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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 500,000
Max Cl/Cd: 62.33 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1408-il-500000-n5.txt
Download as CSV file: xf-naca1408-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7983   0.09396   0.09175   0.0040   1.0000   0.0064
 -11.750  -0.9559   0.04857   0.04613  -0.0313   1.0000   0.0053
 -11.500  -0.9828   0.04162   0.03885  -0.0344   1.0000   0.0052
 -11.250  -0.9881   0.03723   0.03414  -0.0347   1.0000   0.0053
 -11.000  -0.9843   0.03389   0.03048  -0.0344   1.0000   0.0055
 -10.750  -0.9755   0.03111   0.02738  -0.0338   1.0000   0.0057
 -10.500  -0.9630   0.02875   0.02473  -0.0332   1.0000   0.0059
 -10.250  -0.9479   0.02672   0.02238  -0.0325   1.0000   0.0061
 -10.000  -0.9306   0.02500   0.02039  -0.0317   1.0000   0.0063
  -9.750  -0.9145   0.02295   0.01807  -0.0309   1.0000   0.0065
  -9.500  -0.8954   0.02149   0.01642  -0.0301   1.0000   0.0068
  -9.250  -0.8742   0.02041   0.01521  -0.0295   1.0000   0.0071
  -9.000  -0.8523   0.01946   0.01412  -0.0290   1.0000   0.0074
  -8.750  -0.8300   0.01854   0.01306  -0.0283   1.0000   0.0078
  -8.500  -0.8075   0.01766   0.01203  -0.0277   1.0000   0.0082
  -8.250  -0.7848   0.01683   0.01107  -0.0270   1.0000   0.0087
  -8.000  -0.7613   0.01619   0.01026  -0.0264   1.0000   0.0091
  -7.750  -0.7393   0.01525   0.00924  -0.0256   1.0000   0.0101
  -7.500  -0.7157   0.01471   0.00863  -0.0249   1.0000   0.0110
  -7.250  -0.6922   0.01417   0.00802  -0.0242   1.0000   0.0118
  -7.000  -0.6688   0.01365   0.00741  -0.0234   1.0000   0.0128
  -6.750  -0.6456   0.01306   0.00675  -0.0226   1.0000   0.0141
  -6.500  -0.6217   0.01268   0.00638  -0.0220   1.0000   0.0164
  -6.250  -0.5976   0.01239   0.00603  -0.0213   1.0000   0.0186
  -6.000  -0.5736   0.01207   0.00567  -0.0206   1.0000   0.0203
  -5.750  -0.5500   0.01170   0.00529  -0.0198   1.0000   0.0233
  -5.500  -0.5259   0.01148   0.00505  -0.0191   1.0000   0.0262
  -5.250  -0.5018   0.01128   0.00481  -0.0184   1.0000   0.0283
  -5.000  -0.4699   0.01102   0.00448  -0.0194   0.9980   0.0300
  -4.750  -0.4362   0.01057   0.00402  -0.0209   0.9953   0.0336
  -4.500  -0.4028   0.01029   0.00371  -0.0222   0.9922   0.0364
  -4.250  -0.3690   0.01005   0.00343  -0.0236   0.9887   0.0387
  -4.000  -0.3344   0.00978   0.00311  -0.0251   0.9859   0.0407
  -3.750  -0.3025   0.00949   0.00281  -0.0260   0.9812   0.0439
  -3.500  -0.2694   0.00924   0.00257  -0.0272   0.9767   0.0481
  -3.250  -0.2382   0.00900   0.00234  -0.0280   0.9705   0.0572
  -3.000  -0.2060   0.00869   0.00214  -0.0290   0.9645   0.0831
  -2.750  -0.1762   0.00838   0.00196  -0.0295   0.9563   0.1155
  -2.500  -0.1455   0.00811   0.00180  -0.0301   0.9482   0.1497
  -2.250  -0.1163   0.00785   0.00166  -0.0304   0.9377   0.1874
  -2.000  -0.0880   0.00758   0.00154  -0.0305   0.9258   0.2325
  -1.500  -0.0337   0.00704   0.00133  -0.0302   0.8973   0.3421
  -1.250  -0.0073   0.00680   0.00124  -0.0299   0.8806   0.4009
  -1.000   0.0190   0.00660   0.00117  -0.0294   0.8622   0.4562
  -0.750   0.0444   0.00632   0.00112  -0.0289   0.8417   0.5394
  -0.500   0.0682   0.00593   0.00110  -0.0279   0.8194   0.6608
  -0.250   0.0916   0.00567   0.00110  -0.0267   0.7946   0.7549
   0.000   0.1158   0.00557   0.00111  -0.0256   0.7684   0.8121
   0.250   0.1399   0.00554   0.00114  -0.0244   0.7419   0.8627
   0.500   0.1650   0.00557   0.00117  -0.0234   0.7151   0.9066
   0.750   0.1944   0.00567   0.00121  -0.0234   0.6858   0.9400
