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WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il)
Reynolds number: 500,000
Max Cl/Cd: 121.31 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx05h126-il-500000.txt
Download as CSV file: xf-fx05h126-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 05-H-126 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4114   0.08770   0.08435  -0.0036   0.6055   0.0219
  -8.000  -0.4194   0.08311   0.07980  -0.0080   0.6047   0.0220
  -7.750  -0.4241   0.07858   0.07524  -0.0119   0.6040   0.0220
  -7.500  -0.4224   0.07348   0.07007  -0.0156   0.6032   0.0221
  -7.250  -0.4280   0.06691   0.06344  -0.0181   0.6025   0.0224
  -7.000  -0.4202   0.06395   0.06044  -0.0187   0.6017   0.0227
  -6.750  -0.4090   0.06128   0.05774  -0.0194   0.6010   0.0231
  -6.500  -0.3964   0.05835   0.05476  -0.0204   0.6002   0.0235
  -6.250  -0.3827   0.05513   0.05145  -0.0214   0.5994   0.0241
  -6.000  -0.3677   0.05163   0.04783  -0.0223   0.5985   0.0250
  -5.750  -0.3457   0.04657   0.04232  -0.0229   0.5977   0.0278
  -5.500  -0.3384   0.04003   0.03545  -0.0229   0.5969   0.0286
  -5.250  -0.3184   0.03827   0.03368  -0.0230   0.5960   0.0292
  -5.000  -0.2971   0.03678   0.03213  -0.0230   0.5950   0.0301
  -4.750  -0.2753   0.03483   0.03003  -0.0228   0.5940   0.0315
  -4.500  -0.2534   0.03166   0.02618  -0.0212   0.5930   0.0358
  -4.250  -0.2322   0.02911   0.02361  -0.0212   0.5919   0.0369
  -4.000  -0.2081   0.02786   0.02230  -0.0211   0.5910   0.0383
  -3.750  -0.1830   0.02670   0.02097  -0.0207   0.5901   0.0410
  -3.500  -0.1593   0.02481   0.01866  -0.0197   0.5893   0.0460
  -3.250  -0.1339   0.02363   0.01745  -0.0197   0.5885   0.0477
  -3.000  -0.1076   0.02289   0.01659  -0.0194   0.5876   0.0510
  -2.750  -0.0791   0.01712   0.00977  -0.0165   0.5868   0.0287
  -2.500  -0.0515   0.01626   0.00883  -0.0163   0.5861   0.0287
  -2.250  -0.0241   0.01546   0.00800  -0.0161   0.5852   0.0289
  -2.000   0.0029   0.01484   0.00738  -0.0159   0.5843   0.0294
  -1.750   0.0300   0.01440   0.00694  -0.0158   0.5832   0.0303
  -1.500   0.0573   0.01408   0.00663  -0.0157   0.5820   0.0317
  -1.250   0.0843   0.01377   0.00630  -0.0155   0.5809   0.0325
  -1.000   0.1115   0.01351   0.00603  -0.0153   0.5799   0.0336
  -0.750   0.1390   0.01333   0.00582  -0.0152   0.5788   0.0348
  -0.500   0.1662   0.01311   0.00558  -0.0150   0.5779   0.0369
  -0.250   0.1938   0.01297   0.00545  -0.0149   0.5768   0.0412
   0.000   0.2214   0.01282   0.00534  -0.0148   0.5757   0.0558
   0.250   0.2442   0.01199   0.00523  -0.0142   0.5747   0.2790
   0.500   0.3175   0.00996   0.00530  -0.0240   0.5735   0.9714
   0.750   0.3964   0.01018   0.00537  -0.0346   0.5717   0.9998
   1.000   0.4240   0.01023   0.00539  -0.0347   0.5702   1.0000
   1.250   0.4505   0.01031   0.00547  -0.0346   0.5687   1.0000
   1.500   0.4770   0.01041   0.00554  -0.0345   0.5672   1.0000
   1.750   0.5035   0.01051   0.00563  -0.0344   0.5657   1.0000
   2.000   0.5300   0.01062   0.00572  -0.0342   0.5644   1.0000
   2.250   0.5564   0.01070   0.00578  -0.0341   0.5630   1.0000
   2.500   0.5828   0.01076   0.00582  -0.0338   0.5616   1.0000
   2.750   0.6093   0.01082   0.00585  -0.0336   0.5603   1.0000
   3.000   0.6357   0.01090   0.00591  -0.0334   0.5592   1.0000
   3.250   0.6622   0.01100   0.00598  -0.0332   0.5581   1.0000
   3.500   0.6884   0.01119   0.00614  -0.0330   0.5568   1.0000
