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WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il)
Reynolds number: 50,000
Max Cl/Cd: -0.14 at α=-2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w343-il-50000.txt
Download as CSV file: xf-fx77w343-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-343 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.1814   0.15600   0.14910  -0.0456   0.6639   0.2248
 -14.000  -0.1703   0.15147   0.14456  -0.0493   0.6630   0.2231
 -13.750  -0.5505   0.08912   0.08144  -0.0688   0.6759   0.2051
 -13.500  -0.5956   0.08228   0.07423  -0.0693   0.6762   0.2071
 -13.250  -0.6272   0.07733   0.06890  -0.0693   0.6760   0.2100
 -13.000  -0.5679   0.07878   0.07063  -0.0709   0.6729   0.2196
 -12.750  -0.5614   0.07680   0.06856  -0.0714   0.6719   0.2273
 -12.500  -0.5497   0.07553   0.06726  -0.0719   0.6709   0.2374
 -12.250  -0.5154   0.07609   0.06799  -0.0725   0.6694   0.2514
 -12.000  -0.4800   0.07716   0.06927  -0.0730   0.6683   0.2678
 -11.750  -0.4529   0.07793   0.07020  -0.0738   0.6678   0.2864
 -11.500  -0.3835   0.08357   0.07631  -0.0762   0.6668   0.3105
 -11.250  -0.8355   0.08859   0.08075  -0.0549   0.8782   0.2231
 -11.000  -0.7497   0.08998   0.08247  -0.0612   0.8515   0.2445
 -10.750  -0.6910   0.09029   0.08300  -0.0647   0.8279   0.2698
 -10.500  -0.6334   0.09058   0.08367  -0.0663   0.7905   0.3045
 -10.250  -0.0972   0.11956   0.11259  -0.0802   0.6665   0.3836
 -10.000  -0.0983   0.12661   0.11986  -0.0836   0.6819   0.3892
  -9.750  -0.1018   0.12859   0.12185  -0.0828   0.6922   0.4042
  -9.500  -0.0592   0.13172   0.12483  -0.0823   0.6896   0.4241
  -8.750  -0.6538   0.11456   0.10902  -0.0339   0.8885   0.4017
  -8.500  -0.6180   0.11953   0.11391  -0.0322   0.8693   0.4200
  -7.750  -0.4673   0.13957   0.13359  -0.0315   0.8264   0.4631
  -7.500  -0.4860   0.13894   0.13291  -0.0261   0.8134   0.4797
  -7.250  -0.4367   0.14431   0.13814  -0.0275   0.8048   0.4994
  -7.000  -0.3925   0.14924   0.14300  -0.0265   0.7886   0.5089
  -6.750  -0.3429   0.15363   0.14725  -0.0289   0.7818   0.5315
  -6.500  -0.3429   0.15442   0.14799  -0.0248   0.7680   0.5438
  -6.250  -0.2966   0.15805   0.15150  -0.0267   0.7606   0.5662
  -6.000  -0.2584   0.16229   0.15560  -0.0287   0.7575   0.5949
  -5.750  -0.2719   0.16127   0.15459  -0.0228   0.7424   0.6054
  -5.500  -0.1734   0.17147   0.16472  -0.0268   0.7364   0.6889
  -5.250  -0.1703   0.16965   0.16288  -0.0247   0.7256   0.6996
  -5.000  -0.1546   0.16951   0.16265  -0.0248   0.7186   0.7203
  -4.750  -0.1309   0.17012   0.16312  -0.0264   0.7146   0.7410
  -4.250  -0.1290   0.16883   0.16170  -0.0229   0.6983   0.7702
  -4.000  -0.1097   0.16897   0.16173  -0.0239   0.6935   0.7873
  -3.750  -0.0845   0.17047   0.16309  -0.0259   0.6908   0.8066
  -3.500  -0.1046   0.16864   0.16126  -0.0213   0.6810   0.8190
  -3.250  -0.0859   0.16815   0.16068  -0.0225   0.6745   0.8342
  -3.000  -0.0606   0.16892   0.16133  -0.0244   0.6707   0.8527
  -2.750  -0.0236   0.17110   0.16338  -0.0283   0.6685   0.8722
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