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RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAF 27 AIRFOIL (raf27-il)
Reynolds number: 200,000
Max Cl/Cd: 43.88 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf27-il-200000-n5.txt
Download as CSV file: xf-raf27-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 27 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7880   0.08147   0.07778  -0.0188   1.0000   0.0119
 -12.250  -0.8234   0.06914   0.06527  -0.0282   1.0000   0.0116
 -12.000  -0.8509   0.06072   0.05663  -0.0343   1.0000   0.0113
 -11.750  -0.8752   0.05442   0.05010  -0.0376   1.0000   0.0112
 -11.500  -0.8936   0.04994   0.04541  -0.0386   1.0000   0.0113
 -11.250  -0.9097   0.04633   0.04157  -0.0379   1.0000   0.0113
 -11.000  -0.9233   0.04333   0.03833  -0.0356   1.0000   0.0115
 -10.750  -0.9344   0.04072   0.03547  -0.0323   1.0000   0.0116
 -10.500  -0.9404   0.03825   0.03273  -0.0290   1.0000   0.0118
 -10.250  -0.9402   0.03581   0.03000  -0.0262   1.0000   0.0121
 -10.000  -0.9351   0.03370   0.02758  -0.0238   1.0000   0.0127
  -9.750  -0.9263   0.03184   0.02543  -0.0216   1.0000   0.0132
  -9.500  -0.9150   0.03018   0.02346  -0.0195   1.0000   0.0138
  -9.250  -0.9057   0.02806   0.02115  -0.0173   1.0000   0.0147
  -9.000  -0.8916   0.02674   0.01970  -0.0155   1.0000   0.0154
  -8.750  -0.8760   0.02556   0.01839  -0.0138   1.0000   0.0162
  -8.500  -0.8599   0.02435   0.01704  -0.0121   1.0000   0.0171
  -8.250  -0.8430   0.02327   0.01580  -0.0104   1.0000   0.0184
  -8.000  -0.8248   0.02238   0.01475  -0.0088   1.0000   0.0200
  -7.750  -0.8090   0.02118   0.01345  -0.0069   1.0000   0.0215
  -7.500  -0.7922   0.02023   0.01245  -0.0052   1.0000   0.0233
  -7.250  -0.7740   0.01946   0.01157  -0.0036   1.0000   0.0257
  -7.000  -0.7544   0.01886   0.01083  -0.0021   1.0000   0.0288
  -6.750  -0.7380   0.01791   0.00985  -0.0002   1.0000   0.0316
  -6.500  -0.7195   0.01724   0.00913   0.0014   1.0000   0.0351
  -6.250  -0.6996   0.01673   0.00852   0.0028   1.0000   0.0389
  -6.000  -0.6818   0.01602   0.00782   0.0045   1.0000   0.0439
  -5.750  -0.6617   0.01556   0.00727   0.0059   1.0000   0.0493
  -5.500  -0.6426   0.01501   0.00674   0.0074   1.0000   0.0561
  -5.250  -0.6227   0.01456   0.00627   0.0089   1.0000   0.0652
  -5.000  -0.6030   0.01409   0.00581   0.0104   1.0000   0.0778
  -4.750  -0.5838   0.01360   0.00537   0.0119   1.0000   0.0952
  -4.500  -0.5649   0.01309   0.00497   0.0134   1.0000   0.1216
  -4.250  -0.5470   0.01251   0.00464   0.0150   1.0000   0.1727
  -4.000  -0.5285   0.01204   0.00438   0.0165   1.0000   0.2225
  -3.750  -0.5025   0.01165   0.00414   0.0165   0.9979   0.2671
  -3.500  -0.4666   0.01124   0.00390   0.0144   0.9915   0.3203
  -3.250  -0.4318   0.01080   0.00372   0.0125   0.9854   0.3841
  -3.000  -0.4009   0.01038   0.00356   0.0116   0.9780   0.4516
  -2.750  -0.3698   0.01004   0.00342   0.0108   0.9707   0.5096
  -2.500  -0.3378   0.00971   0.00333   0.0099   0.9640   0.5663
  -2.250  -0.3085   0.00945   0.00326   0.0097   0.9551   0.6158
  -2.000  -0.2747   0.00927   0.00318   0.0086   0.9487   0.6576
  -1.750  -0.2434   0.00911   0.00310   0.0081   0.9392   0.6877
  -1.500  -0.2096   0.00898   0.00301   0.0070   0.9308   0.7122
  -1.250  -0.1747   0.00885   0.00294   0.0057   0.9220   0.7355
  -1.000  -0.1414   0.00874   0.00288   0.0048   0.9111   0.7583
  -0.750  -0.1066   0.00864   0.00283   0.0036   0.8995   0.7808