   3.750   0.7155   0.01133   0.00634  -0.0331   0.5550   1.0000
   4.000   0.7425   0.01148   0.00654  -0.0332   0.5529   1.0000
   4.250   0.7694   0.01158   0.00668  -0.0332   0.5509   1.0000
   4.500   0.7962   0.01164   0.00676  -0.0331   0.5488   1.0000
   4.750   0.8230   0.01164   0.00677  -0.0330   0.5470   1.0000
   5.000   0.8498   0.01147   0.00657  -0.0326   0.5448   1.0000
   5.250   0.8764   0.01128   0.00629  -0.0321   0.5421   1.0000
   5.500   0.9037   0.01117   0.00630  -0.0322   0.5374   1.0000
   5.750   0.9310   0.01099   0.00615  -0.0321   0.5335   1.0000
   6.000   0.9582   0.01074   0.00588  -0.0318   0.5303   1.0000
   6.250   0.9854   0.01055   0.00567  -0.0315   0.5264   1.0000
   6.500   1.0128   0.01046   0.00569  -0.0316   0.5211   1.0000
   6.750   1.0402   0.01030   0.00556  -0.0315   0.5169   1.0000
   7.000   1.0675   0.01014   0.00540  -0.0314   0.5125   1.0000
   7.250   1.0950   0.01005   0.00544  -0.0315   0.5049   1.0000
   7.500   1.1223   0.00993   0.00533  -0.0315   0.4995   1.0000
   7.750   1.1498   0.00994   0.00547  -0.0317   0.4901   1.0000
   8.000   1.1770   0.00993   0.00553  -0.0318   0.4790   1.0000
   8.250   1.2040   0.00997   0.00561  -0.0319   0.4638   1.0000
   8.500   1.2301   0.01014   0.00573  -0.0320   0.4356   1.0000
   8.750   1.2516   0.01108   0.00637  -0.0321   0.3813   1.0000
   9.000   1.2680   0.01270   0.00770  -0.0323   0.3194   1.0000
   9.250   1.2739   0.01531   0.00992  -0.0325   0.2458   1.0000
   9.500   1.2697   0.01909   0.01347  -0.0340   0.1948   1.0000
   9.750   1.2535   0.02217   0.01642  -0.0317   0.1708   1.0000
  10.000   1.2410   0.02501   0.01911  -0.0297   0.1456   1.0000
  10.250   1.2352   0.02746   0.02145  -0.0282   0.1232   1.0000
  10.500   1.2291   0.02998   0.02381  -0.0269   0.1015   1.0000
  10.750   1.2291   0.03205   0.02582  -0.0258   0.0899   1.0000
  11.000   1.2328   0.03388   0.02765  -0.0250   0.0828   1.0000
  11.250   1.2363   0.03572   0.02949  -0.0241   0.0767   1.0000
  11.500   1.2432   0.03731   0.03111  -0.0235   0.0723   1.0000
  11.750   1.2476   0.03918   0.03297  -0.0228   0.0677   1.0000
  12.000   1.2554   0.04081   0.03465  -0.0223   0.0642   1.0000
  12.250   1.2645   0.04235   0.03625  -0.0219   0.0603   1.0000
  12.500   1.2708   0.04418   0.03807  -0.0214   0.0556   1.0000
  12.750   1.2807   0.04569   0.03963  -0.0211   0.0515   1.0000
  13.000   1.2880   0.04748   0.04142  -0.0208   0.0463   1.0000
  13.250   1.2959   0.04923   0.04318  -0.0205   0.0400   1.0000
  13.500   1.2990   0.05146   0.04533  -0.0201   0.0299   1.0000
  13.750   1.2978   0.05421   0.04800  -0.0197   0.0215   1.0000
  14.000   1.2993   0.05671   0.05050  -0.0194   0.0181   1.0000
  14.250   1.3007   0.05932   0.05316  -0.0191   0.0160   1.0000
  14.500   1.3044   0.06167   0.05557  -0.0190   0.0147   1.0000
  14.750   1.3021   0.06478   0.05873  -0.0188   0.0135   1.0000
  15.000   1.3035   0.06751   0.06154  -0.0188   0.0130   1.0000
  15.250   1.3074   0.07001   0.06412  -0.0189   0.0124   1.0000
  15.500   1.3086   0.07285   0.06704  -0.0189   0.0117   1.0000
  15.750   1.3085   0.07587   0.07014  -0.0191   0.0114   1.0000
  16.000   1.3089   0.07891   0.07326  -0.0194   0.0111   1.0000
  16.250   1.3053   0.08251   0.07693  -0.0198   0.0107   1.0000
  16.500   1.3012   0.08619   0.08067  -0.0202   0.0104   1.0000
  16.750   1.2956   0.09010   0.08467  -0.0207   0.0102   1.0000
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