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

NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(3)-618 (naca653618-il)
Reynolds number: 500,000
Max Cl/Cd: 110.34 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca653618-il-500000.txt
Download as CSV file: xf-naca653618-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(3)-618                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.5409   0.08503   0.08234  -0.0897   1.0000   0.0254
 -14.750  -0.5659   0.07892   0.07621  -0.0916   1.0000   0.0252
 -14.500  -0.6006   0.06798   0.06503  -0.1010   0.9971   0.0251
 -14.250  -0.6271   0.05962   0.05641  -0.1082   0.9883   0.0250
 -14.000  -0.6454   0.05298   0.04951  -0.1137   0.9813   0.0250
 -13.750  -0.6637   0.04703   0.04318  -0.1190   0.9723   0.0252
 -13.500  -0.6690   0.04259   0.03837  -0.1241   0.9641   0.0255
 -13.250  -0.6582   0.03822   0.03380  -0.1280   0.9573   0.0260
 -13.000  -0.6291   0.03693   0.03252  -0.1312   0.9497   0.0265
 -12.750  -0.6057   0.03506   0.03052  -0.1344   0.9398   0.0269
 -12.500  -0.5918   0.03348   0.02878  -0.1355   0.9258   0.0275
 -12.250  -0.5865   0.03173   0.02679  -0.1347   0.9116   0.0278
 -12.000  -0.5826   0.03028   0.02511  -0.1331   0.8988   0.0283
 -11.500  -0.5751   0.02787   0.02224  -0.1286   0.8766   0.0292
 -11.250  -0.5728   0.02708   0.02122  -0.1256   0.8672   0.0296
 -11.000  -0.5618   0.02562   0.01956  -0.1239   0.8591   0.0302
 -10.750  -0.5348   0.02420   0.01807  -0.1245   0.8537   0.0309
 -10.500  -0.5166   0.02335   0.01716  -0.1236   0.8468   0.0313
 -10.250  -0.4982   0.02266   0.01640  -0.1227   0.8399   0.0319
 -10.000  -0.4784   0.02199   0.01563  -0.1219   0.8337   0.0325
  -9.750  -0.4602   0.02140   0.01497  -0.1209   0.8269   0.0333
  -9.500  -0.4395   0.02074   0.01418  -0.1201   0.8211   0.0340
  -9.250  -0.4187   0.02017   0.01349  -0.1194   0.8157   0.0345
  -9.000  -0.3990   0.01970   0.01292  -0.1184   0.8096   0.0349
  -8.750  -0.3702   0.01845   0.01166  -0.1188   0.8049   0.0358
  -8.500  -0.3493   0.01786   0.01105  -0.1181   0.7998   0.0366
  -8.250  -0.3303   0.01735   0.01054  -0.1170   0.7940   0.0374
  -8.000  -0.3107   0.01692   0.01006  -0.1161   0.7885   0.0383
  -7.750  -0.2904   0.01649   0.00954  -0.1152   0.7836   0.0391
  -7.500  -0.2712   0.01603   0.00907  -0.1142   0.7785   0.0399
  -7.250  -0.2510   0.01564   0.00862  -0.1133   0.7735   0.0405
  -7.000  -0.2327   0.01508   0.00800  -0.1122   0.7689   0.0414
  -6.750  -0.2150   0.01451   0.00741  -0.1110   0.7644   0.0426
  -6.500  -0.1944   0.01411   0.00701  -0.1103   0.7595   0.0439
  -6.250  -0.1721   0.01378   0.00664  -0.1097   0.7550   0.0456
  -6.000  -0.1486   0.01348   0.00626  -0.1093   0.7508   0.0471
  -5.750  -0.1268   0.01305   0.00581  -0.1088   0.7466   0.0489
  -5.500  -0.1035   0.01269   0.00545  -0.1084   0.7424   0.0516
  -5.250  -0.0785   0.01242   0.00515  -0.1083   0.7385   0.0549
  -5.000  -0.0537   0.01208   0.00480  -0.1082   0.7349   0.0615
  -4.750  -0.0291   0.01168   0.00447  -0.1081   0.7313   0.0810
  -4.500  -0.0098   0.01048   0.00392  -0.1080   0.7273   0.2239
