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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 100,000
Max Cl/Cd: 54.68 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr1-il-100000.txt
Download as CSV file: xf-cr1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CURTISS CR-1 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3549   0.11265   0.10821  -0.0223   1.0000   0.1239
  -8.250  -0.3834   0.11259   0.10824  -0.0266   0.9964   0.1266
  -8.000  -0.4042   0.11037   0.10608  -0.0353   0.9869   0.1274
  -7.750  -0.3440   0.10324   0.09885  -0.0305   0.9888   0.1303
  -7.500  -0.3236   0.09989   0.09547  -0.0330   0.9845   0.1339
  -7.250  -0.3182   0.09713   0.09271  -0.0364   0.9781   0.1383
  -7.000  -0.3592   0.09577   0.09131  -0.0506   0.9621   0.1424
  -6.750  -0.3330   0.09089   0.08651  -0.0461   0.9610   0.1440
  -6.500  -0.3057   0.08796   0.08355  -0.0447   0.9582   0.1476
  -6.250  -0.2953   0.08519   0.08076  -0.0473   0.9522   0.1528
  -6.000  -0.3040   0.08107   0.07651  -0.0576   0.9415   0.1589
  -5.750  -0.2835   0.07797   0.07345  -0.0556   0.9383   0.1608
  -5.500  -0.2786   0.07602   0.07151  -0.0535   0.9315   0.1634
  -5.250  -0.2640   0.07212   0.06731  -0.0638   0.9246   0.1747
  -5.000  -0.2602   0.06981   0.06509  -0.0598   0.9185   0.1762
  -4.750  -0.2446   0.06772   0.06303  -0.0583   0.9133   0.1802
  -4.500  -0.2191   0.06399   0.05901  -0.0651   0.9083   0.1922
  -4.250  -0.2248   0.04997   0.04394  -0.0694   0.9006   0.1285
  -4.000  -0.2033   0.04635   0.03997  -0.0701   0.8956   0.1255
  -3.750  -0.1738   0.04211   0.03509  -0.0720   0.8919   0.1262
  -3.500  -0.1676   0.03991   0.03241  -0.0690   0.8847   0.1271
  -3.250  -0.1423   0.03831   0.03078  -0.0693   0.8793   0.1300
  -3.000  -0.1041   0.03741   0.02975  -0.0713   0.8754   0.1368
  -2.750  -0.0955   0.03618   0.02800  -0.0682   0.8672   0.1416
  -2.500  -0.0645   0.03528   0.02710  -0.0690   0.8617   0.1477
  -2.250  -0.0214   0.03415   0.02555  -0.0714   0.8580   0.1593
  -2.000  -0.0161   0.03428   0.02578  -0.0679   0.8481   0.1643
  -1.750   0.0233   0.03350   0.02473  -0.0697   0.8432   0.1766
  -1.500   0.0394   0.03353   0.02477  -0.0679   0.8346   0.1842
  -1.250   0.0735   0.03296   0.02405  -0.0688   0.8284   0.1955
  -1.000   0.1078   0.03262   0.02349  -0.0696   0.8224   0.2072
  -0.750   0.1283   0.03237   0.02331  -0.0684   0.8134   0.2153
  -0.500   0.1761   0.03154   0.02239  -0.0713   0.8094   0.2290
  -0.250   0.1875   0.03172   0.02251  -0.0686   0.7983   0.2371
   0.000   0.2348   0.03086   0.02165  -0.0713   0.7939   0.2519
   0.250   0.2501   0.03093   0.02173  -0.0692   0.7831   0.2620
   0.500   0.2973   0.03001   0.02086  -0.0718   0.7784   0.2806
   0.750   0.3517   0.02890   0.01982  -0.0754   0.7752   0.3084
   1.000   0.3646   0.02897   0.02000  -0.0729   0.7630   0.3255
   1.250   0.4309   0.02747   0.01878  -0.0786   0.7608   0.3763
   1.500   0.5990   0.02402   0.01690  -0.1040   0.7616   1.0000
   1.750   0.6170   0.02418   0.01694  -0.1017   0.7500   1.0000
   2.000   0.6666   0.02322   0.01582  -0.1041   0.7449   1.0000
   2.250   0.6871   0.02322   0.01574  -0.1021   0.7331   1.0000
   2.500   0.7373   0.02211   0.01450  -0.1045   0.7273   1.0000
   2.750   0.7568   0.02208   0.01442  -0.1023   0.7143   1.0000
   3.000   0.7861   0.02170   0.01398  -0.1015   0.7034   1.0000
   3.250   0.8259   0.02096   0.01313  -0.1024   0.6943   1.0000
   3.500   0.8463   0.02089   0.01304  -0.1004   0.6806   1.0000
   3.750   0.8708   0.02070   0.01280  -0.0990   0.6675   1.0000
   4.000   0.8994   0.02036   0.01240  -0.0982   0.6550   1.0000
