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

NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 747A315 (naca747a315-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.34 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca747a315-il-1000000-n5.txt
Download as CSV file: xf-naca747a315-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 747A315                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.0914   0.07060   0.06790  -0.0425   1.0000   0.0104
 -17.500  -1.1235   0.06078   0.05788  -0.0492   1.0000   0.0104
 -17.250  -1.1455   0.05392   0.05083  -0.0533   1.0000   0.0104
 -17.000  -1.1603   0.04895   0.04571  -0.0554   1.0000   0.0104
 -16.750  -1.1709   0.04502   0.04163  -0.0564   1.0000   0.0104
 -16.500  -1.1769   0.04193   0.03841  -0.0565   1.0000   0.0105
 -16.250  -1.1781   0.03952   0.03589  -0.0562   1.0000   0.0106
 -16.000  -1.1809   0.03709   0.03333  -0.0555   1.0000   0.0107
 -15.750  -1.1768   0.03538   0.03152  -0.0547   1.0000   0.0107
 -15.500  -1.1733   0.03367   0.02970  -0.0537   1.0000   0.0108
 -15.000  -1.1693   0.03001   0.02582  -0.0512   0.9633   0.0110
 -14.750  -1.1562   0.02867   0.02427  -0.0512   0.9138   0.0112
 -14.500  -1.1524   0.02758   0.02301  -0.0488   0.8857   0.0113
 -14.250  -1.1449   0.02665   0.02194  -0.0468   0.8641   0.0114
 -14.000  -1.1351   0.02583   0.02101  -0.0449   0.8455   0.0115
 -13.750  -1.1243   0.02505   0.02010  -0.0431   0.8283   0.0117
 -13.500  -1.1121   0.02435   0.01929  -0.0414   0.8127   0.0118
 -13.250  -1.0991   0.02368   0.01851  -0.0397   0.7988   0.0120
 -13.000  -1.0859   0.02300   0.01773  -0.0380   0.7861   0.0122
 -12.750  -1.0724   0.02234   0.01695  -0.0363   0.7739   0.0123
 -12.500  -1.0583   0.02169   0.01620  -0.0346   0.7631   0.0125
 -12.250  -1.0434   0.02110   0.01549  -0.0329   0.7530   0.0127
 -12.000  -1.0283   0.02049   0.01479  -0.0312   0.7432   0.0128
 -11.750  -1.0124   0.01996   0.01415  -0.0295   0.7345   0.0130
 -11.500  -0.9964   0.01942   0.01351  -0.0278   0.7262   0.0131
 -11.250  -0.9788   0.01895   0.01294  -0.0263   0.7189   0.0133
 -11.000  -0.9594   0.01847   0.01238  -0.0251   0.7120   0.0134
 -10.750  -0.9406   0.01788   0.01170  -0.0239   0.7055   0.0136
 -10.500  -0.9210   0.01730   0.01106  -0.0228   0.6999   0.0138
 -10.250  -0.8999   0.01684   0.01054  -0.0219   0.6936   0.0141
 -10.000  -0.8781   0.01642   0.01006  -0.0211   0.6876   0.0143
  -9.750  -0.8551   0.01607   0.00967  -0.0205   0.6821   0.0147
  -9.500  -0.8323   0.01569   0.00923  -0.0198   0.6759   0.0149
  -9.250  -0.8092   0.01532   0.00880  -0.0191   0.6701   0.0152
  -9.000  -0.7859   0.01495   0.00837  -0.0185   0.6645   0.0155
  -8.750  -0.7622   0.01460   0.00797  -0.0179   0.6583   0.0157
  -8.500  -0.7383   0.01427   0.00756  -0.0174   0.6527   0.0160
  -8.250  -0.7140   0.01394   0.00719  -0.0169   0.6472   0.0162
  -8.000  -0.6896   0.01364   0.00682  -0.0164   0.6411   0.0164
  -7.750  -0.6658   0.01327   0.00641  -0.0158   0.6355   0.0169
  -7.500  -0.6411   0.01295   0.00607  -0.0154   0.6299   0.0174
  -7.250  -0.6161   0.01268   0.00575  -0.0150   0.6239   0.0178
  -7.000  -0.5909   0.01243   0.00546  -0.0146   0.6189   0.0182
  -6.750  -0.5653   0.01218   0.00518  -0.0143   0.6140   0.0188
  -6.500  -0.5396   0.01195   0.00491  -0.0140   0.6089   0.0193
