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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 200,000
Max Cl/Cd: 45.59 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf30-il-200000-n5.txt
Download as CSV file: xf-raf30-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.8546   0.12012   0.11587  -0.0110   1.0000   0.0222
 -16.500  -0.8966   0.10636   0.10189  -0.0194   1.0000   0.0221
 -16.250  -0.9268   0.09614   0.09150  -0.0257   1.0000   0.0220
 -16.000  -0.9515   0.08758   0.08274  -0.0309   1.0000   0.0219
 -15.750  -0.9730   0.08015   0.07509  -0.0354   1.0000   0.0221
 -15.500  -0.9925   0.07357   0.06828  -0.0391   1.0000   0.0222
 -15.250  -1.0091   0.06791   0.06239  -0.0419   1.0000   0.0223
 -15.000  -1.0195   0.06345   0.05779  -0.0438   1.0000   0.0226
 -14.750  -1.0239   0.05998   0.05423  -0.0449   1.0000   0.0229
 -14.500  -1.0273   0.05679   0.05094  -0.0458   1.0000   0.0233
 -14.250  -1.0306   0.05369   0.04773  -0.0465   1.0000   0.0236
 -14.000  -1.0327   0.05091   0.04485  -0.0469   1.0000   0.0240
 -13.750  -1.0347   0.04819   0.04198  -0.0470   1.0000   0.0244
 -13.500  -1.0358   0.04574   0.03940  -0.0469   1.0000   0.0250
 -13.250  -1.0362   0.04348   0.03697  -0.0464   1.0000   0.0257
 -13.000  -1.0358   0.04132   0.03464  -0.0457   1.0000   0.0263
 -12.750  -1.0337   0.03941   0.03253  -0.0447   1.0000   0.0270
 -12.500  -1.0307   0.03768   0.03059  -0.0434   1.0000   0.0276
 -12.250  -1.0253   0.03590   0.02869  -0.0420   1.0000   0.0283
 -12.000  -1.0179   0.03434   0.02709  -0.0406   1.0000   0.0290
 -11.750  -1.0102   0.03306   0.02576  -0.0391   1.0000   0.0297
 -11.500  -1.0021   0.03186   0.02449  -0.0373   1.0000   0.0305
 -11.250  -0.9935   0.03076   0.02330  -0.0355   1.0000   0.0315
 -11.000  -0.9840   0.02968   0.02212  -0.0335   1.0000   0.0323
 -10.750  -0.9741   0.02869   0.02101  -0.0313   1.0000   0.0332
 -10.500  -0.9637   0.02779   0.01997  -0.0291   1.0000   0.0341
 -10.250  -0.9542   0.02674   0.01885  -0.0267   1.0000   0.0349
 -10.000  -0.9464   0.02569   0.01779  -0.0239   1.0000   0.0359
  -9.750  -0.9361   0.02482   0.01690  -0.0215   1.0000   0.0369
  -9.500  -0.9240   0.02402   0.01605  -0.0193   1.0000   0.0379
  -9.250  -0.9113   0.02324   0.01522  -0.0170   1.0000   0.0390
  -9.000  -0.8977   0.02254   0.01445  -0.0148   1.0000   0.0402
  -8.750  -0.8836   0.02187   0.01369  -0.0127   1.0000   0.0414
  -8.500  -0.8691   0.02122   0.01297  -0.0106   1.0000   0.0424
  -8.250  -0.8576   0.02038   0.01212  -0.0080   1.0000   0.0437
  -8.000  -0.8438   0.01970   0.01142  -0.0058   1.0000   0.0451
  -7.750  -0.8289   0.01911   0.01080  -0.0036   1.0000   0.0469
  -7.500  -0.8132   0.01858   0.01021  -0.0016   1.0000   0.0489
  -7.250  -0.7972   0.01808   0.00965   0.0004   1.0000   0.0509
  -7.000  -0.7824   0.01752   0.00909   0.0026   1.0000   0.0536
  -6.750  -0.7670   0.01701   0.00859   0.0048   1.0000   0.0574
  -6.500  -0.7516   0.01656   0.00814   0.0069   1.0000   0.0629
