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RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il)
Reynolds number: 50,000
Max Cl/Cd: 4.25 at α=12°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r1082-il-50000.txt
Download as CSV file: xf-r1082-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RONCZ 1082 VOYAGER ROOT OUTER AFT WING 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2264   0.11664   0.11143  -0.0462   0.9476   0.3349
  -8.750  -0.2536   0.11529   0.11015  -0.0456   0.9455   0.3466
  -8.500  -0.4818   0.09374   0.08839  -0.0602   0.9602   0.1666
  -8.250  -0.5327   0.08977   0.08438  -0.0580   0.9557   0.1531
  -8.000  -0.6022   0.08619   0.08057  -0.0532   0.9520   0.1434
  -7.750  -0.6096   0.08211   0.07642  -0.0518   0.9491   0.1368
  -7.500  -0.6533   0.07797   0.07178  -0.0472   0.9479   0.1281
  -7.250  -0.6559   0.07474   0.06845  -0.0450   0.9470   0.1252
  -7.000  -0.6683   0.07162   0.06509  -0.0416   0.9473   0.1220
  -6.750  -0.6871   0.06794   0.06088  -0.0373   0.9485   0.1178
  -6.500  -0.6992   0.06528   0.05746  -0.0328   0.9502   0.1145
  -6.250  -0.6964   0.06269   0.05459  -0.0303   0.9513   0.1142
  -6.000  -0.6942   0.06035   0.05187  -0.0274   0.9541   0.1144
  -5.750  -0.6880   0.05821   0.04931  -0.0249   0.9582   0.1148
  -5.500  -0.7648   0.05771   0.04930  -0.0075   1.0000   0.1139
  -5.250  -0.7524   0.05512   0.04623  -0.0059   1.0000   0.1144
  -5.000  -0.7379   0.05275   0.04339  -0.0045   1.0000   0.1148
  -4.750  -0.7217   0.05014   0.04053  -0.0034   1.0000   0.1162
  -4.500  -0.7042   0.04817   0.03841  -0.0023   1.0000   0.1183
  -4.250  -0.6863   0.04669   0.03676  -0.0013   1.0000   0.1229
  -4.000  -0.6672   0.04535   0.03494   0.0000   1.0000   0.1293
  -3.750  -0.6481   0.04389   0.03354   0.0009   1.0000   0.1370
  -3.500  -0.6276   0.04271   0.03221   0.0020   1.0000   0.1482
  -3.250  -0.6072   0.04171   0.03129   0.0031   1.0000   0.1657
  -3.000  -0.5869   0.04080   0.03054   0.0044   1.0000   0.1965
  -2.750  -0.5686   0.03977   0.02991   0.0060   1.0000   0.2467
  -2.500  -0.5550   0.03805   0.02915   0.0081   1.0000   0.3432
  -2.250  -0.5720   0.03766   0.03164   0.0224   1.0000   0.7617
  -2.000  -0.2182   0.05405   0.04598  -0.0251   1.0000   1.0000
  -1.750  -0.2148   0.05382   0.04557  -0.0232   1.0000   1.0000
  -1.500  -0.2110   0.05368   0.04524  -0.0213   1.0000   1.0000
  -1.250  -0.2066   0.05358   0.04496  -0.0194   1.0000   1.0000
  -1.000  -0.2019   0.05352   0.04474  -0.0175   1.0000   1.0000
  -0.750  -0.1970   0.05351   0.04457  -0.0156   1.0000   1.0000
  -0.500  -0.1918   0.05353   0.04444  -0.0136   1.0000   1.0000
  -0.250  -0.1865   0.05357   0.04432  -0.0117   1.0000   1.0000
   0.000  -0.1811   0.05363   0.04425  -0.0098   1.0000   1.0000
   0.250  -0.1756   0.05371   0.04421  -0.0079   1.0000   1.0000
   0.500  -0.1701   0.05380   0.04418  -0.0059   1.0000   1.0000
   0.750  -0.1645   0.05391   0.04417  -0.0040   1.0000   1.0000
   1.000  -0.1590   0.05403   0.04418  -0.0020   1.0000   1.0000