  -6.000  -0.4881   0.01148   0.00438  -0.0134   0.5999   0.0204
  -5.750  -0.4622   0.01126   0.00415  -0.0132   0.5952   0.0213
  -5.500  -0.4359   0.01108   0.00394  -0.0130   0.5905   0.0224
  -5.250  -0.4094   0.01091   0.00374  -0.0128   0.5863   0.0234
  -5.000  -0.3830   0.01072   0.00354  -0.0127   0.5823   0.0248
  -4.750  -0.3564   0.01054   0.00336  -0.0125   0.5779   0.0263
  -4.500  -0.3296   0.01040   0.00319  -0.0124   0.5736   0.0280
  -4.250  -0.3029   0.01024   0.00302  -0.0123   0.5698   0.0302
  -4.000  -0.2759   0.01009   0.00288  -0.0122   0.5662   0.0326
  -3.750  -0.2489   0.00995   0.00273  -0.0121   0.5623   0.0354
  -3.500  -0.2219   0.00982   0.00260  -0.0121   0.5585   0.0390
  -3.000  -0.1676   0.00955   0.00236  -0.0120   0.5520   0.0500
  -2.750  -0.1404   0.00942   0.00225  -0.0120   0.5487   0.0581
  -2.500  -0.1135   0.00926   0.00214  -0.0119   0.5453   0.0711
  -2.250  -0.0871   0.00906   0.00203  -0.0118   0.5418   0.0961
  -2.000  -0.0615   0.00881   0.00192  -0.0115   0.5386   0.1406
  -1.750  -0.0362   0.00848   0.00181  -0.0113   0.5363   0.2017
  -1.500  -0.0113   0.00813   0.00170  -0.0110   0.5338   0.2721
  -1.250   0.0123   0.00768   0.00157  -0.0105   0.5313   0.3682
  -1.000   0.0363   0.00726   0.00146  -0.0100   0.5288   0.4608
  -0.750   0.0594   0.00680   0.00134  -0.0094   0.5264   0.5611
  -0.500   0.0781   0.00614   0.00131  -0.0077   0.5241   0.7395
  -0.250   0.1052   0.00615   0.00141  -0.0075   0.5221   0.7783
   0.000   0.1334   0.00620   0.00149  -0.0075   0.5204   0.7973
   0.250   0.1620   0.00625   0.00154  -0.0076   0.5186   0.8070
   0.500   0.1908   0.00629   0.00159  -0.0079   0.5167   0.8125
   0.750   0.2199   0.00634   0.00162  -0.0082   0.5148   0.8162
   1.000   0.2490   0.00638   0.00163  -0.0085   0.5130   0.8186
   1.250   0.2781   0.00642   0.00165  -0.0088   0.5112   0.8208
   1.500   0.3069   0.00646   0.00169  -0.0091   0.5092   0.8232
   1.750   0.3357   0.00651   0.00173  -0.0094   0.5072   0.8253
   2.000   0.3648   0.00655   0.00177  -0.0098   0.5058   0.8268
   2.250   0.3940   0.00658   0.00181  -0.0102   0.5046   0.8280
   2.500   0.4231   0.00661   0.00186  -0.0105   0.5031   0.8294
   2.750   0.4522   0.00665   0.00190  -0.0109   0.5008   0.8308
   3.000   0.4812   0.00670   0.00195  -0.0113   0.4976   0.8322
   3.250   0.5100   0.00676   0.00200  -0.0116   0.4944   0.8334
   3.500   0.5387   0.00683   0.00206  -0.0120   0.4916   0.8346
   3.750   0.5676   0.00688   0.00212  -0.0123   0.4886   0.8357
   4.000   0.5966   0.00692   0.00217  -0.0127   0.4837   0.8367
   4.250   0.6249   0.00699   0.00223  -0.0130   0.4767   0.8380
   4.500   0.6533   0.00704   0.00230  -0.0133   0.4685   0.8394
   4.750   0.6809   0.00714   0.00238  -0.0134   0.4585   0.8409
   5.000   0.7090   0.00722   0.00247  -0.0137   0.4462   0.8424
   5.250   0.7365   0.00734   0.00256  -0.0138   0.4310   0.8439
   5.500   0.7619   0.00762   0.00271  -0.0137   0.3955   0.8455
   5.750   0.7802   0.00843   0.00318  -0.0126   0.3239   0.8474
   6.000   0.7992   0.00915   0.00364  -0.0116   0.2685   0.8493
   6.250   0.8142   0.01007   0.00423  -0.0101   0.2014   0.8514
   6.500   0.8304   0.01082   0.00473  -0.0087   0.1538   0.8533
   6.750   0.8452   0.01155   0.00526  -0.0070   0.1112   0.8555
