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

NACA CYH (nacacyh-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA CYH (nacacyh-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.41 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacacyh-il-1000000.txt
Download as CSV file: xf-nacacyh-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA CYH                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.9895   0.04458   0.04221  -0.0614   1.0000   0.0174
 -14.250  -1.0079   0.04010   0.03752  -0.0627   1.0000   0.0175
 -14.000  -1.0135   0.03766   0.03490  -0.0615   1.0000   0.0176
 -13.750  -1.0127   0.03599   0.03309  -0.0594   1.0000   0.0177
 -13.500  -1.0338   0.03146   0.02820  -0.0564   1.0000   0.0181
 -13.250  -1.0202   0.03030   0.02698  -0.0551   1.0000   0.0184
 -13.000  -1.0014   0.02970   0.02636  -0.0540   1.0000   0.0186
 -12.750  -0.9817   0.02917   0.02579  -0.0530   1.0000   0.0188
 -12.500  -0.9620   0.02859   0.02517  -0.0520   1.0000   0.0191
 -12.250  -0.9420   0.02801   0.02454  -0.0510   1.0000   0.0194
 -12.000  -0.9216   0.02743   0.02391  -0.0499   1.0000   0.0198
 -11.750  -0.9024   0.02665   0.02304  -0.0488   1.0000   0.0202
 -11.500  -0.8841   0.02570   0.02195  -0.0475   1.0000   0.0207
 -11.250  -0.8657   0.02476   0.02087  -0.0462   1.0000   0.0211
 -11.000  -0.8461   0.02411   0.02009  -0.0448   1.0000   0.0214
 -10.750  -0.8257   0.02380   0.01968  -0.0434   1.0000   0.0216
 -10.500  -0.8123   0.02076   0.01639  -0.0422   0.9972   0.0224
 -10.250  -0.7791   0.02020   0.01581  -0.0435   0.9916   0.0228
 -10.000  -0.7460   0.01973   0.01529  -0.0448   0.9830   0.0233
  -9.750  -0.7156   0.01909   0.01459  -0.0454   0.9695   0.0238
  -9.500  -0.6904   0.01844   0.01382  -0.0448   0.9483   0.0243
  -9.250  -0.6685   0.01783   0.01306  -0.0434   0.9220   0.0248
  -9.000  -0.6464   0.01738   0.01243  -0.0420   0.8929   0.0253
  -8.750  -0.6225   0.01709   0.01198  -0.0409   0.8663   0.0257
  -8.500  -0.5978   0.01685   0.01157  -0.0400   0.8444   0.0260
  -8.250  -0.5747   0.01580   0.01030  -0.0391   0.8271   0.0264
  -8.000  -0.5518   0.01455   0.00891  -0.0382   0.8127   0.0270
  -7.750  -0.5265   0.01398   0.00827  -0.0377   0.8005   0.0276
  -7.500  -0.5004   0.01361   0.00784  -0.0372   0.7902   0.0281
  -7.250  -0.4742   0.01322   0.00737  -0.0367   0.7808   0.0287
  -7.000  -0.4478   0.01279   0.00688  -0.0362   0.7725   0.0291
  -6.750  -0.4214   0.01241   0.00642  -0.0357   0.7644   0.0296
  -6.500  -0.3947   0.01202   0.00598  -0.0353   0.7568   0.0301
  -6.250  -0.3680   0.01170   0.00557  -0.0349   0.7487   0.0306
  -6.000  -0.3409   0.01141   0.00524  -0.0345   0.7410   0.0310
  -5.750  -0.3135   0.01121   0.00498  -0.0342   0.7337   0.0314
  -5.500  -0.2867   0.01085   0.00456  -0.0338   0.7275   0.0317
  -5.250  -0.2609   0.01029   0.00394  -0.0333   0.7206   0.0325
  -5.000  -0.2343   0.00996   0.00355  -0.0328   0.7140   0.0333
