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

NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(3)-418 (naca663418-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.56 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca663418-il-1000000-n5.txt
Download as CSV file: xf-naca663418-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(3)-418                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.8717   0.08368   0.08065  -0.1009   0.9576   0.0130
 -19.500  -0.8852   0.07549   0.07225  -0.1082   0.9530   0.0129
 -19.250  -0.8854   0.06916   0.06575  -0.1150   0.9474   0.0130
 -19.000  -0.8780   0.06431   0.06075  -0.1208   0.9389   0.0131
 -18.750  -0.8744   0.05978   0.05605  -0.1254   0.9276   0.0132
 -18.500  -0.8734   0.05611   0.05220  -0.1281   0.9140   0.0133
 -18.250  -0.8764   0.05274   0.04867  -0.1294   0.9011   0.0134
 -18.000  -0.8763   0.05004   0.04582  -0.1302   0.8907   0.0135
 -17.750  -0.8787   0.04730   0.04292  -0.1306   0.8812   0.0135
 -17.500  -0.8773   0.04498   0.04049  -0.1308   0.8734   0.0137
 -17.000  -0.8735   0.04084   0.03610  -0.1304   0.8586   0.0138
 -16.750  -0.8691   0.03910   0.03425  -0.1301   0.8524   0.0138
 -16.250  -0.8592   0.03583   0.03076  -0.1290   0.8418   0.0141
 -16.000  -0.8515   0.03447   0.02931  -0.1285   0.8368   0.0142
 -15.750  -0.8458   0.03304   0.02777  -0.1276   0.8318   0.0142
 -15.500  -0.8350   0.03199   0.02664  -0.1270   0.8277   0.0143
 -15.250  -0.8245   0.03092   0.02548  -0.1264   0.8238   0.0144
 -15.000  -0.8154   0.02977   0.02424  -0.1255   0.8196   0.0145
 -14.750  -0.8037   0.02887   0.02326  -0.1248   0.8155   0.0146
 -14.500  -0.7969   0.02765   0.02195  -0.1235   0.8115   0.0147
 -14.250  -0.7875   0.02658   0.02083  -0.1225   0.8084   0.0150
 -14.000  -0.7761   0.02567   0.01985  -0.1215   0.8050   0.0150
 -13.750  -0.7644   0.02483   0.01896  -0.1205   0.8014   0.0152
 -13.500  -0.7519   0.02404   0.01812  -0.1195   0.7979   0.0154
 -13.000  -0.7243   0.02263   0.01660  -0.1175   0.7920   0.0156
 -12.750  -0.7096   0.02198   0.01590  -0.1166   0.7891   0.0158
 -12.500  -0.6938   0.02139   0.01527  -0.1157   0.7862   0.0159
 -12.250  -0.6790   0.02077   0.01460  -0.1147   0.7831   0.0161
 -12.000  -0.6640   0.02019   0.01396  -0.1136   0.7800   0.0162
 -11.750  -0.6476   0.01968   0.01339  -0.1127   0.7772   0.0165
 -11.500  -0.6314   0.01912   0.01280  -0.1117   0.7748   0.0167
 -11.250  -0.6148   0.01861   0.01225  -0.1108   0.7722   0.0170
 -11.000  -0.5973   0.01815   0.01175  -0.1099   0.7697   0.0172
 -10.750  -0.5799   0.01770   0.01125  -0.1089   0.7671   0.0174
 -10.500  -0.5626   0.01726   0.01077  -0.1080   0.7647   0.0176
 -10.250  -0.5461   0.01679   0.01025  -0.1068   0.7623   0.0178
 -10.000  -0.5298   0.01630   0.00972  -0.1056   0.7602   0.0180
  -9.750  -0.5126   0.01584   0.00925  -0.1046   0.7584   0.0183
  -9.500  -0.4944   0.01544   0.00885  -0.1036   0.7564   0.0187
  -9.250  -0.4757   0.01508   0.00846  -0.1027   0.7544   0.0191
  -9.000  -0.4577   0.01469   0.00805  -0.1016   0.7524   0.0193
  -8.750  -0.4387   0.01436   0.00770  -0.1007   0.7504   0.0197
  -8.500  -0.4198   0.01403   0.00734  -0.0997   0.7484   0.0201
  -8.250  -0.4009   0.01372   0.00700  -0.0987   0.7465   0.0205
  -8.000  -0.3819   0.01343   0.00667  -0.0976   0.7446   0.0209
  -7.750  -0.3629   0.01311   0.00634  -0.0966   0.7432   0.0213
  -7.500  -0.3443   0.01278   0.00602  -0.0955   0.7418   0.0221
