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N-9 (n9-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 100,000
Max Cl/Cd: 53.28 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n9-il-100000.txt
Download as CSV file: xf-n9-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3633   0.10240   0.09758  -0.0182   1.0000   0.0950
 -10.500  -0.3644   0.09899   0.09420  -0.0193   1.0000   0.0983
 -10.250  -0.4742   0.10504   0.10001  -0.0131   1.0000   0.0909
 -10.000  -0.4657   0.10170   0.09668  -0.0129   1.0000   0.0943
  -9.750  -0.4641   0.09838   0.09341  -0.0147   1.0000   0.0977
  -9.500  -0.4752   0.09553   0.09066  -0.0198   1.0000   0.1009
  -9.250  -0.4925   0.09182   0.08701  -0.0330   1.0000   0.1020
  -9.000  -0.4752   0.08698   0.08224  -0.0245   1.0000   0.1041
  -8.750  -0.4637   0.08384   0.07912  -0.0222   1.0000   0.1073
  -8.500  -0.4597   0.08021   0.07551  -0.0247   1.0000   0.1115
  -8.250  -0.4681   0.07455   0.06973  -0.0379   1.0000   0.1171
  -8.000  -0.4546   0.07128   0.06659  -0.0325   1.0000   0.1196
  -7.750  -0.4451   0.06835   0.06367  -0.0318   1.0000   0.1250
  -7.500  -0.4411   0.06365   0.05888  -0.0363   1.0000   0.1334
  -7.250  -0.4330   0.06033   0.05538  -0.0390   1.0000   0.1461
  -7.000  -0.4208   0.05784   0.05306  -0.0349   1.0000   0.1514
  -6.750  -0.4107   0.05445   0.04959  -0.0359   1.0000   0.1631
  -6.500  -0.3993   0.05151   0.04657  -0.0360   1.0000   0.1766
  -6.250  -0.3657   0.03709   0.03011  -0.0434   1.0000   0.0883
  -6.000  -0.3461   0.03403   0.02672  -0.0425   1.0000   0.0875
  -5.750  -0.3258   0.03077   0.02312  -0.0417   1.0000   0.0870
  -5.500  -0.3037   0.02791   0.01986  -0.0410   1.0000   0.0865
  -5.250  -0.2807   0.02560   0.01709  -0.0403   1.0000   0.0893
  -5.000  -0.2581   0.02397   0.01543  -0.0397   1.0000   0.0939
  -4.750  -0.2334   0.02246   0.01359  -0.0390   1.0000   0.0969
  -4.500  -0.2086   0.02135   0.01213  -0.0383   1.0000   0.1032
  -4.250  -0.1839   0.02006   0.01085  -0.0379   1.0000   0.1095
  -4.000  -0.1587   0.01922   0.00980  -0.0374   1.0000   0.1170
  -3.750  -0.1333   0.01828   0.00894  -0.0373   1.0000   0.1301
  -3.500  -0.1077   0.01736   0.00821  -0.0372   1.0000   0.1466
  -3.250  -0.0834   0.01684   0.00794  -0.0370   1.0000   0.1783
  -3.000  -0.0585   0.01632   0.00769  -0.0371   1.0000   0.2349
  -2.750  -0.0308   0.01400   0.00761  -0.0371   1.0000   0.6948
  -2.500  -0.0160   0.01380   0.00773  -0.0345   1.0000   1.0000
  -2.250   0.0339   0.01412   0.00768  -0.0394   0.9904   1.0000
  -2.000   0.0909   0.01430   0.00758  -0.0454   0.9769   1.0000
  -1.750   0.1443   0.01435   0.00742  -0.0506   0.9633   1.0000
  -1.500   0.1916   0.01441   0.00733  -0.0546   0.9515   1.0000
  -1.250   0.2385   0.01443   0.00724  -0.0585   0.9413   1.0000
  -1.000   0.2879   0.01436   0.00709  -0.0627   0.9322   1.0000
  -0.750   0.3298   0.01432   0.00699  -0.0653   0.9203   1.0000
  -0.500   0.3705   0.01428   0.00690  -0.0676   0.9084   1.0000
  -0.250   0.4091   0.01423   0.00682  -0.0693   0.8959   1.0000