   1.250  -0.1536   0.05415   0.04420  -0.0001   1.0000   1.0000
   1.500  -0.1482   0.05427   0.04423   0.0019   1.0000   1.0000
   1.750  -0.1429   0.05440   0.04427   0.0038   1.0000   1.0000
   2.000  -0.1338   0.05472   0.04449   0.0050   0.9988   1.0000
   2.250  -0.1065   0.05620   0.04587   0.0024   0.9899   1.0000
   2.500  -0.0820   0.05761   0.04718   0.0005   0.9800   1.0000
   2.750  -0.0593   0.05894   0.04843  -0.0009   0.9692   1.0000
   3.000  -0.0356   0.06063   0.05002  -0.0025   0.9584   1.0000
   3.250  -0.0160   0.06160   0.05093  -0.0032   0.9458   1.0000
   3.500  -0.0013   0.06222   0.05149  -0.0030   0.9329   1.0000
   3.750   0.0124   0.06306   0.05228  -0.0026   0.9215   1.0000
   4.000   0.0394   0.06569   0.05481  -0.0044   0.9124   1.0000
   4.250   0.0489   0.06564   0.05473  -0.0032   0.8984   1.0000
   4.500   0.0597   0.06631   0.05535  -0.0022   0.8869   1.0000
   4.750   0.0912   0.06944   0.05842  -0.0048   0.8786   1.0000
   5.000   0.0989   0.06933   0.05828  -0.0034   0.8647   1.0000
   5.250   0.1110   0.07029   0.05921  -0.0028   0.8536   1.0000
   5.500   0.1443   0.07349   0.06237  -0.0057   0.8450   1.0000
   5.750   0.1514   0.07361   0.06249  -0.0044   0.8315   1.0000
   6.000   0.1648   0.07493   0.06379  -0.0042   0.8210   1.0000
   6.250   0.1972   0.07800   0.06684  -0.0069   0.8115   1.0000
   6.500   0.2032   0.07837   0.06723  -0.0056   0.7984   1.0000
   6.750   0.2195   0.08023   0.06909  -0.0060   0.7889   1.0000
   7.000   0.2478   0.08287   0.07174  -0.0080   0.7777   1.0000
   7.250   0.2536   0.08360   0.07249  -0.0070   0.7652   1.0000
   7.500   0.2759   0.08628   0.07520  -0.0083   0.7567   1.0000
   7.750   0.2961   0.08819   0.07715  -0.0092   0.7439   1.0000
   8.000   0.3021   0.08930   0.07829  -0.0084   0.7317   1.0000
   8.250   0.3298   0.09268   0.08170  -0.0105   0.7234   1.0000
   8.500   0.3433   0.09411   0.08320  -0.0106   0.7098   1.0000
   8.750   0.3488   0.09542   0.08456  -0.0100   0.6976   1.0000
   9.000   0.3740   0.09875   0.08795  -0.0118   0.6890   1.0000
   9.250   0.3912   0.10072   0.08998  -0.0124   0.6751   1.0000
   9.500   0.3932   0.10197   0.09130  -0.0116   0.6629   1.0000
   9.750   0.4104   0.10478   0.09417  -0.0126   0.6534   1.0000
  10.000   0.4402   0.10816   0.09765  -0.0145   0.6403   1.0000
  10.250   0.4368   0.10901   0.09855  -0.0135   0.6275   1.0000
  10.500   0.4458   0.11131   0.10093  -0.0138   0.6165   1.0000
  10.750   0.4751   0.11515   0.10488  -0.0157   0.6056   1.0000
  11.000   0.4870   0.11708   0.10690  -0.0160   0.5911   1.0000
  11.250   0.4846   0.11865   0.10853  -0.0156   0.5794   1.0000
  11.500   0.4968   0.12148   0.11145  -0.0164   0.5691   1.0000
  11.750   0.5225   0.12502   0.11511  -0.0178   0.5563   1.0000
  12.000   0.5437   0.12794   0.11814  -0.0188   0.5411   1.0000
  12.250   0.5310   0.12902   0.11928  -0.0182   0.5306   1.0000
  12.500   0.5409   0.13201   0.12236  -0.0191   0.5208   1.0000
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