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WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.88 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx05h126-il-1000000-n5.txt
Download as CSV file: xf-fx05h126-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4677   0.08212   0.07917  -0.0002   0.5578   0.0087
  -8.500  -0.4697   0.07876   0.07584  -0.0023   0.5572   0.0088
  -8.250  -0.4816   0.07488   0.07199  -0.0049   0.5567   0.0089
  -8.000  -0.4843   0.07023   0.06733  -0.0087   0.5561   0.0090
  -7.750  -0.4849   0.06485   0.06191  -0.0125   0.5554   0.0091
  -7.250  -0.5535   0.02496   0.02033  -0.0170   0.5553   0.0110
  -7.000  -0.5353   0.02213   0.01710  -0.0160   0.5545   0.0112
  -6.750  -0.5124   0.02070   0.01544  -0.0155   0.5536   0.0113
  -6.500  -0.4923   0.01833   0.01270  -0.0146   0.5528   0.0115
  -6.250  -0.4677   0.01732   0.01154  -0.0142   0.5520   0.0117
  -6.000  -0.4418   0.01662   0.01073  -0.0139   0.5512   0.0119
  -5.750  -0.4155   0.01601   0.01002  -0.0137   0.5504   0.0120
  -5.500  -0.3891   0.01541   0.00933  -0.0135   0.5496   0.0122
  -5.250  -0.3624   0.01485   0.00867  -0.0133   0.5488   0.0123
  -5.000  -0.3355   0.01432   0.00805  -0.0131   0.5480   0.0125
  -4.750  -0.3086   0.01379   0.00743  -0.0129   0.5472   0.0127
  -4.500  -0.2815   0.01329   0.00684  -0.0127   0.5464   0.0130
  -4.250  -0.2543   0.01287   0.00635  -0.0125   0.5456   0.0133
  -4.000  -0.2268   0.01251   0.00592  -0.0124   0.5447   0.0137
  -3.750  -0.1995   0.01212   0.00547  -0.0122   0.5438   0.0140
  -3.500  -0.1721   0.01172   0.00502  -0.0121   0.5433   0.0143
  -3.250  -0.1445   0.01139   0.00465  -0.0119   0.5427   0.0146
  -3.000  -0.1168   0.01110   0.00433  -0.0118   0.5419   0.0148
  -2.750  -0.0890   0.01085   0.00405  -0.0118   0.5412   0.0150
  -2.500  -0.0615   0.01054   0.00371  -0.0116   0.5404   0.0152
  -2.250  -0.0347   0.01012   0.00326  -0.0114   0.5397   0.0156
  -2.000  -0.0071   0.00986   0.00298  -0.0113   0.5389   0.0160
  -1.750   0.0208   0.00966   0.00277  -0.0113   0.5382   0.0165
  -1.500   0.0488   0.00948   0.00259  -0.0112   0.5374   0.0169
  -1.250   0.0769   0.00934   0.00244  -0.0112   0.5367   0.0176
  -1.000   0.1051   0.00921   0.00230  -0.0113   0.5359   0.0183
  -0.750   0.1334   0.00908   0.00217  -0.0113   0.5352   0.0189
  -0.500   0.1617   0.00898   0.00205  -0.0114   0.5344   0.0195
  -0.250   0.1901   0.00889   0.00196  -0.0114   0.5336   0.0199
   0.000   0.2184   0.00878   0.00183  -0.0115   0.5326   0.0208
   0.250   0.2467   0.00870   0.00173  -0.0115   0.5314   0.0222
   0.500   0.2751   0.00865   0.00167  -0.0116   0.5299   0.0239
   1.000   0.3316   0.00842   0.00161  -0.0118   0.5279   0.0652
   1.250   0.3595   0.00826   0.00159  -0.0119   0.5268   0.1102
   1.500   0.3859   0.00791   0.00159  -0.0118   0.5256   0.2406
   1.750   0.4065   0.00701   0.00158  -0.0107   0.5241   0.5584
   2.000   0.4254   0.00636   0.00158  -0.0089   0.5227   0.7594
   2.250   0.5179   0.00594   0.00174  -0.0230   0.5214   0.9872
   2.500   0.5609   0.00602   0.00179  -0.0263   0.5203   0.9951
   2.750   0.5982   0.00604   0.00180  -0.0284   0.5191   0.9979
   3.000   0.6367   0.00608   0.00181  -0.0308   0.5178   1.0000
   3.250   0.6639   0.00612   0.00184  -0.0307   0.5165   1.0000
   3.500   0.6911   0.00618   0.00189  -0.0307   0.5152   1.0000
   3.750   0.7185   0.00620   0.00194  -0.0307   0.5138   1.0000
   4.000   0.7459   0.00622   0.00198  -0.0307   0.5115   1.0000
   4.250   0.7733   0.00625   0.00203  -0.0307   0.5091   1.0000
   4.500   0.8008   0.00625   0.00202  -0.0307   0.5045   1.0000
   4.750   0.8283   0.00627   0.00205  -0.0307   0.4983   1.0000
   5.000   0.8558   0.00631   0.00210  -0.0308   0.4931   1.0000
