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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.72 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1408-il-1000000.txt
Download as CSV file: xf-naca1408-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6537   0.14352   0.14182   0.0249   1.0000   0.0115
 -12.250  -0.6503   0.13947   0.13777   0.0232   1.0000   0.0119
 -11.750  -1.0026   0.04092   0.03869  -0.0352   1.0000   0.0072
 -11.250  -1.0342   0.02891   0.02570  -0.0345   1.0000   0.0075
 -11.000  -1.0246   0.02620   0.02272  -0.0336   1.0000   0.0078
 -10.750  -1.0066   0.02485   0.02123  -0.0330   1.0000   0.0080
 -10.500  -0.9868   0.02372   0.01997  -0.0324   1.0000   0.0083
 -10.250  -0.9669   0.02253   0.01865  -0.0319   1.0000   0.0085
 -10.000  -0.9464   0.02136   0.01732  -0.0312   1.0000   0.0088
  -9.750  -0.9256   0.02018   0.01597  -0.0306   1.0000   0.0091
  -9.500  -0.9043   0.01909   0.01471  -0.0299   1.0000   0.0094
  -9.250  -0.8820   0.01815   0.01363  -0.0293   1.0000   0.0097
  -9.000  -0.8589   0.01741   0.01277  -0.0287   1.0000   0.0100
  -8.750  -0.8395   0.01580   0.01092  -0.0276   1.0000   0.0105
  -8.500  -0.8176   0.01483   0.00986  -0.0268   1.0000   0.0111
  -8.250  -0.7936   0.01438   0.00936  -0.0263   1.0000   0.0117
  -8.000  -0.7695   0.01399   0.00893  -0.0257   1.0000   0.0123
  -7.750  -0.7455   0.01361   0.00849  -0.0250   1.0000   0.0130
  -7.500  -0.7214   0.01326   0.00809  -0.0243   1.0000   0.0135
  -7.250  -0.7001   0.01227   0.00698  -0.0232   1.0000   0.0145
  -7.000  -0.6766   0.01185   0.00655  -0.0225   1.0000   0.0155
  -6.750  -0.6526   0.01159   0.00627  -0.0217   1.0000   0.0164
  -6.500  -0.6288   0.01132   0.00597  -0.0209   1.0000   0.0175
  -6.250  -0.6047   0.01116   0.00578  -0.0202   1.0000   0.0182
  -6.000  -0.5826   0.01048   0.00506  -0.0192   1.0000   0.0203
  -5.750  -0.5587   0.01030   0.00489  -0.0184   1.0000   0.0218
  -5.500  -0.5350   0.01011   0.00468  -0.0176   1.0000   0.0233
  -5.250  -0.5111   0.01000   0.00455  -0.0168   1.0000   0.0243
  -5.000  -0.4811   0.00936   0.00386  -0.0175   0.9991   0.0272
  -4.750  -0.4464   0.00912   0.00362  -0.0191   0.9974   0.0296
  -4.500  -0.4114   0.00889   0.00337  -0.0207   0.9957   0.0315
  -4.250  -0.3758   0.00874   0.00321  -0.0224   0.9943   0.0326
  -4.000  -0.3430   0.00825   0.00267  -0.0235   0.9917   0.0368
  -3.750  -0.3090   0.00800   0.00243  -0.0249   0.9891   0.0398
  -3.500  -0.2739   0.00781   0.00222  -0.0265   0.9868   0.0423
  -3.250  -0.2383   0.00752   0.00196  -0.0282   0.9849   0.0503
  -3.000  -0.2050   0.00713   0.00175  -0.0295   0.9818   0.0874
  -2.750  -0.1747   0.00675   0.00158  -0.0301   0.9760   0.1378
  -2.500  -0.1429   0.00642   0.00143  -0.0311   0.9711   0.1901
  -2.250  -0.1149   0.00611   0.00132  -0.0312   0.9627   0.2433
  -2.000  -0.0864   0.00580   0.00121  -0.0313   0.9543   0.3059
  -1.750  -0.0599   0.00552   0.00112  -0.0310   0.9431   0.3676
  -1.500  -0.0341   0.00520   0.00104  -0.0305   0.9304   0.4461
  -1.250  -0.0084   0.00492   0.00097  -0.0300   0.9160   0.5213
  -1.000   0.0172   0.00470   0.00092  -0.0294   0.8996   0.5891
  -0.750   0.0426   0.00447   0.00088  -0.0287   0.8814   0.6636
  -0.500   0.0669   0.00419   0.00087  -0.0278   0.8612   0.7582
  -0.250   0.0912   0.00404   0.00087  -0.0267   0.8402   0.8254
   0.000   0.1147   0.00394   0.00090  -0.0253   0.8170   0.8871
   0.250   0.1386   0.00395   0.00092  -0.0240   0.7919   0.9321
   0.500   0.1664   0.00404   0.00094  -0.0237   0.7628   0.9582
   0.750   0.1987   0.00417   0.00096  -0.0245   0.7305   0.9751
   1.000   0.2329   0.00433   0.00098  -0.0258   0.6947   0.9863
