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Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns)
Reynolds number: 500,000
Max Cl/Cd: 62.73 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-prandtl-d-tip-ns-500000.txt
Download as CSV file: xf-prandtl-d-tip-ns-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Prandtl-D tip - NASA Preliminary Research Aerody
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -20.000  -0.6332   0.22724   0.22526   0.0632   1.0000   0.0113
 -19.750  -0.6290   0.22394   0.22195   0.0611   1.0000   0.0114
 -19.500  -0.6245   0.22076   0.21877   0.0590   1.0000   0.0115
 -19.250  -0.6198   0.21730   0.21530   0.0571   1.0000   0.0116
 -19.000  -0.6149   0.21384   0.21183   0.0552   1.0000   0.0116
 -18.750  -0.6100   0.21040   0.20838   0.0533   1.0000   0.0116
 -18.500  -0.6053   0.20684   0.20482   0.0514   1.0000   0.0116
 -18.250  -0.6044   0.20089   0.19888   0.0495   1.0000   0.0122
 -18.000  -0.5977   0.19794   0.19592   0.0482   1.0000   0.0124
 -17.750  -0.5911   0.19516   0.19310   0.0468   1.0000   0.0127
 -17.500  -0.5853   0.19226   0.19020   0.0453   1.0000   0.0130
 -17.250  -0.5797   0.18936   0.18730   0.0437   1.0000   0.0134
 -17.000  -0.5746   0.18633   0.18425   0.0419   1.0000   0.0137
 -16.750  -0.5695   0.18330   0.18122   0.0402   1.0000   0.0142
 -16.500  -0.5649   0.18019   0.17810   0.0385   1.0000   0.0148
 -16.250  -0.5605   0.17699   0.17490   0.0366   1.0000   0.0154
 -16.000  -0.5567   0.17366   0.17156   0.0347   1.0000   0.0163
 -15.750  -0.5536   0.17015   0.16806   0.0326   1.0000   0.0172
 -15.500  -0.5519   0.16667   0.16457   0.0298   1.0000   0.0186
 -15.250  -0.5485   0.16334   0.16124   0.0278   1.0000   0.0188
 -15.000  -0.5458   0.15979   0.15768   0.0258   1.0000   0.0189
 -14.750  -0.5437   0.15611   0.15400   0.0238   1.0000   0.0189
 -14.500  -0.5659   0.14504   0.14295   0.0200   1.0000   0.0122
 -14.250  -0.5636   0.14168   0.13957   0.0182   1.0000   0.0118
 -14.000  -0.5708   0.13780   0.13567   0.0161   1.0000   0.0111
 -13.500  -0.8439   0.09165   0.08917  -0.0044   1.0000   0.0074
 -13.250  -0.8686   0.08128   0.07865  -0.0109   1.0000   0.0072
 -13.000  -0.8932   0.07163   0.06887  -0.0175   1.0000   0.0073
 -12.750  -0.8900   0.06772   0.06487  -0.0204   1.0000   0.0070
 -12.500  -0.9114   0.05960   0.05657  -0.0265   1.0000   0.0070
 -12.250  -0.9305   0.05286   0.04964  -0.0312   1.0000   0.0070
 -12.000  -0.9490   0.04735   0.04393  -0.0343   1.0000   0.0071
 -11.750  -0.9453   0.04531   0.04181  -0.0349   1.0000   0.0069
 -11.500  -0.9713   0.04045   0.03668  -0.0347   1.0000   0.0070
 -11.250  -0.9797   0.03797   0.03402  -0.0328   1.0000   0.0070
 -11.000  -0.9966   0.03491   0.03071  -0.0291   1.0000   0.0071
 -10.750  -1.0049   0.03237   0.02794  -0.0253   1.0000   0.0071
 -10.500  -1.0074   0.02967   0.02497  -0.0222   1.0000   0.0074
 -10.250  -1.0026   0.02750   0.02260  -0.0197   1.0000   0.0076
 -10.000  -0.9917   0.02602   0.02098  -0.0177   1.0000   0.0080
  -9.750  -0.9796   0.02447   0.01925  -0.0158   1.0000   0.0082
  -9.500  -0.9650   0.02321   0.01786  -0.0140   1.0000   0.0086
  -9.250  -0.9493   0.02202   0.01653  -0.0123   1.0000   0.0089