   1.000   0.2267   0.00583   0.00124  -0.0242   0.6506   0.9632
   1.250   0.2603   0.00608   0.00127  -0.0254   0.5980   0.9782
   1.500   0.2938   0.00637   0.00132  -0.0268   0.5416   0.9889
   1.750   0.3289   0.00669   0.00139  -0.0285   0.4795   0.9976
   2.000   0.3572   0.00699   0.00146  -0.0288   0.4264   1.0000
   2.250   0.3819   0.00728   0.00155  -0.0282   0.3776   1.0000
   2.500   0.4067   0.00755   0.00166  -0.0277   0.3358   1.0000
   2.750   0.4312   0.00791   0.00180  -0.0272   0.2833   1.0000
   3.000   0.4554   0.00834   0.00197  -0.0266   0.2231   1.0000
   3.250   0.4801   0.00873   0.00217  -0.0262   0.1758   1.0000
   3.500   0.5049   0.00912   0.00239  -0.0257   0.1338   1.0000
   3.750   0.5298   0.00953   0.00263  -0.0253   0.0964   1.0000
   4.000   0.5549   0.00992   0.00289  -0.0248   0.0670   1.0000
   4.250   0.5803   0.01028   0.00317  -0.0244   0.0491   1.0000
   4.500   0.6062   0.01057   0.00345  -0.0241   0.0427   1.0000
   4.750   0.6321   0.01086   0.00374  -0.0237   0.0396   1.0000
   5.000   0.6578   0.01119   0.00409  -0.0233   0.0371   1.0000
   5.250   0.6833   0.01156   0.00451  -0.0229   0.0346   1.0000
   5.500   0.7094   0.01182   0.00481  -0.0226   0.0334   1.0000
   5.750   0.7352   0.01212   0.00515  -0.0223   0.0316   1.0000
   6.000   0.7609   0.01244   0.00551  -0.0220   0.0294   1.0000
   6.250   0.7860   0.01286   0.00595  -0.0216   0.0269   1.0000
   6.500   0.8109   0.01332   0.00647  -0.0211   0.0247   1.0000
   6.750   0.8370   0.01354   0.00674  -0.0209   0.0228   1.0000
   7.000   0.8627   0.01384   0.00709  -0.0206   0.0200   1.0000
   7.250   0.8876   0.01427   0.00750  -0.0202   0.0170   1.0000
   7.500   0.9123   0.01472   0.00803  -0.0198   0.0152   1.0000
   7.750   0.9371   0.01514   0.00847  -0.0194   0.0132   1.0000
   8.000   0.9609   0.01575   0.00908  -0.0188   0.0113   1.0000
   8.250   0.9841   0.01642   0.00985  -0.0182   0.0105   1.0000
   8.500   1.0073   0.01708   0.01061  -0.0176   0.0097   1.0000
   8.750   1.0302   0.01776   0.01138  -0.0170   0.0090   1.0000
   9.000   1.0529   0.01845   0.01214  -0.0163   0.0084   1.0000
   9.250   1.0737   0.01942   0.01320  -0.0155   0.0076   1.0000
   9.500   1.0947   0.02033   0.01427  -0.0147   0.0072   1.0000
   9.750   1.1156   0.02122   0.01530  -0.0138   0.0068   1.0000
  10.000   1.1355   0.02222   0.01645  -0.0129   0.0065   1.0000
  10.250   1.1547   0.02328   0.01765  -0.0120   0.0062   1.0000
  10.500   1.1732   0.02436   0.01887  -0.0110   0.0059   1.0000
  10.750   1.1909   0.02549   0.02014  -0.0099   0.0057   1.0000
  11.000   1.2071   0.02673   0.02151  -0.0088   0.0055   1.0000
  11.250   1.2207   0.02820   0.02314  -0.0074   0.0053   1.0000
  11.500   1.2291   0.03018   0.02532  -0.0056   0.0051   1.0000
  11.750   1.2348   0.03231   0.02770  -0.0036   0.0050   1.0000
  12.000   1.2394   0.03420   0.02981  -0.0015   0.0049   1.0000
  12.250   1.2386   0.03626   0.03209   0.0009   0.0049   1.0000
  12.500   1.2346   0.03870   0.03474   0.0029   0.0048   1.0000
  12.750   1.2276   0.04167   0.03793   0.0041   0.0047   1.0000
  13.000   1.2185   0.04531   0.04179   0.0040   0.0047   1.0000
  13.250   1.2061   0.05001   0.04671   0.0023   0.0046   1.0000
  13.500   1.1896   0.05623   0.05316  -0.0014   0.0046   1.0000
  13.750   1.1699   0.06417   0.06131  -0.0071   0.0046   1.0000
  14.000   1.1432   0.07450   0.07184  -0.0145   0.0047   1.0000
  14.250   1.1092   0.08709   0.08460  -0.0227   0.0048   1.0000
  14.500   1.0673   0.10158   0.09919  -0.0307   0.0049   1.0000
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