   4.250   0.9306   0.01993   0.01190  -0.0979   0.6423   1.0000
   4.500   0.9558   0.01968   0.01159  -0.0966   0.6274   1.0000
   4.750   0.9784   0.01951   0.01137  -0.0949   0.6110   1.0000
   5.000   0.9968   0.01948   0.01132  -0.0926   0.5926   1.0000
   5.250   1.0164   0.01946   0.01123  -0.0905   0.5732   1.0000
   5.500   1.0378   0.01945   0.01113  -0.0887   0.5533   1.0000
   5.750   1.0604   0.01952   0.01106  -0.0873   0.5334   1.0000
   6.000   1.0805   0.01976   0.01116  -0.0854   0.5125   1.0000
   6.250   1.0983   0.02014   0.01143  -0.0833   0.4911   1.0000
   6.500   1.1175   0.02057   0.01170  -0.0815   0.4710   1.0000
   6.750   1.1375   0.02109   0.01205  -0.0799   0.4520   1.0000
   7.000   1.1578   0.02168   0.01246  -0.0785   0.4342   1.0000
   7.250   1.1764   0.02233   0.01300  -0.0768   0.4176   1.0000
   7.500   1.1952   0.02301   0.01362  -0.0752   0.4027   1.0000
   7.750   1.2128   0.02373   0.01432  -0.0735   0.3892   1.0000
   8.000   1.2319   0.02450   0.01507  -0.0721   0.3772   1.0000
   8.250   1.2557   0.02528   0.01575  -0.0715   0.3668   1.0000
   8.500   1.2744   0.02603   0.01654  -0.0700   0.3568   1.0000
   8.750   1.2941   0.02687   0.01739  -0.0688   0.3480   1.0000
   9.000   1.3164   0.02765   0.01814  -0.0680   0.3396   1.0000
   9.250   1.3359   0.02858   0.01914  -0.0669   0.3325   1.0000
   9.500   1.3545   0.02941   0.02006  -0.0655   0.3255   1.0000
   9.750   1.3796   0.03032   0.02094  -0.0653   0.3188   1.0000
  10.000   1.3893   0.03118   0.02198  -0.0625   0.3120   1.0000
  10.250   1.4203   0.03196   0.02262  -0.0633   0.3049   1.0000
  10.500   1.4248   0.03295   0.02390  -0.0598   0.2993   1.0000
  10.750   1.4409   0.03387   0.02492  -0.0582   0.2937   1.0000
  11.000   1.4715   0.03484   0.02582  -0.0589   0.2880   1.0000
  11.250   1.4717   0.03592   0.02720  -0.0549   0.2830   1.0000
  11.500   1.4862   0.03664   0.02799  -0.0531   0.2766   1.0000
  11.750   1.5008   0.03747   0.02885  -0.0514   0.2699   1.0000
  12.000   1.4997   0.03830   0.02986  -0.0472   0.2637   1.0000
  12.250   1.5202   0.03865   0.03009  -0.0463   0.2555   1.0000
  12.500   1.5089   0.03969   0.03139  -0.0408   0.2507   1.0000
  12.750   1.5272   0.03990   0.03150  -0.0396   0.2429   1.0000
  13.000   1.5218   0.04109   0.03290  -0.0355   0.2380   1.0000
  13.250   1.5154   0.04219   0.03418  -0.0315   0.2326   1.0000
  13.500   1.5341   0.04241   0.03427  -0.0305   0.2250   1.0000
  13.750   1.5189   0.04411   0.03628  -0.0261   0.2208   1.0000
  14.000   1.5191   0.04502   0.03726  -0.0235   0.2146   1.0000
  14.250   1.5240   0.04595   0.03824  -0.0215   0.2087   1.0000
  14.500   1.5096   0.04800   0.04056  -0.0183   0.2039   1.0000
  14.750   1.5214   0.04816   0.04058  -0.0169   0.1960   1.0000
  15.000   1.5003   0.05095   0.04371  -0.0140   0.1917   1.0000
  15.250   1.4899   0.05299   0.04589  -0.0120   0.1854   1.0000
  15.500   1.4824   0.05490   0.04786  -0.0105   0.1786   1.0000
  15.750   1.4646   0.05814   0.05135  -0.0091   0.1726   1.0000
  16.000   1.4556   0.06056   0.05379  -0.0082   0.1650   1.0000
  16.250   1.4342   0.06496   0.05848  -0.0079   0.1583   1.0000
  16.500   1.4183   0.06894   0.06254  -0.0080   0.1500   1.0000
  16.750   1.3955   0.07440   0.06821  -0.0090   0.1415   1.0000
  17.000   1.3717   0.08056   0.07456  -0.0105   0.1322   1.0000
  17.250   1.3484   0.08707   0.08117  -0.0126   0.1227   1.0000
  17.500   1.3217   0.09449   0.08865  -0.0153   0.1126   1.0000
  17.750   1.2951   0.10228   0.09652  -0.0183   0.1040   1.0000
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