Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

N-14 (n14-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-14 (n14-il)
Reynolds number: 50,000
Max Cl/Cd: 27.52 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n14-il-50000-n5.txt
Download as CSV file: xf-n14-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-14                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6653   0.09634   0.08838  -0.0327   1.0000   0.0743
 -11.750  -0.7008   0.08527   0.07732  -0.0398   1.0000   0.0736
 -11.500  -0.7410   0.07631   0.06829  -0.0449   1.0000   0.0727
 -11.250  -0.7769   0.06996   0.06182  -0.0465   1.0000   0.0721
 -11.000  -0.8069   0.06531   0.05702  -0.0455   1.0000   0.0719
 -10.750  -0.8313   0.06170   0.05323  -0.0428   1.0000   0.0720
 -10.500  -0.8507   0.05864   0.04998  -0.0390   1.0000   0.0723
 -10.250  -0.8636   0.05555   0.04663  -0.0357   1.0000   0.0730
 -10.000  -0.8716   0.05262   0.04338  -0.0323   1.0000   0.0739
  -9.750  -0.8773   0.04985   0.04025  -0.0289   1.0000   0.0756
  -9.500  -0.8801   0.04714   0.03710  -0.0255   1.0000   0.0775
  -9.250  -0.8680   0.04560   0.03555  -0.0237   1.0000   0.0797
  -9.000  -0.8584   0.04376   0.03352  -0.0214   1.0000   0.0820
  -8.750  -0.8477   0.04168   0.03116  -0.0192   1.0000   0.0842
  -8.500  -0.8350   0.03963   0.02876  -0.0171   1.0000   0.0867
  -8.250  -0.8204   0.03792   0.02683  -0.0152   1.0000   0.0902
  -8.000  -0.8048   0.03662   0.02545  -0.0135   1.0000   0.0944
  -7.750  -0.7879   0.03514   0.02369  -0.0118   1.0000   0.0995
  -7.500  -0.7677   0.03359   0.02203  -0.0106   1.0000   0.1042
  -7.250  -0.7478   0.03221   0.02062  -0.0093   1.0000   0.1103
  -7.000  -0.7277   0.03088   0.01916  -0.0080   1.0000   0.1186
  -6.750  -0.7099   0.02970   0.01793  -0.0064   1.0000   0.1301
  -6.500  -0.6935   0.02856   0.01687  -0.0046   1.0000   0.1433
  -6.250  -0.6773   0.02755   0.01591  -0.0027   1.0000   0.1584
  -6.000  -0.6620   0.02670   0.01512  -0.0007   1.0000   0.1760
  -5.750  -0.6475   0.02594   0.01443   0.0014   1.0000   0.1957
  -5.500  -0.6327   0.02525   0.01380   0.0035   1.0000   0.2203
  -5.250  -0.6197   0.02457   0.01327   0.0058   1.0000   0.2508
  -5.000  -0.6072   0.02386   0.01276   0.0083   1.0000   0.2862
  -4.750  -0.5942   0.02310   0.01221   0.0107   1.0000   0.3241
  -4.500  -0.5805   0.02236   0.01165   0.0132   1.0000   0.3649
  -4.250  -0.5668   0.02170   0.01120   0.0157   1.0000   0.4102
  -4.000  -0.5530   0.02110   0.01089   0.0183   1.0000   0.4637
  -3.750  -0.5387   0.02064   0.01076   0.0212   1.0000   0.5281
  -3.500  -0.5207   0.02039   0.01079   0.0238   1.0000   0.5998
  -3.250  -0.4973   0.02040   0.01098   0.0255   1.0000   0.6655
  -3.000  -0.4722   0.02056   0.01119   0.0269   1.0000   0.7211
  -2.750  -0.4469   0.02081   0.01141   0.0283   1.0000   0.7704
  -2.500  -0.4157   0.02119   0.01173   0.0286   1.0000   0.8121
  -2.250  -0.3814   0.02161   0.01204   0.0282   1.0000   0.8474
  -2.000  -0.3380   0.02215   0.01245   0.0261   1.0000   0.8778
  -1.750  -0.2833   0.02275   0.01287   0.0217   1.0000   0.9042
  -1.500  -0.2304   0.02314   0.01313   0.0172   1.0000   0.9257
  -1.250  -0.1850   0.02336   0.01322   0.0135   1.0000   0.9449
  -1.000  -0.1381   0.02347   0.01324   0.0093   1.0000   0.9611
  -0.750  -0.0841   0.02352   0.01321   0.0035   1.0000   0.9777
  -0.500  -0.0261   0.02348   0.01312  -0.0032   1.0000   0.9947
