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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 500,000
Max Cl/Cd: 97.77 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf48-il-500000.txt
Download as CSV file: xf-raf48-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF-48 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
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.7767   0.10552   0.10252  -0.0428   1.0000   0.0248
 -17.000  -0.8387   0.08965   0.08639  -0.0532   1.0000   0.0248
 -16.750  -0.8747   0.07966   0.07622  -0.0597   1.0000   0.0247
 -16.500  -0.9027   0.07124   0.06762  -0.0654   1.0000   0.0247
 -16.250  -0.9261   0.06385   0.06005  -0.0707   1.0000   0.0248
 -16.000  -0.9496   0.05703   0.05304  -0.0750   1.0000   0.0250
 -15.750  -0.9616   0.05219   0.04808  -0.0779   1.0000   0.0252
 -15.500  -0.9686   0.04826   0.04406  -0.0799   1.0000   0.0254
 -15.250  -0.9710   0.04513   0.04087  -0.0815   1.0000   0.0257
 -15.000  -0.9745   0.04208   0.03773  -0.0826   1.0000   0.0259
 -14.750  -0.9753   0.03959   0.03515  -0.0832   1.0000   0.0262
 -14.500  -0.9747   0.03749   0.03297  -0.0833   1.0000   0.0267
 -14.250  -0.9752   0.03545   0.03084  -0.0829   1.0000   0.0271
 -14.000  -0.9763   0.03354   0.02881  -0.0819   1.0000   0.0274
 -13.750  -0.9754   0.03199   0.02714  -0.0804   1.0000   0.0279
 -13.500  -0.9737   0.03077   0.02579  -0.0785   1.0000   0.0284
 -13.250  -0.9726   0.02964   0.02451  -0.0760   1.0000   0.0288
 -13.000  -0.9739   0.02814   0.02291  -0.0729   1.0000   0.0294
 -12.750  -0.9707   0.02714   0.02189  -0.0699   1.0000   0.0299
 -12.500  -0.9678   0.02641   0.02113  -0.0664   1.0000   0.0303
 -12.250  -0.9655   0.02588   0.02059  -0.0625   1.0000   0.0309
 -12.000  -0.9607   0.02527   0.01994  -0.0590   1.0000   0.0315
 -11.750  -0.9594   0.02470   0.01932  -0.0548   1.0000   0.0319
 -11.500  -0.9267   0.02374   0.01823  -0.0568   0.9948   0.0330
 -11.250  -0.8964   0.02272   0.01706  -0.0583   0.9858   0.0340
 -11.000  -0.8675   0.02153   0.01588  -0.0596   0.9760   0.0351
 -10.750  -0.8325   0.02080   0.01512  -0.0618   0.9682   0.0363
 -10.500  -0.7959   0.02003   0.01425  -0.0641   0.9588   0.0376
 -10.250  -0.7561   0.01937   0.01345  -0.0671   0.9493   0.0388
 -10.000  -0.7186   0.01811   0.01217  -0.0700   0.9380   0.0405
  -9.750  -0.6829   0.01748   0.01147  -0.0721   0.9235   0.0419
  -9.500  -0.6544   0.01698   0.01086  -0.0725   0.9070   0.0432
  -9.250  -0.6306   0.01667   0.01040  -0.0718   0.8911   0.0446
  -9.000  -0.6120   0.01603   0.00967  -0.0702   0.8765   0.0459
  -8.750  -0.5928   0.01554   0.00913  -0.0687   0.8638   0.0473
  -8.500  -0.5716   0.01519   0.00871  -0.0675   0.8530   0.0488
  -8.250  -0.5502   0.01486   0.00831  -0.0662   0.8420   0.0504
  -8.000  -0.5274   0.01462   0.00795  -0.0652   0.8324   0.0519
  -7.750  -0.5091   0.01399   0.00730  -0.0635   0.8230   0.0542
  -7.500  -0.4871   0.01366   0.00693  -0.0624   0.8142   0.0564
  -7.250  -0.4642   0.01340   0.00658  -0.0614   0.8052   0.0588
  -7.000  -0.4432   0.01297   0.00612  -0.0600   0.7959   0.0620
  -6.750  -0.4206   0.01268   0.00578  -0.0589   0.7873   0.0656
  -6.500  -0.3976   0.01238   0.00544  -0.0579   0.7790   0.0697
