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RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il)
Reynolds number: 200,000
Max Cl/Cd: 59.89 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-amsoil1-il-200000-n5.txt
Download as CSV file: xf-amsoil1-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5649   0.08908   0.08512  -0.0305   1.0000   0.0315
 -10.250  -0.6859   0.05692   0.05277  -0.0559   1.0000   0.0314
 -10.000  -0.7879   0.03812   0.03255  -0.0563   1.0000   0.0321
  -9.750  -0.7712   0.03715   0.03156  -0.0559   0.9964   0.0325
  -9.500  -0.7449   0.03601   0.03035  -0.0572   0.9858   0.0331
  -9.250  -0.7212   0.03423   0.02836  -0.0584   0.9762   0.0338
  -9.000  -0.7001   0.03166   0.02541  -0.0593   0.9671   0.0348
  -8.750  -0.6796   0.02875   0.02198  -0.0598   0.9587   0.0358
  -8.500  -0.6583   0.02655   0.01930  -0.0597   0.9500   0.0367
  -8.250  -0.6321   0.02575   0.01847  -0.0600   0.9433   0.0374
  -8.000  -0.6078   0.02504   0.01769  -0.0598   0.9350   0.0382
  -7.750  -0.5832   0.02415   0.01664  -0.0596   0.9283   0.0393
  -7.500  -0.5594   0.02307   0.01533  -0.0592   0.9212   0.0404
  -7.250  -0.5353   0.02197   0.01397  -0.0587   0.9145   0.0414
  -7.000  -0.5108   0.02113   0.01303  -0.0582   0.9085   0.0423
  -6.750  -0.4857   0.02059   0.01247  -0.0579   0.9017   0.0433
  -6.500  -0.4606   0.02005   0.01186  -0.0575   0.8961   0.0446
  -6.250  -0.4352   0.01941   0.01109  -0.0571   0.8906   0.0461
  -6.000  -0.4094   0.01873   0.01025  -0.0567   0.8843   0.0474
  -5.750  -0.3842   0.01814   0.00967  -0.0562   0.8789   0.0486
  -5.500  -0.3584   0.01772   0.00922  -0.0559   0.8741   0.0501
  -5.250  -0.3319   0.01727   0.00873  -0.0557   0.8682   0.0521
  -5.000  -0.3057   0.01681   0.00816  -0.0553   0.8629   0.0541
  -4.750  -0.2801   0.01636   0.00773  -0.0549   0.8584   0.0558
  -4.500  -0.2532   0.01598   0.00735  -0.0548   0.8530   0.0581
  -4.250  -0.2263   0.01563   0.00693  -0.0546   0.8477   0.0611
  -4.000  -0.2001   0.01526   0.00660  -0.0543   0.8429   0.0640
  -3.750  -0.1733   0.01495   0.00626  -0.0540   0.8386   0.0675
  -3.500  -0.1461   0.01462   0.00595  -0.0540   0.8330   0.0713
  -3.250  -0.1189   0.01436   0.00569  -0.0538   0.8279   0.0763
  -3.000  -0.0920   0.01408   0.00542  -0.0536   0.8236   0.0817
  -2.750  -0.0645   0.01385   0.00519  -0.0535   0.8190   0.0880
  -2.500  -0.0369   0.01361   0.00500  -0.0535   0.8137   0.0954
  -2.250  -0.0094   0.01339   0.00481  -0.0534   0.8088   0.1041
  -2.000   0.0181   0.01320   0.00462  -0.0533   0.8048   0.1150
  -1.750   0.0460   0.01299   0.00449  -0.0533   0.8002   0.1290
  -1.500   0.0739   0.01279   0.00438  -0.0534   0.7951   0.1478
  -1.250   0.1015   0.01253   0.00425  -0.0534   0.7905   0.1765
  -1.000   0.1286   0.01218   0.00410  -0.0533   0.7866   0.2319
  -0.750   0.1487   0.01065   0.00409  -0.0526   0.7817   0.6117
  -0.500   0.1724   0.01043   0.00426  -0.0512   0.7766   0.7265
  -0.250   0.1974   0.01039   0.00433  -0.0501   0.7719   0.7765
   0.000   0.2228   0.01039   0.00436  -0.0489   0.7680   0.8104
   0.250   0.2484   0.01043   0.00446  -0.0481   0.7622   0.8373
   0.500   0.2734   0.01045   0.00453  -0.0471   0.7570   0.8603
   0.750   0.2982   0.01046   0.00455  -0.0458   0.7526   0.8811
   1.000   0.3231   0.01049   0.00460  -0.0447   0.7482   0.9010
   1.250   0.3484   0.01053   0.00469  -0.0437   0.7426   0.9228
   1.500   0.3763   0.01052   0.00469  -0.0431   0.7366   0.9436
   1.750   0.4077   0.01045   0.00459  -0.0435   0.7240   0.9560
   2.000   0.4402   0.01035   0.00444  -0.0441   0.7076   0.9630
   2.250   0.4722   0.01030   0.00434  -0.0448   0.6929   0.9712
   2.500   0.5065   0.01028   0.00427  -0.0460   0.6762   0.9779
   2.750   0.5401   0.01027   0.00420  -0.0470   0.6543   0.9855
