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FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 74-130 WP1 (fx74130wp1-il)
Reynolds number: 200,000
Max Cl/Cd: 72.01 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp1-il-200000.txt
Download as CSV file: xf-fx74130wp1-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-130 WP1                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1623   0.11026   0.10650  -0.1080   0.9564   0.0352
 -11.250  -0.1573   0.10675   0.10299  -0.1137   0.9529   0.0360
 -11.000  -0.1491   0.10303   0.09927  -0.1186   0.9500   0.0363
 -10.750  -0.1396   0.09914   0.09537  -0.1232   0.9476   0.0364
 -10.250  -0.1183   0.08949   0.08569  -0.1263   0.9444   0.0382
 -10.000  -0.1107   0.08675   0.08295  -0.1271   0.9410   0.0388
  -9.750  -0.1023   0.08394   0.08013  -0.1283   0.9380   0.0400
  -9.500  -0.0956   0.08075   0.07694  -0.1304   0.9351   0.0418
  -9.250  -0.0901   0.07720   0.07339  -0.1334   0.9321   0.0435
  -9.000  -0.0896   0.07377   0.06998  -0.1361   0.9285   0.0448
  -8.750  -0.0946   0.07053   0.06676  -0.1381   0.9242   0.0453
  -8.500  -0.1038   0.06649   0.06272  -0.1419   0.9194   0.0460
  -8.250  -0.1191   0.06367   0.05986  -0.1429   0.9146   0.0467
  -8.000  -0.1401   0.06222   0.05832  -0.1408   0.9089   0.0474
  -7.750  -0.1547   0.06116   0.05698  -0.1393   0.9039   0.0482
  -7.500  -0.1637   0.06027   0.05588  -0.1363   0.8997   0.0485
  -7.250  -0.1798   0.05776   0.05328  -0.1322   0.8944   0.0489
  -7.000  -0.1732   0.05285   0.04853  -0.1319   0.8921   0.0506
  -6.750  -0.1607   0.05058   0.04624  -0.1315   0.8899   0.0522
  -6.500  -0.1470   0.04830   0.04384  -0.1314   0.8879   0.0552
  -6.250  -0.1768   0.04901   0.04456  -0.1223   0.8798   0.0552
  -5.750  -0.1545   0.04395   0.03886  -0.1205   0.8747   0.0644
  -5.500  -0.1981   0.04546   0.04037  -0.1080   0.8648   0.0640
  -5.250  -0.1797   0.04345   0.03838  -0.1080   0.8629   0.0675
  -5.000  -0.1557   0.04115   0.03576  -0.1089   0.8614   0.0794
  -4.750  -0.1263   0.03905   0.03335  -0.1106   0.8603   0.0927
  -3.250  -0.0541   0.02964   0.02186  -0.0906   0.8386   0.0354
  -3.000  -0.0290   0.02864   0.02069  -0.0900   0.8363   0.0356
  -2.750   0.0015   0.02783   0.01975  -0.0904   0.8345   0.0363
  -2.500   0.0323   0.02661   0.01860  -0.0912   0.8332   0.0422
  -2.250   0.0655   0.02599   0.01794  -0.0923   0.8322   0.0468
  -2.000   0.0661   0.02645   0.01838  -0.0882   0.8271   0.0488
  -1.750   0.0828   0.02628   0.01820  -0.0868   0.8233   0.0618
  -1.500   0.0978   0.02359   0.01836  -0.0853   0.8216   0.7014
  -1.250   0.1112   0.02445   0.01922  -0.0806   0.8191   0.8339
  -1.000   0.1187   0.02485   0.01963  -0.0741   0.8173   0.8721
  -0.750   0.0983   0.02564   0.02045  -0.0659   0.8091   0.8880
  -0.500   0.0970   0.02568   0.02048  -0.0586   0.8057   0.9165
  -0.250   0.2207   0.02648   0.02108  -0.0742   0.8082   0.9859
   0.000   0.2689   0.02660   0.02107  -0.0788   0.8066   0.9890
   0.250   0.3104   0.02666   0.02103  -0.0820   0.8051   0.9912
   0.500   0.3514   0.02668   0.02096  -0.0849   0.8039   0.9928
   0.750   0.3929   0.02669   0.02089  -0.0877   0.8030   0.9939
   1.000   0.3872   0.02768   0.02189  -0.0840   0.7931   0.9999
   1.250   0.4160   0.02770   0.02186  -0.0845   0.7909   1.0000
   1.500   0.4497   0.02767   0.02180  -0.0857   0.7895   1.0000
   1.750   0.4863   0.02765   0.02175  -0.0875   0.7884   1.0000
   2.000   0.4436   0.02836   0.02247  -0.0760   0.7764   1.0000
   2.250   0.4232   0.02885   0.02296  -0.0684   0.7669   1.0000