  -9.000  -0.9331   0.02084   0.01522  -0.0106   1.0000   0.0094
  -8.750  -0.9166   0.01970   0.01393  -0.0088   1.0000   0.0099
  -8.500  -0.8984   0.01880   0.01292  -0.0073   1.0000   0.0105
  -8.250  -0.8773   0.01830   0.01232  -0.0062   1.0000   0.0113
  -8.000  -0.8618   0.01705   0.01092  -0.0041   1.0000   0.0121
  -7.750  -0.8495   0.01549   0.00922  -0.0014   1.0000   0.0144
  -7.500  -0.8297   0.01483   0.00851   0.0001   1.0000   0.0169
  -7.250  -0.8086   0.01434   0.00794   0.0014   1.0000   0.0195
  -7.000  -0.7913   0.01339   0.00695   0.0034   1.0000   0.0254
  -6.750  -0.7693   0.01304   0.00654   0.0045   1.0000   0.0291
  -6.500  -0.7501   0.01237   0.00589   0.0061   1.0000   0.0382
  -6.250  -0.7298   0.01186   0.00543   0.0075   1.0000   0.0496
  -6.000  -0.7092   0.01140   0.00498   0.0089   1.0000   0.0643
  -5.750  -0.6890   0.01094   0.00460   0.0103   1.0000   0.0818
  -5.500  -0.6685   0.01054   0.00428   0.0117   1.0000   0.1023
  -5.250  -0.6480   0.01016   0.00400   0.0131   1.0000   0.1246
  -5.000  -0.6272   0.00985   0.00375   0.0144   1.0000   0.1458
  -4.750  -0.6067   0.00954   0.00353   0.0158   1.0000   0.1702
  -4.500  -0.5862   0.00925   0.00334   0.0172   1.0000   0.1948
  -4.250  -0.5657   0.00899   0.00317   0.0185   1.0000   0.2206
  -4.000  -0.5453   0.00875   0.00300   0.0199   1.0000   0.2473
  -3.750  -0.5211   0.00853   0.00288   0.0204   0.9994   0.2754
  -3.500  -0.4828   0.00827   0.00275   0.0180   0.9956   0.3132
  -3.250  -0.4455   0.00799   0.00262   0.0158   0.9913   0.3535
  -3.000  -0.4079   0.00771   0.00250   0.0136   0.9867   0.3950
  -2.750  -0.3701   0.00745   0.00237   0.0113   0.9822   0.4359
  -2.500  -0.3340   0.00719   0.00225   0.0095   0.9763   0.4765
  -2.250  -0.2947   0.00690   0.00214   0.0071   0.9724   0.5236
  -2.000  -0.2610   0.00665   0.00202   0.0059   0.9643   0.5642
  -1.750  -0.2230   0.00642   0.00192   0.0038   0.9587   0.6018
  -1.500  -0.1909   0.00621   0.00183   0.0031   0.9480   0.6375
  -1.250  -0.1589   0.00602   0.00176   0.0025   0.9351   0.6718
  -1.000  -0.1287   0.00585   0.00168   0.0023   0.9196   0.7065
  -0.500  -0.0748   0.00560   0.00158   0.0034   0.8799   0.7699
  -0.250  -0.0492   0.00552   0.00156   0.0044   0.8563   0.8022
   0.000  -0.0237   0.00549   0.00154   0.0053   0.8312   0.8333
   0.250   0.0026   0.00549   0.00154   0.0061   0.8041   0.8623
   0.500   0.0307   0.00553   0.00156   0.0064   0.7746   0.8882
   0.750   0.0622   0.00562   0.00159   0.0060   0.7439   0.9109
   1.000   0.0974   0.00576   0.00164   0.0047   0.7128   0.9290
   1.250   0.1351   0.00594   0.00171   0.0028   0.6775   0.9424
   1.500   0.1739   0.00614   0.00180   0.0006   0.6422   0.9519
   1.750   0.2091   0.00636   0.00189  -0.0008   0.6073   0.9611
   2.000   0.2468   0.00661   0.00200  -0.0028   0.5693   0.9669
   2.250   0.2812   0.00686   0.00212  -0.0042   0.5298   0.9747
   2.500   0.3187   0.00713   0.00224  -0.0062   0.4854   0.9806
   2.750   0.3553   0.00741   0.00235  -0.0082   0.4421   0.9864
   3.000   0.3936   0.00766   0.00246  -0.0105   0.4025   0.9912
   3.250   0.4316   0.00793   0.00259  -0.0129   0.3608   0.9956
   3.500   0.4706   0.00818   0.00269  -0.0155   0.3200   0.9994
