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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 500,000
Max Cl/Cd: 109.47 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr1-il-500000.txt
Download as CSV file: xf-cr1-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2925   0.12419   0.12178  -0.0431   1.0000   0.0379
 -11.750  -0.2904   0.12156   0.11917  -0.0432   1.0000   0.0391
 -11.250  -0.6446   0.03331   0.02993  -0.1114   0.9714   0.0359
 -11.000  -0.6274   0.03046   0.02692  -0.1133   0.9655   0.0366
 -10.750  -0.5983   0.02954   0.02598  -0.1149   0.9605   0.0374
 -10.500  -0.5693   0.02795   0.02424  -0.1171   0.9563   0.0382
 -10.250  -0.5463   0.02635   0.02245  -0.1180   0.9482   0.0390
 -10.000  -0.5198   0.02476   0.02062  -0.1193   0.9417   0.0399
  -9.750  -0.4987   0.02332   0.01892  -0.1192   0.9323   0.0406
  -9.500  -0.4739   0.02208   0.01740  -0.1196   0.9246   0.0412
  -9.250  -0.4551   0.02106   0.01615  -0.1184   0.9139   0.0416
  -9.000  -0.4386   0.01919   0.01406  -0.1173   0.9045   0.0425
  -8.750  -0.4169   0.01856   0.01337  -0.1163   0.8951   0.0434
  -8.500  -0.3945   0.01797   0.01268  -0.1154   0.8866   0.0441
  -8.250  -0.3724   0.01735   0.01193  -0.1144   0.8781   0.0449
  -8.000  -0.3499   0.01676   0.01120  -0.1135   0.8701   0.0457
  -7.750  -0.3273   0.01618   0.01047  -0.1125   0.8619   0.0465
  -7.500  -0.3037   0.01567   0.00982  -0.1116   0.8548   0.0474
  -7.250  -0.2800   0.01524   0.00927  -0.1107   0.8473   0.0481
  -7.000  -0.2573   0.01438   0.00827  -0.1098   0.8412   0.0494
  -6.750  -0.2342   0.01392   0.00778  -0.1089   0.8339   0.0507
  -6.500  -0.2093   0.01355   0.00735  -0.1082   0.8279   0.0519
  -6.250  -0.1840   0.01322   0.00693  -0.1076   0.8224   0.0533
  -6.000  -0.1591   0.01288   0.00653  -0.1069   0.8162   0.0547
  -5.750  -0.1329   0.01264   0.00616  -0.1064   0.8110   0.0560
  -5.500  -0.1089   0.01209   0.00560  -0.1056   0.8060   0.0585
  -5.250  -0.0833   0.01188   0.00538  -0.1050   0.8006   0.0611
  -5.000  -0.0569   0.01168   0.00510  -0.1046   0.7957   0.0639
  -4.750  -0.0309   0.01135   0.00474  -0.1041   0.7914   0.0677
  -4.500  -0.0050   0.01119   0.00459  -0.1035   0.7864   0.0721
  -4.250   0.0211   0.01098   0.00435  -0.1030   0.7817   0.0774
  -4.000   0.0485   0.01091   0.00425  -0.1028   0.7774   0.0833
  -3.750   0.0749   0.01077   0.00409  -0.1023   0.7729   0.0892
  -3.500   0.1013   0.01070   0.00403  -0.1019   0.7674   0.0949
  -3.250   0.1285   0.01064   0.00389  -0.1015   0.7622   0.0995
  -3.000   0.1546   0.01047   0.00373  -0.1010   0.7571   0.1055
  -2.750   0.1809   0.01040   0.00364  -0.1005   0.7518   0.1103
  -2.500   0.2073   0.01027   0.00348  -0.1001   0.7468   0.1155
  -2.250   0.2343   0.01019   0.00339  -0.0997   0.7419   0.1211
  -2.000   0.2603   0.01012   0.00331  -0.0992   0.7366   0.1258
  -1.750   0.2863   0.00998   0.00318  -0.0986   0.7314   0.1316
  -1.500   0.3138   0.00995   0.00313  -0.0984   0.7268   0.1384
  -1.250   0.3396   0.00987   0.00307  -0.0978   0.7219   0.1448
  -1.000   0.3656   0.00978   0.00302  -0.0973   0.7166   0.1523
  -0.750   0.3925   0.00974   0.00294  -0.0969   0.7117   0.1596
  -0.500   0.4187   0.00968   0.00293  -0.0964   0.7065   0.1693
  -0.250   0.4443   0.00961   0.00289  -0.0957   0.7007   0.1801
   0.000   0.4709   0.00958   0.00284  -0.0953   0.6949   0.1920
   0.250   0.4960   0.00952   0.00283  -0.0945   0.6874   0.2051
   0.500   0.5210   0.00944   0.00277  -0.0938   0.6793   0.2179
   0.750   0.5461   0.00938   0.00273  -0.0930   0.6715   0.2297
   1.000   0.5714   0.00934   0.00270  -0.0923   0.6639   0.2415
   1.250   0.5966   0.00929   0.00268  -0.0916   0.6568   0.2552
   1.500   0.6211   0.00921   0.00267  -0.0908   0.6482   0.2703
   1.750   0.6458   0.00916   0.00265  -0.0900   0.6404   0.2893
   2.000   0.6696   0.00905   0.00266  -0.0890   0.6312   0.3212
   2.250   0.6865   0.00848   0.00271  -0.0869   0.6221   0.5375
   2.500   0.8497   0.00790   0.00307  -0.1163   0.5993   1.0000