  -4.250   0.0113   0.00896   0.00333  -0.1087   0.7233   0.4562
  -4.000   0.0396   0.00878   0.00333  -0.1091   0.7199   0.5321
  -3.750   0.0691   0.00883   0.00335  -0.1096   0.7166   0.5601
  -3.500   0.0979   0.00887   0.00339  -0.1099   0.7135   0.5768
  -3.250   0.1266   0.00890   0.00342  -0.1102   0.7101   0.5885
  -3.000   0.1559   0.00897   0.00342  -0.1105   0.7068   0.5998
  -2.750   0.1851   0.00911   0.00353  -0.1108   0.7037   0.6152
  -2.500   0.2139   0.00932   0.00374  -0.1109   0.7007   0.6305
  -2.250   0.2420   0.00951   0.00397  -0.1109   0.6977   0.6426
  -2.000   0.2708   0.00964   0.00406  -0.1112   0.6946   0.6505
  -1.750   0.2994   0.00961   0.00402  -0.1115   0.6916   0.6538
  -1.500   0.3283   0.00961   0.00401  -0.1118   0.6887   0.6564
  -1.250   0.3576   0.00964   0.00400  -0.1123   0.6861   0.6592
  -1.000   0.3875   0.00970   0.00401  -0.1129   0.6834   0.6622
  -0.750   0.4164   0.00974   0.00402  -0.1133   0.6806   0.6651
  -0.500   0.4454   0.00976   0.00402  -0.1138   0.6777   0.6679
  -0.250   0.4741   0.00974   0.00401  -0.1142   0.6749   0.6706
   0.000   0.5029   0.00976   0.00403  -0.1145   0.6723   0.6731
   0.250   0.5321   0.00979   0.00406  -0.1150   0.6699   0.6756
   0.500   0.5617   0.00986   0.00410  -0.1156   0.6674   0.6784
   0.750   0.5910   0.00995   0.00418  -0.1161   0.6648   0.6815
   1.000   0.6193   0.00999   0.00423  -0.1164   0.6622   0.6846
   1.250   0.6480   0.01003   0.00428  -0.1168   0.6596   0.6873
   1.500   0.6765   0.01005   0.00434  -0.1172   0.6570   0.6899
   1.750   0.7053   0.01009   0.00440  -0.1176   0.6545   0.6926
   2.000   0.7345   0.01016   0.00447  -0.1181   0.6521   0.6957
   2.250   0.7645   0.01030   0.00459  -0.1187   0.6497   0.6991
   2.500   0.7925   0.01038   0.00471  -0.1190   0.6473   0.7025
   2.750   0.8203   0.01043   0.00480  -0.1193   0.6446   0.7055
   3.000   0.8480   0.01047   0.00491  -0.1195   0.6418   0.7085
   3.250   0.8764   0.01053   0.00501  -0.1198   0.6391   0.7116
   3.500   0.9053   0.01058   0.00508  -0.1202   0.6360   0.7150
   3.750   0.9352   0.01073   0.00520  -0.1209   0.6326   0.7188
   4.000   0.9610   0.01076   0.00531  -0.1207   0.6289   0.7225
   4.250   0.9875   0.01077   0.00541  -0.1206   0.6250   0.7261
   4.500   1.0151   0.01080   0.00547  -0.1208   0.6210   0.7296
   4.750   1.0442   0.01088   0.00553  -0.1212   0.6160   0.7335
   5.000   1.0669   0.01083   0.00558  -0.1203   0.6090   0.7378
   5.250   1.0930   0.01079   0.00552  -0.1201   0.6014   0.7417
   5.500   1.1148   0.01076   0.00560  -0.1190   0.5927   0.7456
   5.750   1.1380   0.01077   0.00559  -0.1182   0.5826   0.7502
   6.000   1.1590   0.01078   0.00569  -0.1170   0.5724   0.7552
   6.250   1.1804   0.01084   0.00578  -0.1159   0.5617   0.7599
   6.500   1.2005   0.01094   0.00590  -0.1145   0.5505   0.7643
   6.750   1.2193   0.01105   0.00607  -0.1130   0.5373   0.7695
   7.000   1.2363   0.01123   0.00625  -0.1111   0.5215   0.7750
   7.250   1.2462   0.01144   0.00647  -0.1078   0.5013   0.7802
   7.500   1.2504   0.01185   0.00682  -0.1036   0.4735   0.7864