  -6.250  -0.3747   0.01207   0.00512  -0.0569   0.7716   0.0758
  -6.000  -0.3512   0.01179   0.00484  -0.0560   0.7653   0.0839
  -5.750  -0.3274   0.01152   0.00461  -0.0552   0.7588   0.0942
  -5.500  -0.3030   0.01130   0.00439  -0.0544   0.7530   0.1063
  -5.250  -0.2782   0.01112   0.00421  -0.0537   0.7475   0.1185
  -5.000  -0.2530   0.01096   0.00406  -0.0531   0.7414   0.1297
  -4.750  -0.2282   0.01078   0.00389  -0.0525   0.7358   0.1414
  -4.500  -0.2032   0.01062   0.00374  -0.0518   0.7305   0.1522
  -4.250  -0.1779   0.01046   0.00359  -0.0513   0.7250   0.1634
  -3.750  -0.1273   0.01018   0.00332  -0.0501   0.7147   0.1911
  -3.500  -0.1024   0.00999   0.00321  -0.0494   0.7090   0.2091
  -3.250  -0.0778   0.00980   0.00309  -0.0487   0.7034   0.2315
  -3.000  -0.0527   0.00966   0.00299  -0.0481   0.6983   0.2585
  -2.750  -0.0283   0.00945   0.00290  -0.0473   0.6930   0.2882
  -2.500  -0.0041   0.00924   0.00280  -0.0466   0.6874   0.3213
  -2.250   0.0192   0.00899   0.00270  -0.0456   0.6822   0.3692
  -2.000   0.0412   0.00869   0.00264  -0.0444   0.6766   0.4334
  -1.750   0.0631   0.00842   0.00258  -0.0431   0.6704   0.4947
  -1.500   0.0848   0.00818   0.00251  -0.0417   0.6647   0.5554
  -1.250   0.1057   0.00794   0.00250  -0.0401   0.6589   0.6196
  -1.000   0.1275   0.00775   0.00250  -0.0386   0.6525   0.6771
  -0.750   0.1504   0.00765   0.00249  -0.0373   0.6467   0.7244
  -0.500   0.1740   0.00754   0.00252  -0.0362   0.6398   0.7640
  -0.250   0.1988   0.00749   0.00253  -0.0352   0.6327   0.7948
   0.000   0.2240   0.00748   0.00254  -0.0344   0.6255   0.8216
   0.250   0.2500   0.00745   0.00255  -0.0337   0.6175   0.8451
   0.500   0.2778   0.00745   0.00255  -0.0335   0.6101   0.8661
   0.750   0.3083   0.00742   0.00257  -0.0338   0.6008   0.8860
   1.000   0.3450   0.00746   0.00259  -0.0355   0.5914   0.9041
   1.250   0.3898   0.00754   0.00266  -0.0390   0.5808   0.9191
   1.500   0.4375   0.00767   0.00277  -0.0431   0.5692   0.9311
   1.750   0.4779   0.00782   0.00286  -0.0456   0.5578   0.9398
   2.000   0.5159   0.00800   0.00296  -0.0477   0.5460   0.9461
   2.250   0.5483   0.00818   0.00311  -0.0485   0.5340   0.9557
   2.500   0.5877   0.00840   0.00326  -0.0508   0.5213   0.9613
   2.750   0.6200   0.00862   0.00341  -0.0517   0.5093   0.9701
   3.000   0.6610   0.00883   0.00354  -0.0545   0.4970   0.9741
   3.250   0.6973   0.00900   0.00368  -0.0563   0.4867   0.9796
   3.500   0.7325   0.00919   0.00380  -0.0580   0.4771   0.9839
   3.750   0.7703   0.00932   0.00390  -0.0602   0.4676   0.9872
   4.000   0.8076   0.00948   0.00403  -0.0624   0.4588   0.9915
   4.250   0.8473   0.00962   0.00413  -0.0651   0.4496   0.9952
   4.500   0.8876   0.00972   0.00422  -0.0679   0.4418   0.9987
   4.750   0.9153   0.00982   0.00430  -0.0682   0.4345   1.0000
   5.000   0.9325   0.00996   0.00440  -0.0662   0.4283   1.0000
   5.250   0.9512   0.01003   0.00450  -0.0646   0.4218   1.0000
   5.500   0.9695   0.01018   0.00462  -0.0628   0.4157   1.0000
   5.750   0.9890   0.01032   0.00477  -0.0613   0.4099   1.0000
   6.000   1.0093   0.01044   0.00491  -0.0599   0.4034   1.0000
   6.250   1.0284   0.01065   0.00509  -0.0582   0.3969   1.0000
   6.500   1.0492   0.01077   0.00525  -0.0569   0.3891   1.0000
