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N-9 (n9-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 200,000
Max Cl/Cd: 63.38 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n9-il-200000-n5.txt
Download as CSV file: xf-n9-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-9                                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4805   0.08687   0.08334  -0.0214   1.0000   0.0159
  -9.750  -0.4841   0.08219   0.07871  -0.0240   1.0000   0.0158
  -9.500  -0.4907   0.07744   0.07402  -0.0268   1.0000   0.0157
  -9.250  -0.4945   0.07148   0.06810  -0.0322   1.0000   0.0156
  -9.000  -0.4967   0.06448   0.06110  -0.0384   1.0000   0.0155
  -8.750  -0.4990   0.05610   0.05263  -0.0443   1.0000   0.0155
  -8.500  -0.5043   0.04455   0.04073  -0.0494   1.0000   0.0154
  -8.250  -0.5102   0.03191   0.02718  -0.0513   1.0000   0.0159
  -8.000  -0.4979   0.02712   0.02167  -0.0507   1.0000   0.0172
  -7.750  -0.4805   0.02430   0.01822  -0.0496   1.0000   0.0184
  -7.500  -0.4621   0.02238   0.01607  -0.0486   1.0000   0.0194
  -7.250  -0.4336   0.02122   0.01472  -0.0492   0.9979   0.0206
  -7.000  -0.4001   0.01993   0.01317  -0.0507   0.9948   0.0227
  -6.750  -0.3673   0.01885   0.01176  -0.0518   0.9907   0.0255
  -6.500  -0.3347   0.01743   0.01014  -0.0531   0.9871   0.0279
  -6.250  -0.3025   0.01676   0.00938  -0.0542   0.9823   0.0310
  -6.000  -0.2688   0.01607   0.00850  -0.0553   0.9777   0.0347
  -5.750  -0.2373   0.01512   0.00749  -0.0562   0.9718   0.0381
  -5.500  -0.2036   0.01462   0.00693  -0.0575   0.9666   0.0425
  -5.250  -0.1716   0.01411   0.00629  -0.0583   0.9600   0.0459
  -5.000  -0.1378   0.01349   0.00569  -0.0596   0.9543   0.0506
  -4.750  -0.1049   0.01305   0.00520  -0.0606   0.9470   0.0548
  -4.500  -0.0699   0.01261   0.00472  -0.0620   0.9408   0.0608
  -4.250  -0.0361   0.01228   0.00438  -0.0632   0.9335   0.0708
  -4.000  -0.0001   0.01194   0.00402  -0.0647   0.9259   0.0844
  -3.750   0.0341   0.01164   0.00368  -0.0659   0.9150   0.0986
  -3.500   0.0671   0.01135   0.00336  -0.0668   0.9027   0.1120
  -3.000   0.1256   0.01072   0.00300  -0.0672   0.8738   0.1936
  -2.750   0.1524   0.01036   0.00287  -0.0670   0.8573   0.2679
  -2.500   0.1775   0.00980   0.00277  -0.0665   0.8380   0.4047
  -2.250   0.2015   0.00931   0.00270  -0.0656   0.8142   0.5425
  -2.000   0.2245   0.00886   0.00262  -0.0642   0.7902   0.6712
  -1.750   0.2460   0.00843   0.00259  -0.0618   0.7708   0.8349
  -1.250   0.3236   0.00838   0.00236  -0.0657   0.7363   1.0000
  -1.000   0.3498   0.00849   0.00231  -0.0652   0.7211   1.0000
  -0.750   0.3762   0.00862   0.00230  -0.0647   0.7076   1.0000
  -0.500   0.4026   0.00875   0.00231  -0.0643   0.6939   1.0000
  -0.250   0.4287   0.00890   0.00234  -0.0639   0.6776   1.0000
   0.000   0.4549   0.00904   0.00238  -0.0634   0.6605   1.0000
   0.250   0.4810   0.00918   0.00243  -0.0630   0.6418   1.0000
   0.500   0.5069   0.00933   0.00248  -0.0625   0.6215   1.0000
   0.750   0.5328   0.00948   0.00254  -0.0620   0.5989   1.0000
   1.000   0.5586   0.00964   0.00262  -0.0616   0.5745   1.0000
   1.250   0.5844   0.00981   0.00270  -0.0611   0.5472   1.0000
   1.500   0.6097   0.01003   0.00279  -0.0606   0.5143   1.0000
   1.750   0.6341   0.01032   0.00291  -0.0599   0.4715   1.0000
   2.000   0.6578   0.01072   0.00306  -0.0592   0.4270   1.0000