   2.750   0.8715   0.00800   0.00309  -0.1149   0.5834   1.0000
   3.000   0.8920   0.00815   0.00314  -0.1132   0.5645   1.0000
   3.250   0.9119   0.00833   0.00321  -0.1115   0.5428   1.0000
   3.500   0.9311   0.00855   0.00331  -0.1097   0.5202   1.0000
   3.750   0.9492   0.00882   0.00345  -0.1076   0.4974   1.0000
   4.000   0.9674   0.00910   0.00361  -0.1056   0.4745   1.0000
   4.250   0.9848   0.00940   0.00380  -0.1035   0.4529   1.0000
   4.500   1.0020   0.00972   0.00400  -0.1014   0.4329   1.0000
   4.750   1.0195   0.01002   0.00421  -0.0993   0.4141   1.0000
   5.000   1.0366   0.01033   0.00443  -0.0971   0.3966   1.0000
   5.250   1.0535   0.01064   0.00466  -0.0950   0.3802   1.0000
   5.500   1.0699   0.01095   0.00490  -0.0927   0.3646   1.0000
   5.750   1.0859   0.01127   0.00516  -0.0904   0.3500   1.0000
   6.000   1.1010   0.01161   0.00542  -0.0879   0.3360   1.0000
   6.250   1.1162   0.01194   0.00569  -0.0855   0.3225   1.0000
   6.500   1.1314   0.01225   0.00596  -0.0830   0.3101   1.0000
   6.750   1.1437   0.01257   0.00624  -0.0800   0.2983   1.0000
   7.000   1.1531   0.01293   0.00653  -0.0764   0.2866   1.0000
   7.250   1.1637   0.01328   0.00683  -0.0732   0.2749   1.0000
   7.500   1.1768   0.01362   0.00714  -0.0704   0.2648   1.0000
   7.750   1.1883   0.01404   0.00751  -0.0675   0.2558   1.0000
   8.000   1.2030   0.01439   0.00786  -0.0652   0.2482   1.0000
   8.250   1.2147   0.01488   0.00830  -0.0625   0.2413   1.0000
   8.500   1.2311   0.01522   0.00868  -0.0606   0.2357   1.0000
   8.750   1.2447   0.01570   0.00914  -0.0584   0.2295   1.0000
   9.000   1.2591   0.01618   0.00961  -0.0563   0.2234   1.0000
   9.250   1.2744   0.01663   0.01007  -0.0545   0.2173   1.0000
   9.500   1.2868   0.01725   0.01065  -0.0523   0.2117   1.0000
   9.750   1.3037   0.01767   0.01112  -0.0508   0.2069   1.0000
  10.000   1.3187   0.01820   0.01166  -0.0491   0.2016   1.0000
  10.250   1.3309   0.01890   0.01233  -0.0472   0.1966   1.0000
  10.500   1.3476   0.01939   0.01288  -0.0458   0.1933   1.0000
  10.750   1.3635   0.01993   0.01347  -0.0444   0.1891   1.0000
  11.000   1.3768   0.02063   0.01417  -0.0427   0.1843   1.0000
  11.250   1.3896   0.02139   0.01494  -0.0411   0.1803   1.0000
  11.500   1.4066   0.02191   0.01553  -0.0399   0.1760   1.0000
  11.750   1.4200   0.02266   0.01630  -0.0385   0.1708   1.0000
  12.000   1.4314   0.02355   0.01720  -0.0369   0.1659   1.0000
  12.250   1.4477   0.02417   0.01789  -0.0359   0.1606   1.0000
  12.500   1.4587   0.02514   0.01885  -0.0344   0.1541   1.0000
  12.750   1.4726   0.02594   0.01970  -0.0332   0.1468   1.0000
  13.000   1.4822   0.02707   0.02080  -0.0318   0.1369   1.0000
  13.250   1.4904   0.02833   0.02201  -0.0303   0.1198   1.0000
  13.500   1.4814   0.03095   0.02435  -0.0278   0.0868   1.0000
  13.750   1.4739   0.03357   0.02686  -0.0255   0.0670   1.0000
  14.000   1.4495   0.03777   0.03080  -0.0227   0.0336   1.0000
  14.250   1.4443   0.04052   0.03357  -0.0212   0.0279   1.0000
  14.500   1.4441   0.04289   0.03601  -0.0201   0.0255   1.0000
  14.750   1.4435   0.04537   0.03857  -0.0191   0.0239   1.0000
  15.000   1.4382   0.04844   0.04172  -0.0182   0.0223   1.0000
  15.250   1.4388   0.05099   0.04437  -0.0176   0.0216   1.0000
  15.500   1.4371   0.05386   0.04735  -0.0171   0.0207   1.0000
  15.750   1.4330   0.05710   0.05069  -0.0168   0.0200   1.0000
  16.000   1.4271   0.06070   0.05439  -0.0167   0.0195   1.0000
  16.250   1.4173   0.06490   0.05869  -0.0169   0.0189   1.0000
  16.500   1.4046   0.06964   0.06355  -0.0174   0.0186   1.0000
  16.750   1.3966   0.07390   0.06794  -0.0180   0.0182   1.0000
  17.000   1.3883   0.07833   0.07248  -0.0188   0.0179   1.0000
  17.250   1.3786   0.08302   0.07730  -0.0198   0.0177   1.0000
  17.500   1.3672   0.08808   0.08247  -0.0210   0.0172   1.0000
  17.750   1.3557   0.09325   0.08777  -0.0223   0.0171   1.0000
  18.000   1.3423   0.09876   0.09340  -0.0239   0.0169   1.0000
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