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

NACA 16-021 (naca16021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-021 (naca16021-il)
Reynolds number: 1,000,000
Max Cl/Cd: 31.61 at α=12.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16021-il-1000000-n5.txt
Download as CSV file: xf-naca16021-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-021                                     
  
 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  -1.1016   0.05442   0.04930  -0.1214   0.9854   0.0187
 -19.500  -1.0941   0.05238   0.04721  -0.1219   0.9850   0.0191
 -19.250  -1.0852   0.05051   0.04528  -0.1223   0.9845   0.0195
 -19.000  -1.0751   0.04878   0.04348  -0.1228   0.9840   0.0199
 -18.750  -1.0645   0.04709   0.04174  -0.1232   0.9835   0.0204
 -18.500  -1.0528   0.04555   0.04014  -0.1235   0.9830   0.0208
 -18.250  -1.0450   0.04414   0.03867  -0.1228   0.9816   0.0211
 -18.000  -1.0357   0.04284   0.03730  -0.1222   0.9801   0.0214
 -17.750  -1.0275   0.04136   0.03577  -0.1216   0.9787   0.0218
 -17.500  -1.0174   0.03999   0.03436  -0.1211   0.9775   0.0222
 -17.250  -1.0063   0.03869   0.03301  -0.1208   0.9763   0.0227
 -17.000  -0.9934   0.03752   0.03181  -0.1205   0.9751   0.0231
 -16.750  -0.9802   0.03637   0.03062  -0.1203   0.9741   0.0236
 -16.500  -0.9663   0.03532   0.02952  -0.1200   0.9731   0.0241
 -16.250  -0.9514   0.03431   0.02846  -0.1198   0.9722   0.0246
 -16.000  -0.9367   0.03331   0.02741  -0.1195   0.9713   0.0249
 -15.750  -0.9239   0.03248   0.02653  -0.1185   0.9696   0.0253
 -15.500  -0.9114   0.03161   0.02561  -0.1176   0.9676   0.0256
 -15.250  -0.8997   0.03063   0.02461  -0.1165   0.9656   0.0262
 -15.000  -0.8857   0.02978   0.02373  -0.1157   0.9640   0.0268
 -14.750  -0.8711   0.02896   0.02287  -0.1150   0.9625   0.0273
 -14.500  -0.8557   0.02817   0.02205  -0.1144   0.9611   0.0279
 -14.250  -0.8389   0.02745   0.02129  -0.1139   0.9598   0.0285
 -14.000  -0.8220   0.02675   0.02055  -0.1134   0.9585   0.0290
 -13.750  -0.8070   0.02612   0.01988  -0.1124   0.9564   0.0295
 -13.500  -0.7906   0.02553   0.01925  -0.1116   0.9543   0.0299
 -13.250  -0.7754   0.02486   0.01856  -0.1106   0.9523   0.0307
 -13.000  -0.7596   0.02421   0.01789  -0.1097   0.9505   0.0314
 -12.750  -0.7428   0.02359   0.01725  -0.1089   0.9488   0.0321
 -12.500  -0.7248   0.02302   0.01666  -0.1083   0.9471   0.0330
 -12.250  -0.7061   0.02248   0.01608  -0.1077   0.9455   0.0338
 -12.000  -0.6881   0.02199   0.01556  -0.1070   0.9436   0.0346
 -11.750  -0.6707   0.02149   0.01504  -0.1061   0.9415   0.0353
 -11.500  -0.6533   0.02099   0.01453  -0.1052   0.9395   0.0366
 -11.250  -0.6350   0.02052   0.01406  -0.1045   0.9374   0.0379
 -11.000  -0.6162   0.02006   0.01358  -0.1038   0.9354   0.0394
 -10.750  -0.5969   0.01961   0.01311  -0.1031   0.9335   0.0410
 -10.500  -0.5782   0.01913   0.01262  -0.1024   0.9316   0.0436
 -10.250  -0.5585   0.01871   0.01220  -0.1018   0.9298   0.0462
 -10.000  -0.5396   0.01832   0.01182  -0.1010   0.9278   0.0492
  -9.750  -0.5208   0.01792   0.01143  -0.1002   0.9257   0.0532
  -9.500  -0.5020   0.01751   0.01104  -0.0993   0.9234   0.0578
  -9.250  -0.4827   0.01712   0.01065  -0.0985   0.9211   0.0630
  -9.000  -0.4632   0.01671   0.01026  -0.0977   0.9190   0.0698
  -8.750  -0.4432   0.01633   0.00990  -0.0971   0.9171   0.0770
  -8.500  -0.4225   0.01597   0.00955  -0.0965   0.9153   0.0845
  -8.250  -0.4040   0.01561   0.00924  -0.0955   0.9132   0.0932
  -8.000  -0.3852   0.01526   0.00892  -0.0945   0.9108   0.1021