   2.250   0.6821   0.01110   0.00327  -0.0586   0.3947   1.0000
   2.500   0.7070   0.01144   0.00351  -0.0582   0.3709   1.0000
   3.000   0.7574   0.01209   0.00404  -0.0574   0.3336   1.0000
   3.250   0.7827   0.01240   0.00432  -0.0571   0.3154   1.0000
   3.500   0.8074   0.01277   0.00463  -0.0567   0.2930   1.0000
   3.750   0.8322   0.01313   0.00493  -0.0563   0.2650   1.0000
   4.000   0.8566   0.01355   0.00525  -0.0559   0.2292   1.0000
   4.250   0.8779   0.01435   0.00569  -0.0551   0.1601   1.0000
   4.500   0.8999   0.01511   0.00627  -0.0545   0.1327   1.0000
   4.750   0.9230   0.01570   0.00683  -0.0539   0.1221   1.0000
   5.000   0.9469   0.01618   0.00737  -0.0534   0.1162   1.0000
   5.250   0.9701   0.01672   0.00795  -0.0528   0.1107   1.0000
   5.500   0.9921   0.01739   0.00865  -0.0521   0.1055   1.0000
   5.750   1.0158   0.01785   0.00923  -0.0516   0.1016   1.0000
   6.000   1.0386   0.01840   0.00987  -0.0510   0.0974   1.0000
   6.250   1.0592   0.01918   0.01062  -0.0502   0.0914   1.0000
   6.500   1.0842   0.01943   0.01102  -0.0499   0.0843   1.0000
   6.750   1.1060   0.02002   0.01163  -0.0493   0.0777   1.0000
   7.000   1.1303   0.02033   0.01210  -0.0490   0.0711   1.0000
   7.250   1.1530   0.02079   0.01259  -0.0485   0.0634   1.0000
   7.500   1.1757   0.02125   0.01310  -0.0480   0.0536   1.0000
   7.750   1.1964   0.02192   0.01376  -0.0473   0.0405   1.0000
   8.000   1.2135   0.02298   0.01474  -0.0461   0.0270   1.0000
   8.250   1.2294   0.02414   0.01595  -0.0447   0.0212   1.0000
   8.500   1.2440   0.02541   0.01729  -0.0431   0.0184   1.0000
   8.750   1.2589   0.02655   0.01860  -0.0415   0.0168   1.0000
   9.000   1.2723   0.02777   0.01997  -0.0399   0.0153   1.0000
   9.250   1.2826   0.02919   0.02151  -0.0380   0.0140   1.0000
   9.500   1.2861   0.03090   0.02338  -0.0352   0.0130   1.0000
   9.750   1.2913   0.03242   0.02505  -0.0326   0.0126   1.0000
  10.000   1.2960   0.03403   0.02685  -0.0304   0.0122   1.0000
  10.250   1.2991   0.03584   0.02884  -0.0283   0.0118   1.0000
  10.500   1.3008   0.03789   0.03106  -0.0264   0.0115   1.0000
  10.750   1.3013   0.04013   0.03349  -0.0249   0.0112   1.0000
  11.000   1.3010   0.04259   0.03615  -0.0237   0.0108   1.0000
  11.250   1.2996   0.04529   0.03902  -0.0229   0.0105   1.0000
  11.500   1.2972   0.04826   0.04216  -0.0225   0.0102   1.0000
  11.750   1.2936   0.05157   0.04562  -0.0226   0.0099   1.0000
  12.000   1.2879   0.05531   0.04951  -0.0232   0.0097   1.0000
  12.250   1.2805   0.05947   0.05384  -0.0241   0.0095   1.0000
  12.500   1.2707   0.06414   0.05866  -0.0254   0.0093   1.0000
  12.750   1.2594   0.06925   0.06393  -0.0271   0.0091   1.0000
  13.000   1.2462   0.07484   0.06968  -0.0291   0.0090   1.0000
  13.500   1.2196   0.08699   0.08217  -0.0344   0.0089   1.0000
  13.750   1.2059   0.09364   0.08900  -0.0377   0.0089   1.0000
  14.000   1.1915   0.10067   0.09621  -0.0413   0.0089   1.0000
  14.250   1.1761   0.10818   0.10388  -0.0452   0.0089   1.0000
  14.500   1.1603   0.11593   0.11177  -0.0492   0.0089   1.0000
  14.750   1.1440   0.12409   0.12008  -0.0536   0.0089   1.0000
  15.000   1.1278   0.13255   0.12867  -0.0582   0.0089   1.0000
  15.250   1.1115   0.14154   0.13782  -0.0632   0.0090   1.0000
  15.500   1.0927   0.15204   0.14848  -0.0690   0.0092   1.0000
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