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RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)
Reynolds number: 200,000
Max Cl/Cd: 54.17 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r1046-il-200000-n5.txt
Download as CSV file: xf-r1046-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.0378   0.09944   0.09371  -0.1095   0.6317   0.0185
 -10.750   0.0393   0.09570   0.08998  -0.1110   0.6301   0.0179
 -10.250   0.0298   0.08558   0.07991  -0.1151   0.6275   0.0167
 -10.000   0.0398   0.08421   0.07853  -0.1158   0.6256   0.0175
  -9.750   0.0393   0.08053   0.07485  -0.1174   0.6241   0.0177
  -9.500   0.0412   0.07748   0.07180  -0.1188   0.6227   0.0182
  -9.000  -0.0459   0.05184   0.04627  -0.1341   0.6215   0.0167
  -8.750  -0.0841   0.04588   0.04015  -0.1361   0.6201   0.0166
  -8.500  -0.1095   0.04181   0.03583  -0.1345   0.6186   0.0166
  -8.250  -0.1258   0.03762   0.03125  -0.1325   0.6170   0.0166
  -8.000  -0.1313   0.03401   0.02717  -0.1304   0.6154   0.0167
  -7.750  -0.1279   0.03105   0.02370  -0.1284   0.6138   0.0168
  -7.500  -0.1131   0.02955   0.02201  -0.1273   0.6121   0.0171
  -7.250  -0.0960   0.02828   0.02055  -0.1264   0.6105   0.0174
  -7.000  -0.0779   0.02700   0.01903  -0.1255   0.6090   0.0177
  -6.750  -0.0583   0.02579   0.01758  -0.1247   0.6076   0.0182
  -6.500  -0.0377   0.02460   0.01612  -0.1239   0.6063   0.0187
  -6.250  -0.0159   0.02348   0.01471  -0.1231   0.6051   0.0194
  -6.000   0.0066   0.02251   0.01350  -0.1224   0.6037   0.0202
  -5.750   0.0297   0.02201   0.01301  -0.1220   0.6020   0.0211
  -5.500   0.0533   0.02150   0.01240  -0.1215   0.6002   0.0225
  -5.250   0.0769   0.02084   0.01160  -0.1209   0.5984   0.0238
  -5.000   0.1005   0.02032   0.01108  -0.1204   0.5968   0.0249
  -4.750   0.1244   0.01983   0.01051  -0.1199   0.5954   0.0263
  -4.500   0.1483   0.01934   0.00994  -0.1194   0.5940   0.0281
  -4.250   0.1728   0.01900   0.00957  -0.1190   0.5927   0.0306
  -4.000   0.1974   0.01866   0.00918  -0.1186   0.5915   0.0335
  -3.750   0.2224   0.01836   0.00880  -0.1183   0.5903   0.0371
  -3.500   0.2475   0.01808   0.00850  -0.1180   0.5892   0.0415
  -3.250   0.2732   0.01786   0.00823  -0.1178   0.5882   0.0475
  -3.000   0.2974   0.01767   0.00806  -0.1173   0.5868   0.0558
  -2.750   0.3213   0.01748   0.00792  -0.1169   0.5852   0.0671
  -2.500   0.3453   0.01728   0.00779  -0.1164   0.5835   0.0848
  -2.250   0.3694   0.01709   0.00770  -0.1160   0.5820   0.1133
  -2.000   0.3932   0.01686   0.00765  -0.1156   0.5807   0.1594
  -1.750   0.4166   0.01658   0.00762  -0.1152   0.5794   0.2337
  -1.500   0.4391   0.01625   0.00762  -0.1146   0.5781   0.3338
  -1.250   0.4602   0.01588   0.00770  -0.1137   0.5769   0.4641
  -1.000   0.4822   0.01567   0.00778  -0.1127   0.5758   0.5676
  -0.750   0.5056   0.01555   0.00784  -0.1119   0.5747   0.6395
  -0.500   0.5296   0.01546   0.00790  -0.1110   0.5736   0.7035
  -0.250   0.5547   0.01539   0.00798  -0.1103   0.5725   0.7722
   0.000   0.5880   0.01542   0.00815  -0.1110   0.5714   0.8548
   0.250   0.6349   0.01566   0.00844  -0.1149   0.5700   0.9171
   0.500   0.6733   0.01592   0.00866  -0.1173   0.5686   0.9476
   0.750   0.7111   0.01618   0.00887  -0.1197   0.5672   0.9692
   1.000   0.7559   0.01642   0.00906  -0.1236   0.5658   0.9845