  -0.250  -0.0354   0.00849   0.00276   0.0011   0.8679   0.8269
   0.000   0.0000   0.00847   0.00274   0.0000   0.8486   0.8487
   0.250   0.0354   0.00849   0.00276  -0.0011   0.8269   0.8679
   0.500   0.0714   0.00855   0.00278  -0.0024   0.8044   0.8853
   0.750   0.1066   0.00864   0.00283  -0.0036   0.7809   0.8995
   1.000   0.1414   0.00874   0.00288  -0.0048   0.7584   0.9111
   1.250   0.1747   0.00885   0.00294  -0.0057   0.7357   0.9221
   1.500   0.2095   0.00898   0.00301  -0.0070   0.7123   0.9308
   1.750   0.2433   0.00911   0.00310  -0.0080   0.6875   0.9393
   2.000   0.2747   0.00927   0.00318  -0.0086   0.6574   0.9487
   2.250   0.3085   0.00945   0.00326  -0.0097   0.6159   0.9552
   2.500   0.3378   0.00971   0.00333  -0.0099   0.5660   0.9640
   2.750   0.3699   0.01003   0.00342  -0.0108   0.5107   0.9708
   3.000   0.4012   0.01036   0.00357  -0.0117   0.4544   0.9780
   3.250   0.4320   0.01078   0.00372  -0.0126   0.3875   0.9854
   3.500   0.4667   0.01123   0.00390  -0.0144   0.3206   0.9916
   3.750   0.5026   0.01165   0.00414  -0.0165   0.2673   0.9980
   4.000   0.5283   0.01204   0.00437  -0.0165   0.2224   1.0000
   4.250   0.5468   0.01251   0.00464  -0.0149   0.1717   1.0000
   4.500   0.5647   0.01308   0.00496  -0.0134   0.1219   1.0000
   4.750   0.5836   0.01360   0.00537  -0.0118   0.0949   1.0000
   5.000   0.6028   0.01409   0.00581  -0.0103   0.0776   1.0000
   5.250   0.6225   0.01455   0.00627  -0.0089   0.0654   1.0000
   5.500   0.6424   0.01501   0.00674  -0.0074   0.0562   1.0000
   5.750   0.6615   0.01556   0.00726  -0.0059   0.0493   1.0000
   6.000   0.6815   0.01602   0.00782  -0.0045   0.0438   1.0000
   6.250   0.6993   0.01674   0.00852  -0.0028   0.0390   1.0000
   6.500   0.7193   0.01724   0.00913  -0.0013   0.0352   1.0000
   6.750   0.7379   0.01790   0.00984   0.0002   0.0316   1.0000
   7.000   0.7546   0.01881   0.01080   0.0021   0.0285   1.0000
   7.250   0.7739   0.01946   0.01157   0.0036   0.0256   1.0000
   7.500   0.7922   0.02023   0.01244   0.0052   0.0233   1.0000
   7.750   0.8090   0.02117   0.01344   0.0069   0.0215   1.0000
   8.000   0.8246   0.02241   0.01478   0.0089   0.0200   1.0000
   8.250   0.8429   0.02330   0.01583   0.0104   0.0185   1.0000
   8.500   0.8600   0.02436   0.01704   0.0121   0.0171   1.0000
   8.750   0.8761   0.02555   0.01838   0.0138   0.0161   1.0000
   9.000   0.8917   0.02676   0.01972   0.0155   0.0154   1.0000
   9.250   0.9059   0.02806   0.02115   0.0173   0.0147   1.0000
   9.500   0.9159   0.03007   0.02334   0.0194   0.0139   1.0000
   9.750   0.9261   0.03194   0.02549   0.0215   0.0133   1.0000
  10.000   0.9355   0.03369   0.02757   0.0237   0.0127   1.0000
  10.250   0.9407   0.03581   0.02999   0.0261   0.0122   1.0000
  10.500   0.9409   0.03826   0.03274   0.0289   0.0119   1.0000
  10.750   0.9346   0.04081   0.03557   0.0322   0.0117   1.0000
  11.000   0.9242   0.04333   0.03833   0.0355   0.0115   1.0000
  11.250   0.9106   0.04634   0.04158   0.0377   0.0114   1.0000
  11.500   0.8946   0.04995   0.04542   0.0385   0.0113   1.0000
  11.750   0.8728   0.05493   0.05064   0.0373   0.0115   1.0000
  12.000   0.8521   0.06071   0.05662   0.0341   0.0113   1.0000
  12.250   0.8243   0.06920   0.06533   0.0279   0.0116   1.0000
  12.500   0.7887   0.08168   0.07799   0.0185   0.0119   1.0000
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