  -7.750  -0.3655   0.01492   0.00863  -0.0936   0.9084   0.1119
  -7.500  -0.3457   0.01458   0.00832  -0.0928   0.9061   0.1237
  -7.250  -0.3260   0.01422   0.00801  -0.0919   0.9040   0.1377
  -7.000  -0.3065   0.01386   0.00770  -0.0910   0.9020   0.1543
  -6.750  -0.2885   0.01346   0.00738  -0.0898   0.8998   0.1747
  -6.500  -0.2723   0.01307   0.00710  -0.0882   0.8973   0.1988
  -6.250  -0.2555   0.01269   0.00682  -0.0867   0.8947   0.2246
  -6.000  -0.2404   0.01225   0.00652  -0.0849   0.8921   0.2580
  -5.750  -0.2284   0.01171   0.00615  -0.0824   0.8894   0.3024
  -5.500  -0.2197   0.01107   0.00572  -0.0793   0.8866   0.3592
  -5.250  -0.2143   0.01040   0.00531  -0.0754   0.8836   0.4191
  -5.000  -0.2104   0.00981   0.00493  -0.0711   0.8804   0.4702
  -4.750  -0.2065   0.00925   0.00455  -0.0666   0.8770   0.5194
  -4.500  -0.2033   0.00870   0.00416  -0.0619   0.8736   0.5611
  -4.250  -0.1971   0.00823   0.00381  -0.0578   0.8705   0.6000
  -4.000  -0.1920   0.00787   0.00356  -0.0533   0.8675   0.6312
  -3.750  -0.1868   0.00757   0.00339  -0.0486   0.8641   0.6610
  -3.500  -0.1794   0.00733   0.00323  -0.0444   0.8606   0.6855
  -3.250  -0.1671   0.00715   0.00309  -0.0413   0.8577   0.7068
  -3.000  -0.1520   0.00699   0.00297  -0.0388   0.8551   0.7250
  -2.750  -0.1406   0.00687   0.00290  -0.0353   0.8524   0.7422
  -2.500  -0.1338   0.00680   0.00287  -0.0308   0.8488   0.7578
  -2.250  -0.1250   0.00674   0.00286  -0.0267   0.8453   0.7715
  -2.000  -0.1063   0.00671   0.00285  -0.0248   0.8427   0.7802
  -1.750  -0.0892   0.00665   0.00277  -0.0227   0.8401   0.7869
  -1.500  -0.0683   0.00662   0.00271  -0.0214   0.8376   0.7914
  -1.250  -0.0493   0.00665   0.00278  -0.0196   0.8349   0.7959
  -1.000  -0.0459   0.00664   0.00278  -0.0142   0.8309   0.8020
  -0.750  -0.0425   0.00661   0.00273  -0.0087   0.8270   0.8070
  -0.500  -0.0099   0.00661   0.00274  -0.0102   0.8250   0.8094
  -0.250   0.0209   0.00660   0.00273  -0.0113   0.8229   0.8119
   0.000   0.0006   0.00662   0.00276  -0.0002   0.8177   0.8176
   0.250  -0.0208   0.00660   0.00273   0.0113   0.8119   0.8230
   0.500   0.0100   0.00661   0.00274   0.0102   0.8094   0.8250
   0.750   0.0425   0.00661   0.00273   0.0087   0.8070   0.8270
   1.000   0.0460   0.00664   0.00278   0.0142   0.8020   0.8309
   1.250   0.0494   0.00665   0.00278   0.0196   0.7959   0.8349
   1.500   0.0684   0.00662   0.00271   0.0214   0.7914   0.8376
   1.750   0.0893   0.00665   0.00277   0.0226   0.7869   0.8401
   2.000   0.1063   0.00670   0.00285   0.0248   0.7801   0.8428
   2.250   0.1244   0.00674   0.00286   0.0268   0.7713   0.8454
   2.500   0.1339   0.00679   0.00287   0.0308   0.7579   0.8488
   2.750   0.1407   0.00687   0.00290   0.0353   0.7421   0.8524
   3.000   0.1521   0.00699   0.00297   0.0387   0.7250   0.8551
   3.250   0.1675   0.00714   0.00308   0.0412   0.7072   0.8576
   3.500   0.1800   0.00733   0.00322   0.0443   0.6861   0.8606
   3.750   0.1872   0.00757   0.00338   0.0485   0.6612   0.8641
   4.000   0.1926   0.00786   0.00356   0.0531   0.6316   0.8675
   4.250   0.1971   0.00824   0.00382   0.0578   0.5994   0.8705
   4.500   0.2027   0.00872   0.00417   0.0621   0.5593   0.8736
   4.750   0.2067   0.00925   0.00455   0.0666   0.5189   0.8770
   5.000   0.2111   0.00980   0.00492   0.0709   0.4707   0.8804
   5.250   0.2162   0.01036   0.00529   0.0750   0.4229   0.8835
   5.500   0.2200   0.01107   0.00572   0.0792   0.3580   0.8866
   5.750   0.2294   0.01169   0.00614   0.0822   0.3038   0.8894
