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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 200,000
Max Cl/Cd: 52.28 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf30-il-200000.txt
Download as CSV file: xf-raf30-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 30 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7279   0.10867   0.10473  -0.0199   1.0000   0.0491
 -13.750  -0.7197   0.10703   0.10310  -0.0197   1.0000   0.0497
 -13.500  -0.9410   0.06599   0.06111  -0.0481   1.0000   0.0407
 -13.250  -0.9636   0.06193   0.05684  -0.0487   1.0000   0.0405
 -13.000  -0.9843   0.05776   0.05248  -0.0482   1.0000   0.0407
 -12.750  -1.0018   0.05457   0.04908  -0.0467   1.0000   0.0407
 -12.500  -1.0170   0.05133   0.04562  -0.0445   1.0000   0.0408
 -12.250  -1.0273   0.04853   0.04263  -0.0417   1.0000   0.0410
 -12.000  -1.0323   0.04587   0.03983  -0.0390   1.0000   0.0415
 -11.750  -1.0362   0.04357   0.03735  -0.0358   1.0000   0.0417
 -11.500  -1.0335   0.04144   0.03505  -0.0334   1.0000   0.0423
 -11.250  -1.0262   0.03949   0.03297  -0.0313   1.0000   0.0430
 -11.000  -1.0185   0.03776   0.03108  -0.0291   1.0000   0.0440
 -10.750  -1.0105   0.03607   0.02918  -0.0268   1.0000   0.0451
 -10.500  -1.0013   0.03443   0.02730  -0.0244   1.0000   0.0462
 -10.250  -0.9900   0.03283   0.02544  -0.0222   1.0000   0.0471
 -10.000  -0.9770   0.03143   0.02378  -0.0201   1.0000   0.0478
  -9.750  -0.9581   0.02898   0.02121  -0.0192   1.0000   0.0492
  -9.500  -0.9393   0.02764   0.01989  -0.0181   1.0000   0.0510
  -9.250  -0.9215   0.02653   0.01872  -0.0167   1.0000   0.0526
  -9.000  -0.9030   0.02542   0.01751  -0.0152   1.0000   0.0541
  -8.750  -0.8845   0.02441   0.01640  -0.0137   1.0000   0.0557
  -8.500  -0.8664   0.02364   0.01550  -0.0121   1.0000   0.0571
  -8.250  -0.8495   0.02213   0.01407  -0.0105   1.0000   0.0594
  -8.000  -0.8334   0.02127   0.01322  -0.0086   1.0000   0.0615
  -7.750  -0.8174   0.02049   0.01242  -0.0066   1.0000   0.0637
  -7.500  -0.8013   0.01982   0.01169  -0.0045   1.0000   0.0663
  -7.250  -0.7883   0.01892   0.01082  -0.0020   1.0000   0.0694
  -7.000  -0.7745   0.01823   0.01015   0.0004   1.0000   0.0732
  -6.750  -0.7597   0.01764   0.00952   0.0028   1.0000   0.0778
  -6.500  -0.7482   0.01687   0.00884   0.0056   1.0000   0.0846
  -6.250  -0.7363   0.01617   0.00823   0.0083   1.0000   0.0974
  -6.000  -0.7277   0.01526   0.00754   0.0116   1.0000   0.1306
  -5.750  -0.7192   0.01444   0.00700   0.0147   1.0000   0.1770
  -5.500  -0.7089   0.01384   0.00667   0.0175   1.0000   0.2238
  -5.250  -0.6969   0.01343   0.00645   0.0201   1.0000   0.2688
  -5.000  -0.6846   0.01309   0.00628   0.0225   1.0000   0.3082
  -4.500  -0.6282   0.01246   0.00601   0.0211   0.9925   0.3999
  -4.250  -0.5903   0.01217   0.00592   0.0187   0.9854   0.4514
  -4.000  -0.5530   0.01195   0.00585   0.0166   0.9778   0.4972
  -3.750  -0.5134   0.01180   0.00580   0.0141   0.9712   0.5385
  -3.500  -0.4786   0.01165   0.00575   0.0127   0.9623   0.5739
  -3.250  -0.4375   0.01154   0.00570   0.0101   0.9568   0.6050
  -3.000  -0.4031   0.01141   0.00561   0.0089   0.9477   0.6285
  -2.750  -0.3608   0.01128   0.00549   0.0062   0.9426   0.6507
  -2.500  -0.3246   0.01117   0.00544   0.0047   0.9345   0.6718
  -2.250  -0.2851   0.01108   0.00537   0.0028   0.9282   0.6973
  -2.000  -0.2491   0.01098   0.00533   0.0016   0.9198   0.7164
  -1.750  -0.2110   0.01085   0.00521  -0.0001   0.9119   0.7321
  -1.500  -0.1784   0.01075   0.00511  -0.0007   0.9009   0.7467
  -1.250  -0.1428   0.01064   0.00501  -0.0018   0.8907   0.7600
  -1.000  -0.1106   0.01054   0.00492  -0.0021   0.8779   0.7728
  -0.750  -0.0825   0.01049   0.00486  -0.0016   0.8636   0.7856
  -0.500  -0.0553   0.01046   0.00483  -0.0010   0.8500   0.7988