  -7.250  -0.3250   0.01249   0.00572  -0.0945   0.7403   0.0226
  -7.000  -0.3058   0.01221   0.00544  -0.0934   0.7387   0.0233
  -6.750  -0.2863   0.01196   0.00518  -0.0923   0.7371   0.0240
  -6.500  -0.2671   0.01172   0.00492  -0.0912   0.7356   0.0249
  -6.250  -0.2493   0.01147   0.00467  -0.0897   0.7340   0.0260
  -6.000  -0.2328   0.01126   0.00446  -0.0880   0.7325   0.0271
  -5.750  -0.2165   0.01110   0.00429  -0.0862   0.7309   0.0285
  -5.500  -0.1964   0.01096   0.00412  -0.0851   0.7294   0.0296
  -5.000  -0.1536   0.01060   0.00378  -0.0834   0.7267   0.0340
  -4.750  -0.1311   0.01043   0.00362  -0.0827   0.7257   0.0372
  -4.500  -0.1084   0.01025   0.00347  -0.0821   0.7246   0.0424
  -4.250  -0.0859   0.01004   0.00333  -0.0815   0.7235   0.0527
  -4.000  -0.0641   0.00980   0.00317  -0.0807   0.7224   0.0725
  -3.750  -0.0431   0.00949   0.00300  -0.0799   0.7212   0.1043
  -3.500  -0.0236   0.00909   0.00280  -0.0788   0.7200   0.1596
  -3.250  -0.0041   0.00865   0.00260  -0.0778   0.7189   0.2250
  -3.000   0.0161   0.00819   0.00240  -0.0769   0.7177   0.2964
  -2.750   0.0344   0.00753   0.00214  -0.0759   0.7166   0.4043
  -2.500   0.0504   0.00652   0.00175  -0.0746   0.7155   0.5688
  -2.250   0.0760   0.00630   0.00180  -0.0745   0.7145   0.6581
  -2.000   0.1050   0.00633   0.00183  -0.0749   0.7135   0.6738
  -1.750   0.1342   0.00638   0.00188  -0.0754   0.7126   0.6842
  -1.500   0.1634   0.00643   0.00193  -0.0759   0.7116   0.6930
  -1.250   0.1927   0.00647   0.00198  -0.0764   0.7109   0.6991
  -1.000   0.2221   0.00651   0.00200  -0.0770   0.7102   0.7030
  -0.750   0.2515   0.00654   0.00202  -0.0775   0.7094   0.7057
  -0.500   0.2806   0.00653   0.00202  -0.0780   0.7084   0.7076
  -0.250   0.3099   0.00653   0.00203  -0.0786   0.7076   0.7085
   0.000   0.3392   0.00654   0.00204  -0.0792   0.7067   0.7093
   0.250   0.3685   0.00655   0.00206  -0.0797   0.7059   0.7101
   0.500   0.3977   0.00657   0.00208  -0.0803   0.7050   0.7110
   0.750   0.4269   0.00658   0.00211  -0.0808   0.7039   0.7118
   1.000   0.4557   0.00659   0.00212  -0.0813   0.7021   0.7127
   1.250   0.4844   0.00660   0.00212  -0.0817   0.6994   0.7135
   1.500   0.5131   0.00662   0.00212  -0.0821   0.6964   0.7144
   1.750   0.5418   0.00665   0.00216  -0.0826   0.6942   0.7153
   2.000   0.5700   0.00665   0.00219  -0.0829   0.6919   0.7162
   2.250   0.5981   0.00666   0.00222  -0.0832   0.6887   0.7173
   2.500   0.6259   0.00667   0.00224  -0.0834   0.6850   0.7183
   2.750   0.6537   0.00669   0.00226  -0.0837   0.6812   0.7194
   3.000   0.6810   0.00672   0.00230  -0.0838   0.6766   0.7203
   3.250   0.7077   0.00672   0.00233  -0.0838   0.6695   0.7211
   3.500   0.7336   0.00677   0.00235  -0.0836   0.6630   0.7219
   3.750   0.7601   0.00679   0.00241  -0.0836   0.6548   0.7227
   4.000   0.7836   0.00684   0.00245  -0.0830   0.6405   0.7240
   4.250   0.7945   0.00708   0.00253  -0.0797   0.5923   0.7254
   4.500   0.7791   0.00777   0.00291  -0.0711   0.5273   0.7271
   4.750   0.7605   0.00868   0.00354  -0.0622   0.4666   0.7290
   5.000   0.7479   0.00967   0.00428  -0.0551   0.4091   0.7309
   5.250   0.7394   0.01072   0.00507  -0.0490   0.3548   0.7327
   5.500   0.7377   0.01167   0.00581  -0.0444   0.3079   0.7344
   5.750   0.7415   0.01252   0.00649  -0.0409   0.2708   0.7360
   6.000   0.7410   0.01360   0.00732  -0.0369   0.2210   0.7376
