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

NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NPL 9660 AIRFOIL (npl9660-il)
Reynolds number: 500,000
Max Cl/Cd: 66.22 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9660-il-500000-n5.txt
Download as CSV file: xf-npl9660-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9660 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -1.0738   0.05580   0.05260  -0.0274   1.0000   0.0117
 -13.750  -1.0996   0.04883   0.04534  -0.0311   1.0000   0.0117
 -13.500  -1.1159   0.04407   0.04033  -0.0322   1.0000   0.0117
 -13.250  -1.1259   0.04052   0.03654  -0.0319   1.0000   0.0117
 -13.000  -1.1310   0.03772   0.03352  -0.0307   1.0000   0.0117
 -12.750  -1.1323   0.03538   0.03098  -0.0291   1.0000   0.0117
 -12.500  -1.1299   0.03343   0.02884  -0.0273   1.0000   0.0117
 -12.250  -1.1227   0.03174   0.02698  -0.0257   1.0000   0.0118
 -12.000  -1.1113   0.03016   0.02523  -0.0245   1.0000   0.0118
 -11.750  -1.0976   0.02870   0.02360  -0.0235   1.0000   0.0119
 -11.500  -1.0821   0.02733   0.02208  -0.0226   1.0000   0.0120
 -11.250  -1.0651   0.02605   0.02064  -0.0217   1.0000   0.0120
 -11.000  -1.0468   0.02487   0.01932  -0.0209   1.0000   0.0120
 -10.750  -1.0274   0.02378   0.01810  -0.0202   1.0000   0.0120
 -10.500  -1.0070   0.02278   0.01697  -0.0196   1.0000   0.0120
 -10.250  -0.9860   0.02186   0.01593  -0.0190   1.0000   0.0120
 -10.000  -0.9644   0.02100   0.01497  -0.0185   1.0000   0.0120
  -9.750  -0.9423   0.02020   0.01409  -0.0179   1.0000   0.0120
  -9.500  -0.9201   0.01946   0.01326  -0.0173   1.0000   0.0121
  -9.250  -0.8979   0.01878   0.01249  -0.0167   1.0000   0.0121
  -9.000  -0.8760   0.01815   0.01179  -0.0160   1.0000   0.0121
  -8.750  -0.8499   0.01752   0.01109  -0.0161   0.9950   0.0121
  -8.500  -0.8199   0.01691   0.01040  -0.0169   0.9904   0.0122
  -8.250  -0.7898   0.01633   0.00976  -0.0178   0.9874   0.0122
  -8.000  -0.7594   0.01580   0.00917  -0.0187   0.9848   0.0123
  -7.750  -0.7292   0.01530   0.00861  -0.0195   0.9823   0.0124
  -7.500  -0.7021   0.01488   0.00814  -0.0195   0.9787   0.0124
  -7.250  -0.6753   0.01450   0.00771  -0.0195   0.9741   0.0125
  -7.000  -0.6500   0.01418   0.00735  -0.0191   0.9689   0.0126
  -6.750  -0.6260   0.01388   0.00700  -0.0184   0.9635   0.0127
  -6.500  -0.6019   0.01359   0.00668  -0.0176   0.9593   0.0128
  -6.250  -0.5772   0.01326   0.00634  -0.0171   0.9542   0.0130
  -6.000  -0.5531   0.01298   0.00603  -0.0163   0.9493   0.0133
  -5.750  -0.5276   0.01266   0.00570  -0.0159   0.9441   0.0138
  -5.500  -0.5027   0.01235   0.00539  -0.0153   0.9384   0.0145
  -5.250  -0.4777   0.01206   0.00509  -0.0147   0.9331   0.0160
  -5.000  -0.4519   0.01179   0.00480  -0.0142   0.9270   0.0181
  -4.750  -0.4273   0.01153   0.00454  -0.0134   0.9217   0.0200
  -4.500  -0.4010   0.01129   0.00432  -0.0131   0.9157   0.0228