   6.750   1.0677   0.01100   0.00543  -0.0552   0.3800   1.0000
   7.000   1.0882   0.01113   0.00560  -0.0538   0.3698   1.0000
   7.250   1.1070   0.01135   0.00581  -0.0521   0.3603   1.0000
   7.500   1.1254   0.01157   0.00602  -0.0504   0.3487   1.0000
   7.750   1.1439   0.01179   0.00623  -0.0487   0.3358   1.0000
   8.000   1.1607   0.01207   0.00648  -0.0467   0.3208   1.0000
   8.250   1.1755   0.01242   0.00678  -0.0444   0.3033   1.0000
   8.500   1.1882   0.01284   0.00712  -0.0418   0.2852   1.0000
   8.750   1.1992   0.01332   0.00752  -0.0388   0.2662   1.0000
   9.000   1.2082   0.01382   0.00794  -0.0356   0.2491   1.0000
   9.250   1.2125   0.01432   0.00838  -0.0314   0.2342   1.0000
   9.500   1.2175   0.01485   0.00885  -0.0275   0.2213   1.0000
   9.750   1.2248   0.01540   0.00937  -0.0242   0.2093   1.0000
  10.000   1.2336   0.01598   0.00992  -0.0214   0.1980   1.0000
  10.250   1.2421   0.01664   0.01056  -0.0186   0.1877   1.0000
  10.500   1.2494   0.01743   0.01131  -0.0160   0.1772   1.0000
  10.750   1.2603   0.01812   0.01201  -0.0139   0.1678   1.0000
  11.000   1.2694   0.01896   0.01284  -0.0118   0.1585   1.0000
  11.250   1.2765   0.01998   0.01382  -0.0097   0.1485   1.0000
  11.500   1.2865   0.02089   0.01474  -0.0080   0.1388   1.0000
  11.750   1.2945   0.02199   0.01583  -0.0063   0.1287   1.0000
  12.000   1.3001   0.02330   0.01710  -0.0046   0.1162   1.0000
  12.250   1.3037   0.02484   0.01858  -0.0029   0.1017   1.0000
  12.500   1.3019   0.02684   0.02047  -0.0010   0.0829   1.0000
  12.750   1.2989   0.02904   0.02258   0.0007   0.0680   1.0000
  13.000   1.2971   0.03124   0.02475   0.0021   0.0593   1.0000
  13.250   1.2976   0.03335   0.02687   0.0032   0.0545   1.0000
  13.500   1.2961   0.03568   0.02921   0.0043   0.0507   1.0000
  13.750   1.2973   0.03785   0.03145   0.0051   0.0484   1.0000
  14.000   1.2994   0.04001   0.03367   0.0058   0.0463   1.0000
  14.250   1.2975   0.04262   0.03631   0.0064   0.0442   1.0000
  14.500   1.2937   0.04554   0.03928   0.0068   0.0424   1.0000
  14.750   1.2966   0.04784   0.04168   0.0071   0.0412   1.0000
  15.000   1.2973   0.05044   0.04436   0.0073   0.0398   1.0000
  15.250   1.2957   0.05336   0.04734   0.0073   0.0387   1.0000
  15.500   1.2902   0.05681   0.05084   0.0072   0.0375   1.0000
  15.750   1.2829   0.06054   0.05463   0.0069   0.0365   1.0000
  16.000   1.2843   0.06333   0.05752   0.0066   0.0357   1.0000
  16.250   1.2848   0.06629   0.06056   0.0062   0.0344   1.0000
  16.500   1.2822   0.06967   0.06403   0.0057   0.0337   1.0000
  16.750   1.2786   0.07321   0.06763   0.0051   0.0329   1.0000
  17.000   1.2717   0.07722   0.07168   0.0043   0.0320   1.0000
  17.250   1.2639   0.08135   0.07587   0.0035   0.0312   1.0000
  17.500   1.2642   0.08451   0.07912   0.0028   0.0307   1.0000
  17.750   1.2625   0.08801   0.08272   0.0019   0.0298   1.0000
  18.000   1.2603   0.09156   0.08635   0.0010   0.0292   1.0000
  18.250   1.2575   0.09524   0.09008   0.0000   0.0284   1.0000
  18.500   1.2540   0.09906   0.09395  -0.0012   0.0277   1.0000
  18.750   1.2496   0.10286   0.09778  -0.0022   0.0272   1.0000
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