   1.250   0.8026   0.01663   0.00920  -0.1280   0.5644   0.9961
   1.500   0.8321   0.01682   0.00934  -0.1290   0.5630   1.0000
   1.750   0.8510   0.01701   0.00948  -0.1276   0.5615   1.0000
   2.000   0.8711   0.01719   0.00962  -0.1265   0.5603   1.0000
   2.250   0.8919   0.01739   0.00976  -0.1255   0.5592   1.0000
   2.500   0.9136   0.01759   0.00991  -0.1247   0.5582   1.0000
   2.750   0.9362   0.01779   0.01006  -0.1240   0.5572   1.0000
   3.000   0.9597   0.01800   0.01021  -0.1235   0.5563   1.0000
   3.250   0.9824   0.01824   0.01042  -0.1229   0.5553   1.0000
   3.500   0.9920   0.01873   0.01099  -0.1200   0.5533   1.0000
   3.750   1.0040   0.01919   0.01150  -0.1176   0.5512   1.0000
   4.000   1.0187   0.01962   0.01196  -0.1156   0.5494   1.0000
   4.250   1.0349   0.02002   0.01239  -0.1140   0.5478   1.0000
   4.500   1.0527   0.02039   0.01277  -0.1126   0.5463   1.0000
   4.750   1.0723   0.02070   0.01308  -0.1116   0.5449   1.0000
   5.000   1.0940   0.02094   0.01332  -0.1109   0.5436   1.0000
   5.250   1.1176   0.02115   0.01352  -0.1105   0.5424   1.0000
   5.500   1.1427   0.02135   0.01371  -0.1104   0.5414   1.0000
   5.750   1.1689   0.02158   0.01394  -0.1104   0.5405   1.0000
   6.000   1.1878   0.02199   0.01438  -0.1094   0.5392   1.0000
   6.250   1.1482   0.02374   0.01634  -0.0990   0.5342   1.0000
   6.500   1.1400   0.02484   0.01751  -0.0939   0.5311   1.0000
   6.750   1.1504   0.02549   0.01819  -0.0918   0.5291   1.0000
   7.000   1.1717   0.02576   0.01848  -0.0912   0.5277   1.0000
   7.250   1.1965   0.02593   0.01866  -0.0911   0.5265   1.0000
   7.500   1.2249   0.02597   0.01872  -0.0916   0.5256   1.0000
   7.750   1.2583   0.02587   0.01863  -0.0926   0.5247   1.0000
  11.250   1.1359   0.06061   0.05422  -0.0581   0.4358   1.0000
  12.250   1.1692   0.06678   0.06064  -0.0558   0.4117   1.0000
  12.500   1.1967   0.06622   0.06014  -0.0558   0.4101   1.0000
  12.750   1.2274   0.06526   0.05924  -0.0559   0.4087   1.0000
  13.250   1.2234   0.07086   0.06499  -0.0544   0.3891   1.0000
  13.500   1.2410   0.07144   0.06562  -0.0542   0.3831   1.0000
  13.750   1.2763   0.06989   0.06412  -0.0544   0.3802   1.0000
  14.000   1.2755   0.07265   0.06695  -0.0538   0.3690   1.0000
  14.250   1.2976   0.07265   0.06698  -0.0537   0.3610   1.0000
  14.500   1.3228   0.07226   0.06660  -0.0537   0.3521   1.0000
  14.750   1.3367   0.07324   0.06761  -0.0534   0.3408   1.0000
  15.000   1.3574   0.07337   0.06772  -0.0532   0.3291   1.0000
  15.250   1.3751   0.07382   0.06815  -0.0529   0.3166   1.0000
  15.500   1.3860   0.07507   0.06936  -0.0526   0.3014   1.0000
  15.750   1.3955   0.07647   0.07070  -0.0522   0.2861   1.0000
  16.000   1.4011   0.07836   0.07253  -0.0517   0.2712   1.0000
  16.250   1.4031   0.08075   0.07487  -0.0513   0.2559   1.0000
  16.500   1.4026   0.08348   0.07755  -0.0510   0.2405   1.0000
  16.750   1.4017   0.08631   0.08035  -0.0507   0.2258   1.0000
  17.000   1.3996   0.08934   0.08333  -0.0505   0.2115   1.0000
  17.250   1.3967   0.09251   0.08646  -0.0504   0.1975   1.0000
  17.500   1.3943   0.09568   0.08960  -0.0503   0.1845   1.0000
  17.750   1.3912   0.09899   0.09289  -0.0504   0.1720   1.0000
  18.000   1.3883   0.10231   0.09618  -0.0505   0.1603   1.0000
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