   1.250   0.2680   0.00460   0.00101  -0.0274   0.6342   0.9935
   1.500   0.3052   0.00488   0.00105  -0.0295   0.5749   0.9978
   2.000   0.3626   0.00525   0.00114  -0.0300   0.4987   1.0000
   2.250   0.3881   0.00544   0.00120  -0.0296   0.4624   1.0000
   2.500   0.4131   0.00571   0.00128  -0.0290   0.4141   1.0000
   2.750   0.4378   0.00602   0.00138  -0.0285   0.3592   1.0000
   3.000   0.4623   0.00638   0.00151  -0.0279   0.3001   1.0000
   3.250   0.4865   0.00680   0.00167  -0.0273   0.2380   1.0000
   3.500   0.5105   0.00729   0.00188  -0.0268   0.1720   1.0000
   3.750   0.5345   0.00783   0.00214  -0.0262   0.1065   1.0000
   4.000   0.5585   0.00841   0.00244  -0.0256   0.0513   1.0000
   4.250   0.5842   0.00874   0.00270  -0.0251   0.0413   1.0000
   4.500   0.6105   0.00896   0.00294  -0.0248   0.0388   1.0000
   4.750   0.6368   0.00919   0.00320  -0.0245   0.0365   1.0000
   5.000   0.6628   0.00950   0.00350  -0.0241   0.0337   1.0000
   5.250   0.6880   0.00998   0.00403  -0.0236   0.0304   1.0000
   5.500   0.7145   0.01019   0.00427  -0.0234   0.0296   1.0000
   5.750   0.7408   0.01043   0.00453  -0.0231   0.0280   1.0000
   6.000   0.7670   0.01069   0.00480  -0.0228   0.0261   1.0000
   6.250   0.7918   0.01123   0.00535  -0.0224   0.0235   1.0000
   6.500   0.8170   0.01167   0.00585  -0.0219   0.0221   1.0000
   6.750   0.8435   0.01188   0.00608  -0.0217   0.0208   1.0000
   7.000   0.8698   0.01209   0.00629  -0.0215   0.0192   1.0000
   7.250   0.8938   0.01273   0.00694  -0.0210   0.0171   1.0000
   7.500   0.9192   0.01311   0.00736  -0.0206   0.0163   1.0000
   7.750   0.9448   0.01343   0.00773  -0.0203   0.0153   1.0000
   8.000   0.9703   0.01376   0.00808  -0.0199   0.0143   1.0000
   8.250   0.9950   0.01421   0.00854  -0.0195   0.0133   1.0000
   8.500   1.0166   0.01519   0.00961  -0.0187   0.0123   1.0000
   8.750   1.0416   0.01555   0.01002  -0.0183   0.0117   1.0000
   9.000   1.0658   0.01604   0.01058  -0.0178   0.0111   1.0000
   9.250   1.0897   0.01655   0.01114  -0.0173   0.0105   1.0000
   9.500   1.1132   0.01710   0.01173  -0.0168   0.0100   1.0000
   9.750   1.1329   0.01823   0.01295  -0.0158   0.0094   1.0000
  10.000   1.1505   0.01972   0.01462  -0.0145   0.0090   1.0000
  10.250   1.1722   0.02046   0.01547  -0.0138   0.0088   1.0000
  10.500   1.1927   0.02136   0.01650  -0.0129   0.0085   1.0000
  10.750   1.2120   0.02238   0.01765  -0.0119   0.0082   1.0000
  11.000   1.2306   0.02343   0.01883  -0.0109   0.0079   1.0000
  11.250   1.2486   0.02448   0.02000  -0.0099   0.0077   1.0000
  11.500   1.2668   0.02539   0.02100  -0.0089   0.0074   1.0000
  11.750   1.2844   0.02629   0.02198  -0.0079   0.0072   1.0000
  12.000   1.2986   0.02752   0.02332  -0.0066   0.0069   1.0000
  12.250   1.3005   0.03006   0.02611  -0.0042   0.0066   1.0000
  12.500   1.2808   0.03419   0.03063   0.0002   0.0064   1.0000
  12.750   1.2823   0.03589   0.03248   0.0024   0.0064   1.0000
  13.000   1.2812   0.03797   0.03472   0.0040   0.0063   1.0000
  13.250   1.2749   0.04085   0.03778   0.0049   0.0063   1.0000
  13.500   1.2657   0.04453   0.04165   0.0046   0.0062   1.0000
  13.750   1.2538   0.04921   0.04651   0.0028   0.0062   1.0000
  14.000   1.2353   0.05582   0.05333  -0.0012   0.0062   1.0000
  14.250   1.2119   0.06441   0.06212  -0.0073   0.0062   1.0000
  14.500   1.1775   0.07621   0.07412  -0.0157   0.0063   1.0000
  14.750   1.0232   0.07504   0.07294  -0.0041   0.0067   1.0000
  15.000   0.9988   0.08384   0.08184  -0.0075   0.0068   1.0000
  15.250   0.9475   0.09793   0.09613  -0.0134   0.0070   1.0000
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