  -0.250  -0.0285   0.01044   0.00480  -0.0004   0.8370   0.8124
   0.000   0.0000   0.01044   0.00480   0.0000   0.8248   0.8248
   0.250   0.0285   0.01044   0.00480   0.0004   0.8124   0.8370
   0.500   0.0553   0.01046   0.00483   0.0010   0.7988   0.8500
   0.750   0.0825   0.01049   0.00486   0.0016   0.7856   0.8636
   1.000   0.1106   0.01054   0.00492   0.0021   0.7728   0.8779
   1.250   0.1428   0.01064   0.00501   0.0018   0.7601   0.8907
   1.500   0.1784   0.01075   0.00512   0.0007   0.7467   0.9009
   1.750   0.2111   0.01085   0.00521   0.0001   0.7320   0.9119
   2.000   0.2491   0.01098   0.00534  -0.0016   0.7166   0.9198
   2.250   0.2850   0.01107   0.00537  -0.0028   0.6971   0.9282
   2.500   0.3245   0.01116   0.00543  -0.0047   0.6718   0.9345
   2.750   0.3609   0.01128   0.00549  -0.0062   0.6509   0.9426
   3.000   0.4031   0.01142   0.00561  -0.0089   0.6285   0.9477
   3.250   0.4376   0.01154   0.00570  -0.0101   0.6049   0.9568
   3.500   0.4787   0.01165   0.00574  -0.0127   0.5734   0.9624
   3.750   0.5133   0.01180   0.00580  -0.0141   0.5385   0.9711
   4.000   0.5531   0.01195   0.00585  -0.0166   0.4973   0.9778
   4.250   0.5904   0.01217   0.00592  -0.0187   0.4514   0.9854
   4.500   0.6283   0.01246   0.00601  -0.0212   0.3996   0.9926
   4.750   0.6675   0.01280   0.00612  -0.0240   0.3472   0.9991
   5.000   0.6844   0.01309   0.00627  -0.0225   0.3071   1.0000
   5.250   0.6968   0.01343   0.00645  -0.0200   0.2683   1.0000
   5.500   0.7088   0.01384   0.00667  -0.0175   0.2238   1.0000
   5.750   0.7190   0.01444   0.00701  -0.0147   0.1764   1.0000
   6.000   0.7276   0.01526   0.00755  -0.0116   0.1302   1.0000
   6.250   0.7362   0.01617   0.00823  -0.0083   0.0974   1.0000
   6.500   0.7481   0.01687   0.00884  -0.0055   0.0845   1.0000
   6.750   0.7596   0.01764   0.00952  -0.0027   0.0778   1.0000
   7.000   0.7744   0.01823   0.01015  -0.0004   0.0732   1.0000
   7.250   0.7882   0.01893   0.01083   0.0020   0.0694   1.0000
   7.500   0.8012   0.01983   0.01170   0.0045   0.0664   1.0000
   7.750   0.8175   0.02049   0.01242   0.0066   0.0638   1.0000
   8.000   0.8334   0.02127   0.01322   0.0086   0.0615   1.0000
   8.250   0.8495   0.02212   0.01406   0.0105   0.0595   1.0000
   8.500   0.8665   0.02365   0.01551   0.0120   0.0571   1.0000
   8.750   0.8846   0.02443   0.01641   0.0137   0.0557   1.0000
   9.000   0.9031   0.02544   0.01753   0.0152   0.0541   1.0000
   9.250   0.9215   0.02652   0.01870   0.0167   0.0525   1.0000
   9.500   0.9393   0.02762   0.01987   0.0181   0.0509   1.0000
   9.750   0.9582   0.02899   0.02122   0.0192   0.0493   1.0000
  10.000   0.9772   0.03145   0.02380   0.0200   0.0479   1.0000
  10.250   0.9903   0.03283   0.02543   0.0221   0.0471   1.0000
  10.500   1.0014   0.03443   0.02730   0.0244   0.0462   1.0000
  10.750   1.0105   0.03611   0.02923   0.0268   0.0451   1.0000
  11.000   1.0186   0.03778   0.03110   0.0291   0.0440   1.0000
  11.250   1.0267   0.03947   0.03294   0.0312   0.0430   1.0000
  11.500   1.0332   0.04147   0.03509   0.0334   0.0423   1.0000
  11.750   1.0357   0.04364   0.03743   0.0359   0.0418   1.0000
  12.000   1.0315   0.04592   0.03989   0.0391   0.0416   1.0000
  12.250   1.0274   0.04837   0.04249   0.0418   0.0411   1.0000
  12.500   1.0161   0.05122   0.04554   0.0446   0.0409   1.0000
  12.750   1.0025   0.05453   0.04904   0.0466   0.0407   1.0000
  13.000   0.9847   0.05829   0.05299   0.0480   0.0405   1.0000
  13.250   0.9627   0.06245   0.05737   0.0485   0.0404   1.0000
  13.500   0.9392   0.06604   0.06119   0.0479   0.0408   1.0000
  13.750   0.6283   0.09894   0.09524   0.0262   0.0498   1.0000
  14.000   0.6277   0.10251   0.09881   0.0251   0.0491   1.0000
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