   7.750   1.2469   0.01262   0.00743  -0.0982   0.4336   0.7936
   8.000   1.2353   0.01377   0.00839  -0.0919   0.3888   0.8006
   8.250   1.2221   0.01527   0.00966  -0.0859   0.3441   0.8088
   8.500   1.2103   0.01689   0.01111  -0.0805   0.3010   0.8163
   8.750   1.1996   0.01871   0.01273  -0.0758   0.2586   0.8251
   9.000   1.1893   0.02064   0.01448  -0.0714   0.2185   0.8333
   9.250   1.1818   0.02263   0.01629  -0.0678   0.1800   0.8428
   9.500   1.1741   0.02466   0.01817  -0.0643   0.1442   0.8522
   9.750   1.1668   0.02684   0.02018  -0.0611   0.1081   0.8630
  10.000   1.1601   0.02905   0.02224  -0.0581   0.0771   0.8748
  10.250   1.1566   0.03107   0.02417  -0.0555   0.0549   0.8880
  10.500   1.1576   0.03275   0.02585  -0.0532   0.0451   0.9042
  10.750   1.1600   0.03420   0.02735  -0.0509   0.0401   0.9274
  11.000   1.1653   0.03582   0.02903  -0.0497   0.0365   1.0000
  11.250   1.1770   0.03735   0.03059  -0.0493   0.0339   1.0000
  11.500   1.1840   0.03925   0.03250  -0.0486   0.0318   1.0000
  11.750   1.1928   0.04101   0.03430  -0.0480   0.0301   1.0000
  12.000   1.2021   0.04276   0.03609  -0.0475   0.0287   1.0000
  12.250   1.2100   0.04464   0.03800  -0.0469   0.0275   1.0000
  12.500   1.2117   0.04714   0.04053  -0.0461   0.0265   1.0000
  12.750   1.2210   0.04895   0.04241  -0.0457   0.0257   1.0000
  13.000   1.2294   0.05089   0.04440  -0.0453   0.0248   1.0000
  13.250   1.2372   0.05291   0.04646  -0.0450   0.0242   1.0000
  13.500   1.2439   0.05506   0.04865  -0.0446   0.0235   1.0000
  13.750   1.2486   0.05744   0.05107  -0.0442   0.0228   1.0000
  14.000   1.2492   0.06026   0.05392  -0.0437   0.0223   1.0000
  14.250   1.2587   0.06223   0.05596  -0.0436   0.0218   1.0000
  14.500   1.2677   0.06425   0.05806  -0.0435   0.0213   1.0000
  14.750   1.2755   0.06644   0.06032  -0.0435   0.0208   1.0000
  15.000   1.2832   0.06864   0.06257  -0.0434   0.0203   1.0000
  15.250   1.2908   0.07088   0.06486  -0.0435   0.0199   1.0000
  15.500   1.2979   0.07320   0.06722  -0.0435   0.0196   1.0000
  15.750   1.3051   0.07548   0.06953  -0.0436   0.0192   1.0000
  16.000   1.3124   0.07765   0.07171  -0.0434   0.0188   1.0000
  16.250   1.3215   0.07961   0.07372  -0.0432   0.0185   1.0000
  16.500   1.3291   0.08198   0.07620  -0.0434   0.0183   1.0000
  16.750   1.3371   0.08429   0.07859  -0.0436   0.0181   1.0000
  17.000   1.3450   0.08663   0.08103  -0.0439   0.0178   1.0000
  17.250   1.3523   0.08904   0.08354  -0.0442   0.0176   1.0000
  17.500   1.3593   0.09150   0.08608  -0.0445   0.0174   1.0000
  17.750   1.3661   0.09398   0.08866  -0.0449   0.0172   1.0000
  18.000   1.3724   0.09656   0.09133  -0.0454   0.0170   1.0000
  18.250   1.3780   0.09927   0.09414  -0.0460   0.0168   1.0000
  18.500   1.3825   0.10214   0.09710  -0.0467   0.0166   1.0000
  18.750   1.3858   0.10521   0.10026  -0.0476   0.0164   1.0000
  19.000   1.3890   0.10831   0.10345  -0.0486   0.0162   1.0000
<< Back to NACA 65(3)-618 (naca653618-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(3)-618 (naca653618-il)