   3.750   0.4954   0.00838   0.00278  -0.0151   0.2889   1.0000
   4.000   0.5170   0.00859   0.00289  -0.0139   0.2597   1.0000
   4.250   0.5387   0.00881   0.00303  -0.0128   0.2334   1.0000
   4.500   0.5604   0.00908   0.00319  -0.0117   0.2060   1.0000
   4.750   0.5822   0.00936   0.00340  -0.0106   0.1809   1.0000
   5.000   0.6040   0.00967   0.00362  -0.0095   0.1559   1.0000
   5.250   0.6260   0.00999   0.00386  -0.0084   0.1324   1.0000
   5.500   0.6480   0.01033   0.00413  -0.0073   0.1117   1.0000
   5.750   0.6695   0.01075   0.00444  -0.0062   0.0896   1.0000
   6.000   0.6913   0.01116   0.00479  -0.0051   0.0702   1.0000
   6.250   0.7125   0.01167   0.00521  -0.0039   0.0538   1.0000
   6.500   0.7337   0.01219   0.00572  -0.0027   0.0412   1.0000
   6.750   0.7555   0.01264   0.00618  -0.0015   0.0333   1.0000
   7.000   0.7759   0.01328   0.00683  -0.0002   0.0264   1.0000
   7.250   0.7978   0.01372   0.00730   0.0009   0.0222   1.0000
   7.500   0.8154   0.01476   0.00842   0.0028   0.0174   1.0000
   7.750   0.8366   0.01531   0.00904   0.0040   0.0148   1.0000
   8.000   0.8562   0.01604   0.00984   0.0055   0.0130   1.0000
   8.250   0.8670   0.01793   0.01191   0.0083   0.0111   1.0000
   8.500   0.8821   0.01933   0.01348   0.0104   0.0106   1.0000
   8.750   0.9011   0.02015   0.01440   0.0118   0.0101   1.0000
   9.000   0.9205   0.02084   0.01522   0.0131   0.0095   1.0000
   9.250   0.9372   0.02190   0.01641   0.0147   0.0089   1.0000
   9.500   0.9520   0.02323   0.01790   0.0166   0.0085   1.0000
   9.750   0.9655   0.02468   0.01951   0.0186   0.0083   1.0000
  10.000   0.9772   0.02628   0.02130   0.0206   0.0081   1.0000
  10.250   0.9866   0.02806   0.02328   0.0228   0.0079   1.0000
  10.500   0.9972   0.02936   0.02471   0.0248   0.0075   1.0000
  10.750   1.0027   0.03120   0.02674   0.0271   0.0074   1.0000
  11.000   1.0035   0.03328   0.02902   0.0298   0.0073   1.0000
  11.250   1.0008   0.03480   0.03064   0.0330   0.0070   1.0000
  11.500   0.9910   0.03725   0.03330   0.0360   0.0069   1.0000
  11.750   0.9803   0.04009   0.03632   0.0374   0.0068   1.0000
  12.000   0.9677   0.04374   0.04016   0.0373   0.0068   1.0000
  12.250   0.9373   0.05062   0.04730   0.0340   0.0065   1.0000
  12.500   0.9408   0.05361   0.05043   0.0319   0.0069   1.0000
  12.750   0.9228   0.06064   0.05764   0.0267   0.0068   1.0000
  13.000   0.9015   0.06922   0.06641   0.0202   0.0069   1.0000
  17.500   0.5571   0.18787   0.18573  -0.0352   0.0131   1.0000
  17.750   0.5620   0.19087   0.18873  -0.0369   0.0127   1.0000
  18.000   0.5674   0.19373   0.19159  -0.0385   0.0123   1.0000
  18.250   0.5729   0.19659   0.19446  -0.0400   0.0120   1.0000
  18.500   0.5788   0.19936   0.19725  -0.0415   0.0117   1.0000
  18.750   0.5853   0.20213   0.20004  -0.0428   0.0115   1.0000
  19.000   0.5916   0.20529   0.20322  -0.0440   0.0112   1.0000
  19.250   0.5929   0.21093   0.20883  -0.0460   0.0108   1.0000
  19.500   0.5976   0.21436   0.21227  -0.0478   0.0108   1.0000
  19.750   0.6025   0.21769   0.21561  -0.0496   0.0108   1.0000
  20.000   0.6073   0.22106   0.21899  -0.0514   0.0108   1.0000
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