  -0.250  -0.0050   0.02343   0.01304  -0.0035   1.0000   1.0000
   0.000  -0.0041   0.02343   0.01303  -0.0001   1.0000   1.0000
   0.250   0.0039   0.02344   0.01304   0.0021   0.9983   1.0000
   0.500   0.0690   0.02344   0.01306  -0.0060   0.9796   1.0000
   0.750   0.1240   0.02333   0.01300  -0.0119   0.9620   1.0000
   1.000   0.1674   0.02323   0.01296  -0.0156   0.9474   1.0000
   1.250   0.2086   0.02310   0.01291  -0.0187   0.9325   1.0000
   1.500   0.2500   0.02293   0.01285  -0.0217   0.9171   1.0000
   1.750   0.2937   0.02269   0.01273  -0.0249   0.9011   1.0000
   2.000   0.3391   0.02240   0.01259  -0.0281   0.8842   1.0000
   2.250   0.3741   0.02214   0.01247  -0.0293   0.8625   1.0000
   2.500   0.4135   0.02179   0.01226  -0.0309   0.8395   1.0000
   2.750   0.4487   0.02138   0.01198  -0.0314   0.8078   1.0000
   3.000   0.4768   0.02102   0.01168  -0.0303   0.7652   1.0000
   3.250   0.5007   0.02074   0.01142  -0.0285   0.7146   1.0000
   3.500   0.5244   0.02056   0.01117  -0.0266   0.6588   1.0000
   3.750   0.5475   0.02055   0.01098  -0.0247   0.6007   1.0000
   4.000   0.5660   0.02077   0.01099  -0.0223   0.5442   1.0000
   4.250   0.5826   0.02117   0.01115  -0.0198   0.4908   1.0000
   4.500   0.5971   0.02171   0.01141  -0.0172   0.4414   1.0000
   4.750   0.6097   0.02234   0.01177  -0.0144   0.3939   1.0000
   5.000   0.6215   0.02302   0.01221  -0.0116   0.3495   1.0000
   5.250   0.6337   0.02368   0.01273  -0.0089   0.3093   1.0000
   5.500   0.6464   0.02433   0.01329  -0.0064   0.2729   1.0000
   5.750   0.6594   0.02501   0.01388  -0.0039   0.2394   1.0000
   6.000   0.6716   0.02576   0.01449  -0.0014   0.2075   1.0000
   6.250   0.6847   0.02664   0.01525   0.0010   0.1809   1.0000
   6.500   0.6982   0.02768   0.01610   0.0032   0.1617   1.0000
   6.750   0.7139   0.02875   0.01712   0.0052   0.1457   1.0000
   7.000   0.7299   0.02982   0.01817   0.0070   0.1330   1.0000
   7.250   0.7487   0.03095   0.01940   0.0086   0.1231   1.0000
   7.500   0.7671   0.03221   0.02059   0.0101   0.1167   1.0000
   7.750   0.7867   0.03345   0.02209   0.0115   0.1098   1.0000
   8.000   0.8035   0.03465   0.02331   0.0131   0.1038   1.0000
   8.250   0.8220   0.03615   0.02495   0.0146   0.0993   1.0000
   8.500   0.8395   0.03781   0.02688   0.0161   0.0953   1.0000
   8.750   0.8545   0.03930   0.02852   0.0179   0.0913   1.0000
   9.000   0.8690   0.04087   0.03010   0.0196   0.0877   1.0000
   9.250   0.8780   0.04292   0.03258   0.0221   0.0844   1.0000
   9.500   0.8864   0.04503   0.03499   0.0245   0.0817   1.0000
   9.750   0.8948   0.04683   0.03693   0.0268   0.0788   1.0000
  10.000   0.9053   0.04854   0.03860   0.0286   0.0761   1.0000
  10.250   0.8987   0.05135   0.04189   0.0323   0.0742   1.0000
  10.500   0.8908   0.05428   0.04517   0.0357   0.0729   1.0000
  10.750   0.8784   0.05721   0.04839   0.0392   0.0718   1.0000
  11.000   0.8608   0.06009   0.05148   0.0429   0.0709   1.0000
  11.250   0.8402   0.06337   0.05495   0.0458   0.0702   1.0000
  11.500   0.8147   0.06749   0.05926   0.0472   0.0700   1.0000
  11.750   0.7809   0.07323   0.06518   0.0464   0.0706   1.0000
  12.000   0.7397   0.08149   0.07356   0.0424   0.0719   1.0000
  12.250   0.6995   0.09223   0.08434   0.0356   0.0732   1.0000
<< Back to N-14 (n14-il)

Polar data table (+)

Polar graphs


<< Back to N-14 (n14-il)