   0.000   0.4439   0.01421   0.00678  -0.0702   0.8820   1.0000
   0.250   0.4751   0.01422   0.00679  -0.0703   0.8666   1.0000
   0.500   0.5040   0.01422   0.00679  -0.0699   0.8501   1.0000
   0.750   0.5318   0.01419   0.00675  -0.0691   0.8329   1.0000
   1.000   0.5586   0.01407   0.00662  -0.0680   0.8136   1.0000
   1.250   0.5832   0.01395   0.00649  -0.0663   0.7902   1.0000
   1.500   0.6086   0.01383   0.00632  -0.0648   0.7661   1.0000
   1.750   0.6345   0.01378   0.00618  -0.0634   0.7414   1.0000
   2.000   0.6594   0.01388   0.00621  -0.0620   0.7138   1.0000
   2.250   0.6837   0.01408   0.00630  -0.0606   0.6837   1.0000
   2.500   0.7079   0.01431   0.00647  -0.0593   0.6534   1.0000
   2.750   0.7318   0.01456   0.00664  -0.0581   0.6227   1.0000
   3.000   0.7553   0.01478   0.00685  -0.0569   0.5896   1.0000
   3.250   0.7788   0.01501   0.00703  -0.0557   0.5565   1.0000
   3.500   0.8021   0.01524   0.00718  -0.0545   0.5230   1.0000
   3.750   0.8256   0.01555   0.00741  -0.0535   0.4922   1.0000
   4.000   0.8487   0.01593   0.00772  -0.0525   0.4616   1.0000
   4.250   0.8710   0.01638   0.00809  -0.0513   0.4270   1.0000
   4.500   0.8918   0.01697   0.00852  -0.0500   0.3870   1.0000
   4.750   0.9109   0.01772   0.00911  -0.0485   0.3338   1.0000
   5.000   0.9278   0.01879   0.00986  -0.0467   0.2681   1.0000
   5.250   0.9469   0.01982   0.01060  -0.0454   0.2256   1.0000
   5.500   0.9681   0.02079   0.01146  -0.0443   0.2023   1.0000
   5.750   0.9896   0.02181   0.01238  -0.0434   0.1866   1.0000
   6.000   1.0115   0.02288   0.01342  -0.0425   0.1734   1.0000
   6.250   1.0342   0.02407   0.01462  -0.0418   0.1625   1.0000
   6.500   1.0566   0.02540   0.01593  -0.0411   0.1513   1.0000
   6.750   1.0784   0.02685   0.01737  -0.0404   0.1391   1.0000
   7.000   1.0986   0.02838   0.01890  -0.0397   0.1252   1.0000
   7.250   1.1186   0.03020   0.02079  -0.0389   0.1117   1.0000
   7.500   1.1372   0.03225   0.02294  -0.0379   0.0979   1.0000
   7.750   1.1550   0.03457   0.02536  -0.0368   0.0853   1.0000
   8.000   1.1724   0.03645   0.02727  -0.0357   0.0750   1.0000
   8.250   1.1859   0.03854   0.02986  -0.0336   0.0676   1.0000
   8.500   1.2038   0.04099   0.03230  -0.0329   0.0627   1.0000
   8.750   1.2116   0.04399   0.03592  -0.0304   0.0594   1.0000
   9.000   1.2206   0.04637   0.03866  -0.0284   0.0557   1.0000
   9.250   1.2326   0.04841   0.04079  -0.0271   0.0528   1.0000
   9.500   1.2386   0.05277   0.04534  -0.0257   0.0513   1.0000
   9.750   1.2325   0.05664   0.04969  -0.0228   0.0508   1.0000
  10.000   1.2216   0.06063   0.05410  -0.0199   0.0506   1.0000
  10.250   1.2057   0.06450   0.05831  -0.0169   0.0505   1.0000
  10.500   1.1862   0.06843   0.06250  -0.0143   0.0506   1.0000
  10.750   1.1654   0.07280   0.06710  -0.0130   0.0507   1.0000
  11.000   1.1438   0.07774   0.07224  -0.0130   0.0509   1.0000
  11.250   1.1224   0.08336   0.07803  -0.0142   0.0511   1.0000
  11.500   0.7718   0.12047   0.11580  -0.0298   0.0814   1.0000
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