  -4.250  -0.3749   0.01107   0.00410  -0.0127   0.9094   0.0252
  -4.000  -0.3496   0.01087   0.00388  -0.0120   0.9040   0.0271
  -3.750  -0.3221   0.01068   0.00368  -0.0119   0.8961   0.0287
  -3.500  -0.2961   0.01050   0.00347  -0.0114   0.8881   0.0299
  -3.250  -0.2691   0.01032   0.00328  -0.0111   0.8782   0.0313
  -3.000  -0.2428   0.01016   0.00309  -0.0107   0.8668   0.0327
  -2.750  -0.2163   0.01001   0.00290  -0.0102   0.8519   0.0339
  -2.500  -0.1898   0.00986   0.00272  -0.0098   0.8356   0.0356
  -2.250  -0.1631   0.00974   0.00255  -0.0094   0.8170   0.0378
  -2.000  -0.1360   0.00964   0.00241  -0.0091   0.7956   0.0411
  -1.750  -0.1086   0.00956   0.00227  -0.0089   0.7711   0.0450
  -1.500  -0.0812   0.00950   0.00215  -0.0088   0.7468   0.0496
  -1.250  -0.0535   0.00947   0.00204  -0.0087   0.7244   0.0555
  -1.000  -0.0256   0.00941   0.00194  -0.0087   0.7024   0.0660
  -0.750   0.0024   0.00933   0.00186  -0.0087   0.6823   0.0853
  -0.500   0.0260   0.00786   0.00156  -0.0090   0.6614   0.4400
  -0.250   0.0534   0.00760   0.00151  -0.0091   0.6380   0.5216
   0.000   0.0808   0.00739   0.00148  -0.0091   0.6153   0.5936
   0.250   0.1082   0.00726   0.00148  -0.0091   0.5924   0.6548
   0.500   0.1352   0.00715   0.00150  -0.0089   0.5686   0.7128
   0.750   0.1615   0.00710   0.00156  -0.0084   0.5418   0.7662
   1.000   0.1866   0.00714   0.00168  -0.0076   0.5150   0.8194
   1.250   0.2099   0.00726   0.00186  -0.0062   0.4933   0.8623
   1.500   0.2353   0.00742   0.00198  -0.0054   0.4742   0.8855
   1.750   0.2613   0.00757   0.00208  -0.0049   0.4571   0.8944
   2.000   0.2891   0.00772   0.00215  -0.0048   0.4390   0.9023
   2.250   0.3155   0.00787   0.00224  -0.0044   0.4218   0.9078
   2.500   0.3420   0.00803   0.00234  -0.0040   0.4031   0.9138
   2.750   0.3697   0.00821   0.00243  -0.0040   0.3817   0.9201
   3.000   0.3951   0.00840   0.00256  -0.0034   0.3596   0.9245
   3.250   0.4211   0.00862   0.00268  -0.0030   0.3370   0.9296
   3.500   0.4481   0.00885   0.00282  -0.0029   0.3113   0.9349
   3.750   0.4733   0.00911   0.00297  -0.0024   0.2827   0.9394
   4.000   0.4990   0.00941   0.00313  -0.0021   0.2527   0.9447
   4.250   0.5252   0.00969   0.00331  -0.0018   0.2307   0.9493
   4.500   0.5502   0.00993   0.00346  -0.0013   0.2070   0.9537
   4.750   0.5759   0.01018   0.00363  -0.0010   0.1879   0.9583
   5.000   0.6010   0.01039   0.00378  -0.0005   0.1721   0.9625
   5.250   0.6260   0.01058   0.00392   0.0000   0.1592   0.9678
   5.500   0.6517   0.01080   0.00409   0.0003   0.1449   0.9726
   5.750   0.6790   0.01108   0.00428   0.0002   0.1288   0.9761
   6.000   0.7070   0.01133   0.00449  -0.0001   0.1175   0.9792
   6.250   0.7355   0.01159   0.00472  -0.0005   0.1090   0.9825
   6.500   0.7669   0.01188   0.00499  -0.0015   0.1001   0.9849
