0.3029   0.01816   0.00978  -0.0932   0.7005   0.7156
  -1.000   0.3293   0.01819   0.00969  -0.0928   0.6882   0.7196
  -0.750   0.3567   0.01823   0.00959  -0.0927   0.6767   0.7243
  -0.500   0.3886   0.01821   0.00941  -0.0940   0.6659   0.7305
  -0.250   0.4150   0.01826   0.00934  -0.0936   0.6556   0.7341
   0.000   0.4413   0.01830   0.00931  -0.0934   0.6452   0.7382
   0.250   0.4711   0.01835   0.00923  -0.0941   0.6359   0.7434
   0.500   0.4993   0.01839   0.00918  -0.0944   0.6265   0.7476
   0.750   0.5246   0.01847   0.00920  -0.0939   0.6171   0.7512
   1.000   0.5533   0.01854   0.00917  -0.0943   0.6091   0.7555
   1.250   0.5827   0.01862   0.00920  -0.0951   0.5995   0.7605
   1.500   0.6079   0.01871   0.00924  -0.0946   0.5916   0.7636
   1.750   0.6338   0.01880   0.00931  -0.0944   0.5832   0.7673
   2.000   0.6621   0.01892   0.00939  -0.0947   0.5755   0.7714
   2.250   0.6910   0.01904   0.00947  -0.0953   0.5675   0.7756
   2.500   0.7160   0.01915   0.00959  -0.0949   0.5603   0.7786
   2.750   0.7422   0.01928   0.00974  -0.0948   0.5529   0.7821
   3.000   0.7700   0.01944   0.00988  -0.0951   0.5461   0.7861
   3.250   0.7981   0.01960   0.01006  -0.0956   0.5386   0.7900
   3.750   0.8483   0.01991   0.01045  -0.0949   0.5247   0.7964
   4.000   0.8763   0.02010   0.01062  -0.0952   0.5184   0.8002
   4.250   0.9037   0.02032   0.01092  -0.0956   0.5105   0.8040
   4.750   0.9528   0.02070   0.01145  -0.0947   0.4969   0.8103
   5.000   0.9803   0.02091   0.01168  -0.0950   0.4908   0.8140
   5.250   1.0068   0.02119   0.01209  -0.0952   0.4835   0.8177
   5.500   1.0319   0.02141   0.01237  -0.0949   0.4771   0.8208
   5.750   1.0558   0.02167   0.01275  -0.0944   0.4705   0.8243
   6.000   1.0811   0.02194   0.01312  -0.0943   0.4637   0.8279
   6.250   1.1082   0.02225   0.01353  -0.0945   0.4575   0.8317
   6.500   1.1313   0.02256   0.01399  -0.0940   0.4504   0.8350
   6.750   1.1567   0.02282   0.01431  -0.0938   0.4447   0.8385
   7.000   1.1787   0.02319   0.01488  -0.0931   0.4369   0.8423
   7.250   1.2059   0.02349   0.01528  -0.0933   0.4308   0.8461
   7.500   1.2255   0.02385   0.01585  -0.0922   0.4223   0.8498
   7.750   1.2483   0.02409   0.01616  -0.0915   0.4146   0.8537
   8.000   1.2677   0.02444   0.01671  -0.0904   0.4048   0.8580
   8.250   1.2880   0.02477   0.01722  -0.0894   0.3951   0.8621
   8.500   1.3063   0.02500   0.01754  -0.0879   0.3852   0.8663
   8.750   1.3215   0.02533   0.01805  -0.0860   0.3735   0.8715
   9.000   1.3366   0.02571   0.01861  -0.0843   0.3616   0.8767
   9.250   1.3488   0.02607   0.01912  -0.0819   0.3495   0.8821
   9.500   1.3584   0.02648   0.01965  -0.0792   0.3358   0.8883
   9.750   1.3639   0.02695   0.02024  -0.0758   0.3207   0.8958
  10.000   1.3679   0.02756   0.02099  -0.0725   0.3044   0.9054
  10.500   1.3670   0.02907   0.02268  -0.0650   0.2715   0.9697
  10.750   1.3724   0.03042   0.02410  -0.0633   0.2510   1.0000
  11.000   1.3742   0.03211   0.02580  -0.0615   0.2299   1.0000
  11.250   1.3729   0.03417   0.02786  -0.0598   0.2072   1.0000
  11.500   1.3675   0.03672   0.03038  -0.0582   0.1841   1.0000
  11.750   1.3591   0.03977   0.03338  -0.0570   0.1615   1.0000
  12.000   1.3478   0.04336   0.03691  -0.0561   0.1430   1.0000
  12.250   1.3362   0.04730   0.04083  -0.0558   0.1261   1.0000
  12.500   1.3242   0.05156   0.04509  -0.0559   0.1114   1.0000
  12.750   1.3117   0.05613   0.04967  -0.0564   0.0987   1.0000
  13.000   1.2994   0.06090   0.05445  -0.0572   0.0883   1.0000
  13.250   1.2868   0.06591   0.05948  -0.0582   0.0793   1.0000
  13.500   1.2774   0.07070   0.06434  -0.0594   0.0705   1.0000
  13.750   1.2673   0.07572   0.06941  -0.0608   0.0640   1.0000
  14.000   1.2575   0.08086   0.07460  -0.0624   0.0580   1.0000
  14.250   1.2491   0.08591   0.07976  -0.0640   0.0523   1.0000
  14.500   1.2412   0.09103   0.08494  -0.0658   0.0469   1.0000
  14.750   1.2341   0.09614   0.09012  -0.0677   0.0422   1.0000
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