  -4.750  -0.2068   0.00969   0.00326  -0.0326   0.7080   0.0341
  -4.500  -0.1793   0.00948   0.00302  -0.0323   0.7015   0.0349
  -4.250  -0.1516   0.00930   0.00280  -0.0321   0.6949   0.0359
  -4.000  -0.1238   0.00913   0.00260  -0.0319   0.6874   0.0369
  -3.750  -0.0959   0.00900   0.00244  -0.0317   0.6809   0.0378
  -3.500  -0.0680   0.00880   0.00221  -0.0315   0.6749   0.0394
  -3.250  -0.0402   0.00863   0.00204  -0.0314   0.6689   0.0421
  -3.000  -0.0122   0.00850   0.00190  -0.0312   0.6630   0.0453
  -2.750   0.0153   0.00827   0.00177  -0.0311   0.6562   0.0669
  -2.500   0.0426   0.00807   0.00166  -0.0309   0.6495   0.0977
  -2.250   0.0702   0.00785   0.00157  -0.0308   0.6424   0.1327
  -2.000   0.0970   0.00760   0.00149  -0.0306   0.6355   0.1889
  -1.750   0.1243   0.00738   0.00144  -0.0305   0.6284   0.2450
  -1.500   0.1515   0.00721   0.00140  -0.0303   0.6207   0.2931
  -1.250   0.1784   0.00697   0.00136  -0.0302   0.6131   0.3596
  -1.000   0.2035   0.00658   0.00131  -0.0298   0.6045   0.4769
  -0.750   0.2191   0.00548   0.00127  -0.0274   0.5961   0.7939
  -0.500   0.2430   0.00536   0.00134  -0.0262   0.5865   0.8771
  -0.250   0.2693   0.00536   0.00139  -0.0255   0.5763   0.9109
   0.000   0.2963   0.00542   0.00145  -0.0251   0.5663   0.9317
   0.250   0.3235   0.00552   0.00152  -0.0247   0.5554   0.9489
   0.500   0.3522   0.00564   0.00161  -0.0246   0.5435   0.9623
   0.750   0.3815   0.00577   0.00168  -0.0247   0.5310   0.9712
   1.000   0.4166   0.00591   0.00176  -0.0262   0.5163   0.9752
   1.250   0.4521   0.00609   0.00186  -0.0279   0.4991   0.9804
   1.500   0.4897   0.00628   0.00196  -0.0300   0.4798   0.9837
   1.750   0.5283   0.00646   0.00203  -0.0325   0.4576   0.9853
   2.000   0.5645   0.00669   0.00212  -0.0346   0.4286   0.9872
   2.250   0.5994   0.00695   0.00224  -0.0363   0.3966   0.9894
   2.500   0.6329   0.00721   0.00236  -0.0379   0.3715   0.9919
   2.750   0.6672   0.00743   0.00249  -0.0395   0.3539   0.9941
   3.000   0.7040   0.00759   0.00258  -0.0417   0.3412   0.9954
   3.250   0.7373   0.00772   0.00267  -0.0432   0.3310   0.9965
   3.500   0.7690   0.00787   0.00278  -0.0444   0.3218   0.9975
   3.750   0.8011   0.00797   0.00287  -0.0456   0.3157   0.9986
   4.000   0.8330   0.00813   0.00299  -0.0468   0.3084   0.9996
   4.250   0.8612   0.00822   0.00309  -0.0472   0.3026   1.0000
   4.500   0.8852   0.00835   0.00320  -0.0467   0.2966   1.0000
   4.750   0.9088   0.00849   0.00332  -0.0462   0.2909   1.0000
   5.000   0.9326   0.00859   0.00344  -0.0456   0.2837   1.0000
   5.250   0.9555   0.00876   0.00357  -0.0450   0.2748   1.0000
   5.500   0.9787   0.00890   0.00370  -0.0443   0.2657   1.0000
   5.750   1.0014   0.00907   0.00384  -0.0437   0.2554   1.0000
   6.000   1.0236   0.00928   0.00401  -0.0429   0.2418   1.0000
   6.250   1.0454   0.00953   0.00420  -0.0420   0.2263   1.0000
