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

RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)
Reynolds number: 1,000,000
Max Cl/Cd: 148.84 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r1046-il-1000000.txt
Download as CSV file: xf-r1046-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RONCZ 1046 VOYAGER CANARD AIRFOIL               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750   0.0277   0.10016   0.09647  -0.1130   0.5979   0.0139
 -11.500  -0.2947   0.03773   0.03379  -0.1426   0.6034   0.0090
 -11.250  -0.3254   0.03315   0.02906  -0.1442   0.6022   0.0091
 -11.000  -0.3485   0.03038   0.02610  -0.1415   0.6009   0.0091
 -10.750  -0.3632   0.02856   0.02412  -0.1375   0.5994   0.0091
 -10.500  -0.3576   0.02736   0.02284  -0.1357   0.5978   0.0093
 -10.250  -0.3598   0.02512   0.02032  -0.1331   0.5962   0.0093
 -10.000  -0.3430   0.02451   0.01966  -0.1321   0.5945   0.0095
  -9.750  -0.3309   0.02327   0.01825  -0.1307   0.5928   0.0096
  -9.500  -0.3151   0.02232   0.01716  -0.1295   0.5909   0.0098
  -9.250  -0.2983   0.02139   0.01607  -0.1284   0.5887   0.0100
  -9.000  -0.2823   0.02016   0.01465  -0.1271   0.5874   0.0101
  -8.750  -0.2616   0.01943   0.01382  -0.1264   0.5864   0.0103
  -8.500  -0.2414   0.01856   0.01280  -0.1255   0.5853   0.0106
  -8.250  -0.2204   0.01771   0.01182  -0.1247   0.5840   0.0107
  -8.000  -0.1978   0.01708   0.01107  -0.1241   0.5827   0.0109
  -7.750  -0.1750   0.01642   0.01029  -0.1235   0.5813   0.0111
  -7.500  -0.1506   0.01597   0.00975  -0.1231   0.5798   0.0112
  -7.250  -0.1302   0.01495   0.00859  -0.1221   0.5784   0.0115
  -7.000  -0.1073   0.01433   0.00789  -0.1215   0.5770   0.0117
  -6.750  -0.0827   0.01393   0.00744  -0.1211   0.5756   0.0121
  -6.500  -0.0578   0.01359   0.00704  -0.1207   0.5740   0.0123
  -6.250  -0.0324   0.01331   0.00670  -0.1204   0.5722   0.0127
  -6.000  -0.0068   0.01299   0.00633  -0.1201   0.5712   0.0132
  -5.750   0.0197   0.01274   0.00604  -0.1200   0.5704   0.0137
  -5.500   0.0446   0.01231   0.00557  -0.1196   0.5696   0.0144
  -5.250   0.0709   0.01205   0.00530  -0.1194   0.5686   0.0151
  -5.000   0.0976   0.01184   0.00507  -0.1193   0.5675   0.0159
  -4.750   0.1243   0.01163   0.00481  -0.1192   0.5664   0.0166
  -4.500   0.1502   0.01131   0.00448  -0.1189   0.5652   0.0178
  -4.250   0.1772   0.01114   0.00429  -0.1189   0.5640   0.0192
  -4.000   0.2038   0.01093   0.00405  -0.1187   0.5628   0.0207
  -3.750   0.2309   0.01077   0.00388  -0.1187   0.5618   0.0231
  -3.500   0.2578   0.01060   0.00371  -0.1186   0.5607   0.0266
  -3.250   0.2849   0.01047   0.00357  -0.1186   0.5595   0.0306
  -3.000   0.3120   0.01036   0.00346  -0.1186   0.5582   0.0353
  -2.750   0.3394   0.01029   0.00338  -0.1187   0.5568   0.0412
  -2.500   0.3667   0.01022   0.00333  -0.1187   0.5554   0.0514
  -2.250   0.3937   0.01004   0.00324  -0.1187   0.5548   0.0711
  -2.000   0.4205   0.00986   0.00317  -0.1187   0.5541   0.1001
  -1.750   0.4470   0.00964   0.00310  -0.1187   0.5532   0.1437
  -1.500   0.4729   0.00938   0.00306  -0.1186   0.5523   0.2123
  -1.250   0.4986   0.00911   0.00303  -0.1185   0.5513   0.2921
  -1.000   0.5243   0.00885   0.00301  -0.1184   0.5504   0.3777
  -0.750   0.5495   0.00858   0.00303  -0.1182   0.5494   0.4768
  -0.500   0.5757   0.00844   0.00305  -0.1181   0.5484   0.5437
  -0.250   0.6017   0.00831   0.00309  -0.1179   0.5474   0.6086
   0.000   0.6272   0.00818   0.00313  -0.1176   0.5465   0.6731
   0.250   0.6533   0.00810   0.00316  -0.1173   0.5454   0.7180
   0.500   0.6787   0.00802   0.00320  -0.1170   0.5444   0.7671
   0.750   0.7029   0.00793   0.00327  -0.1163   0.5432   0.8308
   1.000   0.7273   0.00789   0.00342  -0.1154   0.5420   0.9085
   1.250   0.7598   0.00805   0.00361  -0.1164   0.5406   0.9536
   1.500   0.7929   0.00821   0.00374  -0.1176   0.5395   0.9709
   1.750   0.8333   0.00830   0.00382  -0.1205   0.5390   0.9777
   2.000   0.8717   0.00839   0.00389  -0.1230   0.5383   0.9837
   2.250   0.9160   0.00847   0.00396  -0.1268   0.5374   0.9868