   6.750   0.7983   0.01220   0.00528  -0.0026   0.0897   0.9874
   7.000   0.8297   0.01258   0.00558  -0.0037   0.0739   0.9903
   7.250   0.8608   0.01300   0.00596  -0.0048   0.0619   0.9943
   7.500   0.8897   0.01347   0.00638  -0.0055   0.0496   1.0000
   7.750   0.9118   0.01395   0.00680  -0.0048   0.0396   1.0000
   8.000   0.9349   0.01442   0.00725  -0.0043   0.0328   1.0000
   8.250   0.9585   0.01489   0.00772  -0.0039   0.0286   1.0000
   8.500   0.9822   0.01538   0.00821  -0.0035   0.0258   1.0000
   8.750   1.0065   0.01583   0.00868  -0.0032   0.0240   1.0000
   9.000   1.0304   0.01632   0.00921  -0.0029   0.0224   1.0000
   9.250   1.0540   0.01686   0.00977  -0.0026   0.0213   1.0000
   9.500   1.0777   0.01736   0.01032  -0.0023   0.0204   1.0000
   9.750   1.1009   0.01790   0.01092  -0.0019   0.0195   1.0000
  10.000   1.1233   0.01852   0.01157  -0.0015   0.0187   1.0000
  10.250   1.1446   0.01922   0.01232  -0.0009   0.0179   1.0000
  10.500   1.1664   0.01983   0.01301  -0.0004   0.0174   1.0000
  10.750   1.1872   0.02050   0.01375   0.0001   0.0168   1.0000
  11.000   1.2072   0.02122   0.01453   0.0008   0.0163   1.0000
  11.250   1.2261   0.02199   0.01537   0.0016   0.0158   1.0000
  11.500   1.2433   0.02285   0.01629   0.0025   0.0154   1.0000
  11.750   1.2574   0.02389   0.01739   0.0038   0.0150   1.0000
  12.000   1.2687   0.02490   0.01848   0.0054   0.0147   1.0000
  12.250   1.2810   0.02588   0.01956   0.0069   0.0145   1.0000
  12.500   1.2920   0.02699   0.02077   0.0082   0.0142   1.0000
  12.750   1.3017   0.02822   0.02210   0.0095   0.0140   1.0000
  13.000   1.3101   0.02961   0.02359   0.0107   0.0138   1.0000
  13.250   1.3172   0.03116   0.02525   0.0118   0.0136   1.0000
  13.500   1.3232   0.03290   0.02710   0.0126   0.0134   1.0000
  13.750   1.3280   0.03486   0.02917   0.0132   0.0132   1.0000
  14.000   1.3315   0.03707   0.03149   0.0134   0.0131   1.0000
  14.250   1.3338   0.03957   0.03410   0.0133   0.0129   1.0000
  14.500   1.3347   0.04240   0.03704   0.0128   0.0128   1.0000
  14.750   1.3340   0.04557   0.04033   0.0120   0.0127   1.0000
  15.000   1.3317   0.04910   0.04399   0.0108   0.0126   1.0000
  15.250   1.3275   0.05303   0.04803   0.0093   0.0125   1.0000
  15.500   1.3216   0.05733   0.05247   0.0075   0.0125   1.0000
  15.750   1.3136   0.06203   0.05729   0.0054   0.0124   1.0000
  16.000   1.3039   0.06709   0.06248   0.0031   0.0123   1.0000
  16.250   1.2927   0.07250   0.06802   0.0005   0.0123   1.0000
  16.500   1.2803   0.07822   0.07386  -0.0022   0.0122   1.0000
  16.750   1.2672   0.08421   0.07997  -0.0051   0.0122   1.0000
  17.000   1.2533   0.09044   0.08631  -0.0081   0.0122   1.0000
  17.250   1.2393   0.09680   0.09278  -0.0113   0.0121   1.0000
<< Back to NPL 9660 AIRFOIL (npl9660-il)

Polar data table (+)

Polar graphs


<< Back to NPL 9660 AIRFOIL (npl9660-il)