   3.000   0.5737   0.01030   0.00413  -0.0481   0.6288   0.9935
   3.250   0.6052   0.01037   0.00413  -0.0489   0.5984   1.0000
   3.500   0.6273   0.01052   0.00413  -0.0478   0.5634   1.0000
   3.750   0.6486   0.01083   0.00417  -0.0466   0.5039   1.0000
   4.000   0.6648   0.01172   0.00442  -0.0447   0.3858   1.0000
   4.250   0.6788   0.01302   0.00501  -0.0430   0.2587   1.0000
   4.500   0.6981   0.01390   0.00553  -0.0420   0.1942   1.0000
   4.750   0.7201   0.01453   0.00595  -0.0413   0.1609   1.0000
   5.000   0.7429   0.01506   0.00635  -0.0408   0.1394   1.0000
   5.250   0.7662   0.01555   0.00674  -0.0402   0.1237   1.0000
   5.500   0.7893   0.01604   0.00717  -0.0396   0.1118   1.0000
   5.750   0.8125   0.01653   0.00759  -0.0391   0.1022   1.0000
   6.000   0.8357   0.01700   0.00804  -0.0385   0.0947   1.0000
   6.250   0.8579   0.01754   0.00853  -0.0378   0.0883   1.0000
   6.500   0.8808   0.01801   0.00901  -0.0371   0.0825   1.0000
   6.750   0.9022   0.01860   0.00954  -0.0363   0.0778   1.0000
   7.000   0.9243   0.01911   0.01010  -0.0356   0.0736   1.0000
   7.250   0.9452   0.01971   0.01066  -0.0347   0.0700   1.0000
   7.500   0.9660   0.02031   0.01128  -0.0338   0.0667   1.0000
   7.750   0.9867   0.02090   0.01189  -0.0329   0.0637   1.0000
   8.000   1.0058   0.02159   0.01255  -0.0318   0.0613   1.0000
   8.250   1.0251   0.02227   0.01327  -0.0307   0.0592   1.0000
   8.500   1.0444   0.02293   0.01398  -0.0296   0.0570   1.0000
   8.750   1.0623   0.02361   0.01467  -0.0284   0.0550   1.0000
   9.000   1.0777   0.02442   0.01545  -0.0268   0.0535   1.0000
   9.250   1.0952   0.02517   0.01629  -0.0255   0.0520   1.0000
   9.500   1.1123   0.02597   0.01716  -0.0242   0.0505   1.0000
   9.750   1.1291   0.02679   0.01801  -0.0230   0.0491   1.0000
  10.000   1.1452   0.02764   0.01888  -0.0218   0.0479   1.0000
  10.250   1.1604   0.02863   0.01987  -0.0206   0.0468   1.0000
  10.500   1.1773   0.02956   0.02092  -0.0194   0.0456   1.0000
  10.750   1.1934   0.03056   0.02201  -0.0183   0.0444   1.0000
  11.000   1.2088   0.03158   0.02310  -0.0171   0.0434   1.0000
  11.250   1.2234   0.03261   0.02419  -0.0160   0.0425   1.0000
  11.500   1.2372   0.03370   0.02530  -0.0149   0.0416   1.0000
  11.750   1.2508   0.03493   0.02657  -0.0138   0.0408   1.0000
  12.000   1.2642   0.03620   0.02802  -0.0126   0.0399   1.0000
  12.250   1.2766   0.03755   0.02952  -0.0115   0.0390   1.0000
  12.500   1.2882   0.03895   0.03103  -0.0104   0.0383   1.0000
  12.750   1.2987   0.04037   0.03255  -0.0093   0.0375   1.0000
  13.000   1.3084   0.04182   0.03407  -0.0082   0.0369   1.0000
  13.250   1.3176   0.04332   0.03562  -0.0073   0.0363   1.0000
  13.500   1.3264   0.04498   0.03731  -0.0063   0.0358   1.0000
  13.750   1.3307   0.04711   0.03969  -0.0052   0.0351   1.0000
  14.000   1.3340   0.04937   0.04218  -0.0042   0.0345   1.0000
  14.250   1.3360   0.05177   0.04478  -0.0034   0.0340   1.0000
  14.500   1.3367   0.05431   0.04750  -0.0027   0.0335   1.0000
  14.750   1.3364   0.05698   0.05033  -0.0022   0.0330   1.0000
  15.000   1.3354   0.05974   0.05323  -0.0019   0.0326   1.0000
  15.250   1.3341   0.06259   0.05621  -0.0018   0.0322   1.0000
  15.500   1.3325   0.06552   0.05923  -0.0018   0.0319   1.0000
  15.750   1.3305   0.06856   0.06237  -0.0021   0.0315   1.0000
  16.000   1.3280   0.07179   0.06567  -0.0025   0.0312   1.0000
  16.250   1.3158   0.07658   0.07068  -0.0036   0.0310   1.0000
  16.500   1.2964   0.08276   0.07716  -0.0058   0.0307   1.0000
  16.750   1.2739   0.08993   0.08462  -0.0090   0.0305   1.0000
  17.000   1.2463   0.09861   0.09358  -0.0135   0.0304   1.0000
  17.250   1.2100   0.10983   0.10512  -0.0202   0.0304   1.0000
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