   2.500   0.9597   0.00855   0.00402  -0.1305   0.5364   0.9913
   2.750   1.0016   0.00862   0.00408  -0.1338   0.5354   0.9948
   3.000   1.0422   0.00868   0.00413  -0.1369   0.5344   0.9973
   3.250   1.0812   0.00875   0.00419  -0.1397   0.5334   0.9994
   3.500   1.1090   0.00882   0.00425  -0.1400   0.5324   1.0000
   3.750   1.1315   0.00889   0.00432  -0.1393   0.5314   1.0000
   4.000   1.1542   0.00896   0.00439  -0.1385   0.5304   1.0000
   4.250   1.1768   0.00904   0.00446  -0.1378   0.5293   1.0000
   4.500   1.1994   0.00913   0.00454  -0.1371   0.5282   1.0000
   4.750   1.2226   0.00924   0.00465  -0.1364   0.5271   1.0000
   5.000   1.2465   0.00940   0.00480  -0.1360   0.5258   1.0000
   5.250   1.2710   0.00962   0.00501  -0.1357   0.5242   1.0000
   5.500   1.2924   0.00968   0.00511  -0.1348   0.5235   1.0000
   5.750   1.3138   0.00974   0.00521  -0.1338   0.5225   1.0000
   6.000   1.3354   0.00981   0.00531  -0.1329   0.5214   1.0000
   6.250   1.3572   0.00987   0.00540  -0.1320   0.5200   1.0000
   6.500   1.3793   0.00994   0.00550  -0.1312   0.5185   1.0000
   6.750   1.4017   0.01001   0.00558  -0.1305   0.5170   1.0000
   7.000   1.4245   0.01007   0.00566  -0.1298   0.5156   1.0000
   7.250   1.4475   0.01016   0.00577  -0.1293   0.5142   1.0000
   7.500   1.4706   0.01025   0.00587  -0.1287   0.5129   1.0000
   7.750   1.4948   0.01038   0.00600  -0.1284   0.5108   1.0000
   8.000   1.5179   0.01053   0.00618  -0.1279   0.5086   1.0000
   8.250   1.5356   0.01056   0.00627  -0.1263   0.5066   1.0000
   8.500   1.5531   0.01057   0.00633  -0.1246   0.5038   1.0000
   8.750   1.5686   0.01058   0.00637  -0.1225   0.5006   1.0000
   9.000   1.5837   0.01064   0.00644  -0.1204   0.4977   1.0000
   9.250   1.6024   0.01080   0.00658  -0.1191   0.4942   1.0000
   9.500   1.6149   0.01090   0.00677  -0.1166   0.4914   1.0000
   9.750   1.6280   0.01101   0.00694  -0.1143   0.4868   1.0000
  10.000   1.6429   0.01119   0.00713  -0.1124   0.4827   1.0000
  10.250   1.6581   0.01144   0.00741  -0.1107   0.4788   1.0000
  10.500   1.6744   0.01166   0.00771  -0.1092   0.4745   1.0000
  10.750   1.6896   0.01195   0.00804  -0.1076   0.4702   1.0000
  11.000   1.7012   0.01237   0.00845  -0.1055   0.4658   1.0000
  11.250   1.7172   0.01271   0.00887  -0.1042   0.4603   1.0000
  11.500   1.7276   0.01324   0.00943  -0.1021   0.4539   1.0000
  11.750   1.7381   0.01385   0.01008  -0.1001   0.4472   1.0000
  12.000   1.7416   0.01480   0.01103  -0.0974   0.4378   1.0000
  12.250   1.7472   0.01578   0.01204  -0.0951   0.4276   1.0000
  12.500   1.7440   0.01732   0.01358  -0.0920   0.4146   1.0000
  12.750   1.7345   0.01941   0.01564  -0.0886   0.3995   1.0000
  13.000   1.7190   0.02208   0.01828  -0.0850   0.3833   1.0000
  13.250   1.6886   0.02601   0.02216  -0.0805   0.3629   1.0000
  13.500   1.6619   0.02992   0.02603  -0.0767   0.3446   1.0000
  13.750   1.6394   0.03368   0.02976  -0.0735   0.3294   1.0000
  14.000   1.6092   0.03824   0.03426  -0.0700   0.3097   1.0000
  14.250   1.5849   0.04246   0.03843  -0.0672   0.2928   1.0000
  14.500   1.5621   0.04666   0.04256  -0.0647   0.2761   1.0000
  14.750   1.5501   0.05001   0.04587  -0.0629   0.2624   1.0000
  15.000   1.5342   0.05376   0.04956  -0.0610   0.2444   1.0000
  15.250   1.5190   0.05753   0.05325  -0.0593   0.2261   1.0000
  15.500   1.5080   0.06100   0.05665  -0.0580   0.2105   1.0000
  15.750   1.5001   0.06420   0.05979  -0.0568   0.1950   1.0000
  16.000   1.4919   0.06750   0.06304  -0.0558   0.1805   1.0000
  16.250   1.4836   0.07085   0.06630  -0.0548   0.1640   1.0000
  16.500   1.4793   0.07388   0.06928  -0.0541   0.1516   1.0000
  16.750   1.4739   0.07706   0.07239  -0.0534   0.1375   1.0000
  17.000   1.4742   0.07963   0.07493  -0.0530   0.1277   1.0000
  17.250   1.4710   0.08268   0.07795  -0.0526   0.1175   1.0000
  17.500   1.4695   0.08555   0.08077  -0.0523   0.1066   1.0000
<< Back to RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)

Polar data table (+)

Polar graphs


<< Back to RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)