   2.500   0.4466   0.02882   0.02291  -0.0678   0.7636   1.0000
   2.750   0.4805   0.02868   0.02276  -0.0688   0.7617   1.0000
   3.000   0.5177   0.02854   0.02263  -0.0704   0.7605   1.0000
   3.250   0.5002   0.02907   0.02316  -0.0637   0.7492   1.0000
   3.500   0.5379   0.02888   0.02298  -0.0653   0.7476   1.0000
   3.750   0.5766   0.02868   0.02281  -0.0671   0.7462   1.0000
   4.000   0.5798   0.02925   0.02339  -0.0642   0.7354   1.0000
   4.250   0.6197   0.02892   0.02312  -0.0661   0.7339   1.0000
   4.500   0.6610   0.02849   0.02274  -0.0682   0.7326   1.0000
   4.750   0.6698   0.02907   0.02336  -0.0662   0.7218   1.0000
   5.000   0.7120   0.02845   0.02284  -0.0682   0.7203   1.0000
   5.250   0.7269   0.02887   0.02332  -0.0670   0.7104   1.0000
   5.500   0.7702   0.02796   0.02251  -0.0690   0.7082   1.0000
   5.750   0.8179   0.02671   0.02139  -0.0713   0.7069   1.0000
   6.000   0.8381   0.02667   0.02144  -0.0704   0.6968   1.0000
   6.250   0.8912   0.02460   0.01951  -0.0728   0.6950   1.0000
   6.500   0.9547   0.02133   0.01641  -0.0758   0.6940   1.0000
   6.750   0.9890   0.01971   0.01492  -0.0757   0.6830   1.0000
   7.000   1.0304   0.01758   0.01290  -0.0762   0.6680   1.0000
   7.250   1.0593   0.01672   0.01215  -0.0758   0.6464   1.0000
   7.500   1.0852   0.01621   0.01167  -0.0750   0.6133   1.0000
   7.750   1.1155   0.01549   0.01048  -0.0741   0.5178   1.0000
   8.000   1.1081   0.01704   0.01141  -0.0692   0.4256   1.0000
   8.250   1.0957   0.01914   0.01302  -0.0644   0.3469   1.0000
   8.500   1.0835   0.02148   0.01487  -0.0601   0.2674   1.0000
   8.750   1.0727   0.02398   0.01682  -0.0563   0.1832   1.0000
   9.000   1.0645   0.02655   0.01883  -0.0530   0.1079   1.0000
   9.250   1.0636   0.02877   0.02076  -0.0503   0.0756   1.0000
   9.500   1.0691   0.03056   0.02251  -0.0485   0.0629   1.0000
   9.750   1.0786   0.03209   0.02411  -0.0470   0.0559   1.0000
  10.000   1.0852   0.03391   0.02591  -0.0453   0.0509   1.0000
  10.250   1.0972   0.03540   0.02748  -0.0440   0.0469   1.0000
  10.500   1.1109   0.03676   0.02890  -0.0430   0.0428   1.0000
  10.750   1.1262   0.03847   0.03057  -0.0419   0.0394   1.0000
  11.000   1.1472   0.03977   0.03200  -0.0413   0.0366   1.0000
  11.250   1.1661   0.04106   0.03344  -0.0407   0.0335   1.0000
  11.500   1.1876   0.04255   0.03494  -0.0403   0.0308   1.0000
  11.750   1.2180   0.04470   0.03729  -0.0405   0.0276   1.0000
  12.000   1.2393   0.04666   0.03951  -0.0399   0.0260   1.0000
  12.250   1.2594   0.04908   0.04219  -0.0394   0.0245   1.0000
  12.500   1.2756   0.05181   0.04517  -0.0386   0.0236   1.0000
  12.750   1.2840   0.05458   0.04815  -0.0375   0.0227   1.0000
  13.000   1.2920   0.05796   0.05170  -0.0367   0.0217   1.0000
  13.250   1.2894   0.06366   0.05780  -0.0352   0.0211   1.0000
  13.750   1.2591   0.07210   0.06687  -0.0313   0.0207   1.0000
  14.000   1.2441   0.07667   0.07172  -0.0299   0.0207   1.0000
  14.250   1.0951   0.07465   0.07030  -0.0181   0.0222   1.0000
  14.500   1.0667   0.07902   0.07496  -0.0175   0.0223   1.0000
  14.750   1.0430   0.08357   0.07974  -0.0178   0.0221   1.0000
  15.000   0.9742   0.09444   0.09125  -0.0207   0.0246   1.0000
  15.250   0.9428   0.10143   0.09848  -0.0240   0.0249   1.0000
  15.500   0.9086   0.10967   0.10693  -0.0286   0.0264   1.0000
  15.750   0.8784   0.11797   0.11539  -0.0340   0.0271   1.0000
  16.000   0.8480   0.12724   0.12478  -0.0402   0.0277   1.0000
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