   7.000   0.8612   0.01212   0.00572  -0.0055   0.0849   0.8578
   7.250   0.8786   0.01257   0.00612  -0.0041   0.0694   0.8602
   7.500   0.8936   0.01308   0.00656  -0.0024   0.0544   0.8629
   7.750   0.9040   0.01358   0.00701   0.0001   0.0411   0.8662
   8.000   0.9132   0.01409   0.00750   0.0029   0.0343   0.8697
   8.250   0.9241   0.01462   0.00804   0.0051   0.0300   0.8730
   8.500   0.9352   0.01520   0.00863   0.0072   0.0268   0.8766
   8.750   0.9482   0.01575   0.00922   0.0088   0.0249   0.8804
   9.000   0.9604   0.01640   0.00989   0.0105   0.0231   0.8844
   9.500   0.9857   0.01774   0.01130   0.0134   0.0202   0.8926
   9.750   0.9974   0.01851   0.01210   0.0148   0.0190   0.8977
  10.000   1.0093   0.01932   0.01295   0.0161   0.0180   0.9029
  10.250   1.0212   0.02012   0.01380   0.0174   0.0166   0.9085
  10.500   1.0326   0.02099   0.01472   0.0186   0.0159   0.9157
  10.750   1.0428   0.02196   0.01573   0.0199   0.0148   0.9239
  11.000   1.0547   0.02287   0.01671   0.0209   0.0142   0.9344
  11.250   1.0694   0.02388   0.01780   0.0211   0.0135   0.9482
  11.500   1.0936   0.02502   0.01901   0.0192   0.0130   0.9620
  11.750   1.1213   0.02635   0.02037   0.0161   0.0123   0.9754
  12.000   1.1341   0.02765   0.02171   0.0162   0.0118   1.0000
  12.250   1.1447   0.02888   0.02298   0.0168   0.0113   1.0000
  12.500   1.1549   0.03015   0.02429   0.0174   0.0112   1.0000
  12.750   1.1643   0.03152   0.02569   0.0180   0.0107   1.0000
  13.000   1.1735   0.03290   0.02712   0.0185   0.0106   1.0000
  13.250   1.1824   0.03435   0.02860   0.0190   0.0104   1.0000
  13.500   1.1906   0.03590   0.03019   0.0195   0.0102   1.0000
  13.750   1.1989   0.03747   0.03179   0.0199   0.0100   1.0000
  14.000   1.2047   0.03929   0.03366   0.0203   0.0097   1.0000
  14.250   1.2105   0.04115   0.03556   0.0206   0.0095   1.0000
  14.500   1.2183   0.04289   0.03736   0.0208   0.0094   1.0000
  14.750   1.2262   0.04463   0.03914   0.0210   0.0094   1.0000
  15.000   1.2326   0.04654   0.04112   0.0211   0.0093   1.0000
  15.250   1.2388   0.04851   0.04315   0.0212   0.0092   1.0000
  15.500   1.2457   0.05045   0.04514   0.0212   0.0091   1.0000
  15.750   1.2507   0.05261   0.04737   0.0211   0.0090   1.0000
  16.000   1.2563   0.05472   0.04954   0.0210   0.0088   1.0000
  16.250   1.2615   0.05694   0.05182   0.0208   0.0087   1.0000
  16.500   1.2646   0.05942   0.05436   0.0206   0.0086   1.0000
  16.750   1.2693   0.06177   0.05677   0.0203   0.0086   1.0000
  17.000   1.2735   0.06419   0.05926   0.0199   0.0085   1.0000
  17.250   1.2751   0.06696   0.06209   0.0194   0.0084   1.0000
  17.500   1.2773   0.06971   0.06491   0.0189   0.0083   1.0000
  17.750   1.2796   0.07252   0.06778   0.0182   0.0081   1.0000
  18.000   1.2815   0.07540   0.07074   0.0175   0.0081   1.0000
  18.250   1.2811   0.07863   0.07405   0.0167   0.0081   1.0000
  18.500   1.2806   0.08193   0.07742   0.0157   0.0080   1.0000
  18.750   1.2800   0.08532   0.08089   0.0147   0.0079   1.0000
  19.000   1.2773   0.08909   0.08474   0.0134   0.0079   1.0000
  19.250   1.2760   0.09270   0.08843   0.0121   0.0078   1.0000
<< Back to NACA 747A315 (naca747a315-il)

Polar data table (+)

Polar graphs


<< Back to NACA 747A315 (naca747a315-il)