   6.000   0.2408   0.01226   0.00652   0.0848   0.2572   0.8921
   6.250   0.2561   0.01269   0.00682   0.0866   0.2242   0.8947
   6.500   0.2729   0.01307   0.00709   0.0881   0.1980   0.8973
   6.750   0.2891   0.01346   0.00737   0.0897   0.1737   0.8998
   7.000   0.3073   0.01386   0.00769   0.0909   0.1533   0.9020
   7.250   0.3269   0.01422   0.00800   0.0917   0.1376   0.9040
   7.500   0.3466   0.01458   0.00832   0.0926   0.1235   0.9061
   7.750   0.3665   0.01492   0.00862   0.0934   0.1117   0.9083
   8.000   0.3862   0.01525   0.00891   0.0943   0.1017   0.9108
   8.250   0.4052   0.01560   0.00923   0.0952   0.0931   0.9132
   8.500   0.4238   0.01596   0.00955   0.0962   0.0844   0.9153
   8.750   0.4444   0.01632   0.00988   0.0968   0.0769   0.9171
   9.000   0.4645   0.01670   0.01025   0.0975   0.0696   0.9190
   9.250   0.4841   0.01711   0.01064   0.0982   0.0629   0.9211
   9.500   0.5034   0.01750   0.01102   0.0990   0.0576   0.9234
   9.750   0.5223   0.01791   0.01141   0.0998   0.0532   0.9257
  10.000   0.5411   0.01831   0.01180   0.1007   0.0491   0.9278
  10.250   0.5601   0.01870   0.01218   0.1015   0.0461   0.9298
  10.500   0.5798   0.01911   0.01260   0.1021   0.0435   0.9316
  10.750   0.5986   0.01960   0.01309   0.1028   0.0409   0.9335
  11.000   0.6180   0.02004   0.01356   0.1034   0.0394   0.9354
  11.250   0.6368   0.02050   0.01404   0.1041   0.0379   0.9374
  11.500   0.6551   0.02098   0.01452   0.1049   0.0365   0.9394
  11.750   0.6727   0.02148   0.01502   0.1057   0.0352   0.9415
  12.000   0.6903   0.02196   0.01554   0.1066   0.0345   0.9436
  12.250   0.7083   0.02246   0.01606   0.1073   0.0338   0.9454
  12.500   0.7270   0.02300   0.01663   0.1078   0.0329   0.9471
  12.750   0.7451   0.02357   0.01722   0.1084   0.0321   0.9488
  13.000   0.7619   0.02418   0.01786   0.1092   0.0314   0.9505
  13.250   0.7778   0.02483   0.01853   0.1101   0.0306   0.9523
  13.500   0.7932   0.02549   0.01921   0.1111   0.0298   0.9543
  13.750   0.8096   0.02608   0.01984   0.1119   0.0294   0.9565
  14.000   0.8247   0.02671   0.02052   0.1129   0.0290   0.9585
  14.250   0.8416   0.02741   0.02125   0.1134   0.0285   0.9599
  14.500   0.8584   0.02813   0.02201   0.1139   0.0279   0.9612
  14.750   0.8740   0.02891   0.02282   0.1145   0.0273   0.9625
  15.000   0.8886   0.02974   0.02368   0.1152   0.0268   0.9640
  15.250   0.9026   0.03059   0.02456   0.1160   0.0262   0.9657
  15.500   0.9142   0.03157   0.02557   0.1171   0.0256   0.9677
  15.750   0.9271   0.03242   0.02647   0.1180   0.0252   0.9697
  16.000   0.9400   0.03326   0.02736   0.1189   0.0249   0.9714
  16.250   0.9549   0.03425   0.02840   0.1191   0.0245   0.9723
  16.500   0.9697   0.03526   0.02945   0.1194   0.0241   0.9732
  16.750   0.9840   0.03629   0.03053   0.1196   0.0236   0.9742
  17.000   0.9971   0.03744   0.03173   0.1199   0.0231   0.9753
  17.250   1.0101   0.03861   0.03293   0.1202   0.0226   0.9764
  17.500   1.0211   0.03991   0.03428   0.1205   0.0222   0.9777
  17.750   1.0311   0.04128   0.03569   0.1210   0.0217   0.9790
  18.000   1.0395   0.04273   0.03719   0.1216   0.0214   0.9803
  18.250   1.0486   0.04402   0.03854   0.1223   0.0211   0.9819
  18.500   1.0573   0.04546   0.04005   0.1227   0.0208   0.9831
  18.750   1.0696   0.04695   0.04159   0.1224   0.0203   0.9836
  19.000   1.0800   0.04866   0.04336   0.1220   0.0199   0.9842
  19.250   1.0902   0.05040   0.04517   0.1216   0.0195   0.9847
<< Back to NACA 16-021 (naca16021-il)

Polar data table (+)

Polar graphs


<< Back to NACA 16-021 (naca16021-il)