   6.500   1.0655   0.00990   0.00445  -0.0410   0.2030   1.0000
   6.750   1.0839   0.01040   0.00480  -0.0396   0.1740   1.0000
   7.000   1.1023   0.01090   0.00517  -0.0383   0.1507   1.0000
   7.250   1.1211   0.01138   0.00555  -0.0371   0.1320   1.0000
   7.500   1.1401   0.01186   0.00593  -0.0359   0.1141   1.0000
   7.750   1.1593   0.01231   0.00632  -0.0348   0.1005   1.0000
   8.000   1.1792   0.01273   0.00669  -0.0338   0.0907   1.0000
   8.250   1.1991   0.01319   0.00709  -0.0328   0.0817   1.0000
   8.500   1.2200   0.01357   0.00746  -0.0321   0.0749   1.0000
   8.750   1.2404   0.01402   0.00787  -0.0313   0.0664   1.0000
   9.000   1.2584   0.01464   0.00840  -0.0302   0.0526   1.0000
   9.250   1.2668   0.01597   0.00946  -0.0278   0.0217   1.0000
   9.500   1.2826   0.01672   0.01021  -0.0265   0.0175   1.0000
   9.750   1.2998   0.01734   0.01087  -0.0254   0.0159   1.0000
  10.000   1.3165   0.01795   0.01153  -0.0242   0.0150   1.0000
  10.250   1.3291   0.01865   0.01227  -0.0224   0.0142   1.0000
  10.500   1.3388   0.01954   0.01322  -0.0203   0.0134   1.0000
  10.750   1.3512   0.02032   0.01406  -0.0188   0.0130   1.0000
  11.000   1.3639   0.02114   0.01495  -0.0176   0.0126   1.0000
  11.250   1.3754   0.02210   0.01597  -0.0163   0.0122   1.0000
  11.500   1.3859   0.02319   0.01713  -0.0152   0.0118   1.0000
  11.750   1.3953   0.02444   0.01844  -0.0143   0.0115   1.0000
  12.000   1.4027   0.02593   0.02000  -0.0134   0.0112   1.0000
  12.250   1.4067   0.02782   0.02198  -0.0126   0.0109   1.0000
  12.500   1.4047   0.03037   0.02464  -0.0117   0.0105   1.0000
  12.750   1.4100   0.03233   0.02669  -0.0114   0.0104   1.0000
  13.000   1.4171   0.03417   0.02860  -0.0113   0.0102   1.0000
  13.250   1.4221   0.03625   0.03076  -0.0111   0.0100   1.0000
  13.500   1.4256   0.03853   0.03313  -0.0111   0.0098   1.0000
  13.750   1.4270   0.04107   0.03575  -0.0112   0.0096   1.0000
  14.000   1.4269   0.04385   0.03862  -0.0113   0.0094   1.0000
  14.250   1.4249   0.04690   0.04176  -0.0116   0.0093   1.0000
  14.500   1.4219   0.05014   0.04509  -0.0120   0.0092   1.0000
  14.750   1.4172   0.05374   0.04879  -0.0126   0.0090   1.0000
  15.000   1.4113   0.05760   0.05274  -0.0134   0.0089   1.0000
  15.250   1.4043   0.06177   0.05700  -0.0144   0.0088   1.0000
  15.500   1.3959   0.06624   0.06158  -0.0157   0.0087   1.0000
  15.750   1.3858   0.07106   0.06649  -0.0170   0.0087   1.0000
  16.000   1.3746   0.07615   0.07169  -0.0186   0.0086   1.0000
  16.250   1.3620   0.08157   0.07721  -0.0203   0.0085   1.0000
  16.500   1.3487   0.08713   0.08287  -0.0221   0.0085   1.0000
  16.750   1.3346   0.09291   0.08875  -0.0241   0.0084   1.0000
  17.000   1.3203   0.09877   0.09470  -0.0261   0.0083   1.0000
  17.250   1.3056   0.10466   0.10069  -0.0281   0.0082   1.0000
<< Back to NACA CYH (nacacyh-il)

Polar data table (+)

Polar graphs


<< Back to NACA CYH (nacacyh-il)