   5.250   0.8833   0.00636   0.00215  -0.0308   0.4887   1.0000
   5.500   0.9108   0.00641   0.00222  -0.0309   0.4817   1.0000
   5.750   0.9383   0.00650   0.00229  -0.0310   0.4724   1.0000
   6.000   0.9657   0.00662   0.00239  -0.0312   0.4580   1.0000
   6.250   0.9924   0.00711   0.00267  -0.0316   0.4109   1.0000
   6.500   1.0187   0.00768   0.00310  -0.0320   0.3777   1.0000
   6.750   1.0451   0.00810   0.00345  -0.0323   0.3569   1.0000
   7.000   1.0707   0.00870   0.00392  -0.0326   0.3254   1.0000
   7.250   1.0940   0.00979   0.00474  -0.0332   0.2679   1.0000
   7.500   1.1151   0.01110   0.00574  -0.0337   0.2078   1.0000
   7.750   1.1345   0.01237   0.00676  -0.0340   0.1615   1.0000
   8.000   1.1547   0.01332   0.00759  -0.0341   0.1347   1.0000
   8.250   1.1700   0.01474   0.00882  -0.0341   0.0968   1.0000
   8.500   1.1863   0.01612   0.01013  -0.0346   0.0789   1.0000
   8.750   1.2026   0.01770   0.01171  -0.0358   0.0713   1.0000
   9.000   1.2162   0.01908   0.01311  -0.0360   0.0662   1.0000
   9.250   1.2200   0.02055   0.01459  -0.0344   0.0623   1.0000
   9.500   1.2240   0.02207   0.01610  -0.0330   0.0570   1.0000
   9.750   1.2337   0.02331   0.01737  -0.0322   0.0540   1.0000
  10.000   1.2429   0.02462   0.01870  -0.0314   0.0510   1.0000
  10.250   1.2500   0.02612   0.02018  -0.0305   0.0460   1.0000
  10.500   1.2606   0.02738   0.02147  -0.0299   0.0440   1.0000
  10.750   1.2680   0.02887   0.02294  -0.0292   0.0391   1.0000
  11.000   1.2759   0.03035   0.02443  -0.0285   0.0356   1.0000
  11.250   1.2808   0.03207   0.02610  -0.0277   0.0290   1.0000
  11.500   1.2863   0.03376   0.02779  -0.0270   0.0240   1.0000
  11.750   1.2896   0.03562   0.02961  -0.0262   0.0170   1.0000
  12.000   1.2920   0.03766   0.03163  -0.0255   0.0112   1.0000
  12.250   1.2978   0.03946   0.03343  -0.0249   0.0086   1.0000
  12.500   1.3058   0.04111   0.03512  -0.0245   0.0076   1.0000
  12.750   1.3141   0.04277   0.03681  -0.0241   0.0069   1.0000
  13.000   1.3228   0.04440   0.03848  -0.0237   0.0064   1.0000
  13.250   1.3306   0.04614   0.04027  -0.0234   0.0061   1.0000
  13.500   1.3370   0.04804   0.04222  -0.0231   0.0056   1.0000
  13.750   1.3447   0.04983   0.04405  -0.0228   0.0052   1.0000
  14.000   1.3531   0.05158   0.04585  -0.0226   0.0050   1.0000
  14.250   1.3601   0.05351   0.04783  -0.0224   0.0049   1.0000
  14.500   1.3676   0.05536   0.04974  -0.0222   0.0047   1.0000
  14.750   1.3739   0.05740   0.05183  -0.0220   0.0045   1.0000
  15.000   1.3804   0.05944   0.05393  -0.0219   0.0044   1.0000
  15.250   1.3863   0.06156   0.05610  -0.0219   0.0043   1.0000
  15.500   1.3909   0.06384   0.05844  -0.0218   0.0041   1.0000
  15.750   1.3948   0.06624   0.06091  -0.0218   0.0039   1.0000
  16.000   1.3975   0.06880   0.06353  -0.0219   0.0038   1.0000
  16.250   1.3988   0.07161   0.06641  -0.0220   0.0037   1.0000
  16.500   1.3996   0.07446   0.06934  -0.0222   0.0036   1.0000
  16.750   1.4023   0.07717   0.07211  -0.0224   0.0035   1.0000
  17.000   1.4056   0.07980   0.07481  -0.0227   0.0035   1.0000
  17.250   1.4063   0.08283   0.07792  -0.0231   0.0034   1.0000
  17.500   1.4073   0.08583   0.08100  -0.0235   0.0034   1.0000
  17.750   1.4086   0.08882   0.08407  -0.0241   0.0033   1.0000
  18.000   1.4079   0.09214   0.08748  -0.0247   0.0032   1.0000
  18.250   1.4058   0.09572   0.09114  -0.0254   0.0032   1.0000
  18.500   1.4045   0.09922   0.09473  -0.0262   0.0032   1.0000
  18.750   1.4029   0.10276   0.09834  -0.0271   0.0031   1.0000
  19.000   1.3977   0.10693   0.10262  -0.0282   0.0031   1.0000
  19.250   1.3953   0.11071   0.10648  -0.0293   0.0030   1.0000
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