   6.250   0.7452   0.01455   0.00808  -0.0337   0.1790   0.7390
   6.500   0.7489   0.01559   0.00889  -0.0305   0.1342   0.7404
   6.750   0.7585   0.01638   0.00957  -0.0282   0.1046   0.7422
   7.000   0.7683   0.01721   0.01027  -0.0261   0.0780   0.7440
   7.250   0.7820   0.01787   0.01086  -0.0245   0.0607   0.7459
   7.500   0.7958   0.01855   0.01147  -0.0230   0.0454   0.7477
   7.750   0.8109   0.01918   0.01207  -0.0217   0.0367   0.7497
   8.000   0.8279   0.01973   0.01260  -0.0207   0.0322   0.7517
   8.250   0.8454   0.02027   0.01314  -0.0197   0.0288   0.7535
   8.500   0.8621   0.02086   0.01372  -0.0187   0.0258   0.7552
   8.750   0.8797   0.02141   0.01428  -0.0179   0.0241   0.7568
   9.000   0.8966   0.02201   0.01487  -0.0170   0.0222   0.7585
   9.250   0.9143   0.02256   0.01545  -0.0161   0.0206   0.7607
   9.500   0.9309   0.02317   0.01608  -0.0152   0.0188   0.7629
   9.750   0.9476   0.02380   0.01673  -0.0143   0.0177   0.7651
  10.000   0.9645   0.02443   0.01737  -0.0135   0.0163   0.7673
  10.250   0.9812   0.02508   0.01804  -0.0127   0.0156   0.7697
  10.500   0.9974   0.02577   0.01875  -0.0118   0.0146   0.7719
  10.750   1.0137   0.02648   0.01948  -0.0110   0.0140   0.7741
  11.250   1.0447   0.02799   0.02104  -0.0093   0.0124   0.7788
  11.500   1.0603   0.02875   0.02184  -0.0085   0.0121   0.7815
  11.750   1.0751   0.02958   0.02271  -0.0077   0.0118   0.7844
  12.000   1.0905   0.03039   0.02356  -0.0069   0.0114   0.7872
  12.250   1.1053   0.03125   0.02446  -0.0061   0.0113   0.7900
  12.500   1.1197   0.03216   0.02540  -0.0054   0.0108   0.7926
  12.750   1.1334   0.03313   0.02640  -0.0046   0.0106   0.7954
  13.000   1.1466   0.03413   0.02745  -0.0037   0.0103   0.7986
  13.250   1.1598   0.03514   0.02851  -0.0029   0.0101   0.8019
  13.500   1.1721   0.03626   0.02968  -0.0021   0.0100   0.8053
  13.750   1.1835   0.03747   0.03093  -0.0013   0.0098   0.8087
  14.250   1.2067   0.03990   0.03349   0.0002   0.0097   0.8158
  14.500   1.2187   0.04110   0.03476   0.0008   0.0095   0.8197
  14.750   1.2295   0.04242   0.03615   0.0015   0.0094   0.8240
  15.000   1.2406   0.04376   0.03755   0.0021   0.0093   0.8277
  15.250   1.2495   0.04529   0.03915   0.0028   0.0093   0.8316
  15.500   1.2592   0.04677   0.04071   0.0034   0.0092   0.8360
  15.750   1.2678   0.04840   0.04242   0.0040   0.0090   0.8405
  16.000   1.2767   0.05004   0.04413   0.0044   0.0090   0.8448
  16.250   1.2841   0.05182   0.04599   0.0049   0.0088   0.8493
  16.500   1.2906   0.05372   0.04797   0.0054   0.0088   0.8545
  16.750   1.2975   0.05563   0.04997   0.0057   0.0088   0.8598
  17.000   1.3039   0.05763   0.05205   0.0060   0.0087   0.8652
  17.250   1.3092   0.05976   0.05428   0.0063   0.0086   0.8718
  17.500   1.3137   0.06203   0.05665   0.0065   0.0086   0.8786
  17.750   1.3165   0.06450   0.05923   0.0067   0.0085   0.8863
  18.000   1.3206   0.06688   0.06169   0.0067   0.0084   0.8953
  18.250   1.3240   0.06931   0.06423   0.0067   0.0083   0.9063
  18.500   1.3242   0.07221   0.06724   0.0066   0.0082   0.9177
  18.750   1.3251   0.07506   0.07021   0.0064   0.0082   0.9323
  19.000   1.3270   0.07823   0.07352   0.0054   0.0081   0.9551
  19.250   1.3277   0.08201   0.07741   0.0037   0.0080   1.0000
<< Back to NACA 66(3)-418 (naca663418-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(3)-418 (naca663418-il)