  -6.250  -0.7370   0.01608   0.00772   0.0092   1.0000   0.0736
  -6.000  -0.7053   0.01546   0.00723   0.0078   0.9949   0.0986
  -5.750  -0.6730   0.01488   0.00676   0.0063   0.9882   0.1234
  -5.500  -0.6406   0.01434   0.00632   0.0049   0.9814   0.1493
  -5.250  -0.6088   0.01380   0.00591   0.0036   0.9737   0.1798
  -5.000  -0.5792   0.01326   0.00556   0.0028   0.9647   0.2198
  -4.750  -0.5481   0.01275   0.00523   0.0017   0.9566   0.2658
  -4.500  -0.5168   0.01230   0.00494   0.0007   0.9478   0.3076
  -4.250  -0.4859   0.01187   0.00468  -0.0002   0.9383   0.3477
  -4.000  -0.4524   0.01147   0.00443  -0.0015   0.9303   0.3903
  -3.750  -0.4220   0.01113   0.00424  -0.0021   0.9194   0.4299
  -3.500  -0.3894   0.01085   0.00407  -0.0031   0.9097   0.4675
  -3.250  -0.3567   0.01063   0.00393  -0.0041   0.8993   0.5008
  -3.000  -0.3259   0.01047   0.00380  -0.0046   0.8873   0.5252
  -2.750  -0.2954   0.01033   0.00369  -0.0050   0.8754   0.5493
  -2.500  -0.2664   0.01020   0.00362  -0.0050   0.8632   0.5791
  -2.250  -0.2385   0.01011   0.00356  -0.0047   0.8506   0.6050
  -2.000  -0.2113   0.01004   0.00349  -0.0044   0.8375   0.6220
  -1.750  -0.1842   0.00999   0.00343  -0.0040   0.8245   0.6362
  -1.500  -0.1572   0.00995   0.00337  -0.0036   0.8114   0.6495
  -1.250  -0.1306   0.00991   0.00331  -0.0030   0.7968   0.6627
  -1.000  -0.1044   0.00989   0.00325  -0.0024   0.7809   0.6757
  -0.500  -0.0522   0.00986   0.00318  -0.0012   0.7523   0.7013
  -0.250  -0.0261   0.00985   0.00317  -0.0006   0.7393   0.7137
   0.000   0.0000   0.00985   0.00316   0.0000   0.7263   0.7262
   0.250   0.0261   0.00985   0.00317   0.0006   0.7137   0.7392
   0.500   0.0522   0.00986   0.00318   0.0012   0.7013   0.7524
   0.750   0.0785   0.00988   0.00320   0.0018   0.6889   0.7659
   1.000   0.1045   0.00989   0.00325   0.0024   0.6758   0.7810
   1.250   0.1306   0.00991   0.00331   0.0030   0.6628   0.7968
   1.500   0.1572   0.00995   0.00337   0.0036   0.6495   0.8114
   1.750   0.1842   0.00999   0.00343   0.0040   0.6360   0.8244
   2.000   0.2113   0.01004   0.00349   0.0044   0.6220   0.8374
   2.250   0.2385   0.01011   0.00356   0.0047   0.6052   0.8507
   2.500   0.2664   0.01020   0.00362   0.0050   0.5793   0.8632
   2.750   0.2953   0.01033   0.00369   0.0050   0.5489   0.8753
   3.000   0.3259   0.01047   0.00380   0.0046   0.5252   0.8874
   3.250   0.3567   0.01063   0.00393   0.0041   0.5005   0.8994
   3.500   0.3893   0.01086   0.00407   0.0032   0.4662   0.9097
   3.750   0.4220   0.01113   0.00424   0.0021   0.4298   0.9194
   4.000   0.4523   0.01147   0.00443   0.0016   0.3894   0.9303
   4.250   0.4858   0.01188   0.00468   0.0002   0.3472   0.9382
   4.500   0.5168   0.01230   0.00494  -0.0007   0.3073   0.9477
   4.750   0.5481   0.01275   0.00523  -0.0017   0.2660   0.9566
   5.000   0.5792   0.01327   0.00556  -0.0028   0.2192   0.9647
   5.250   0.6088   0.01381   0.00592  -0.0036   0.1788   0.9737
   5.500   0.6406   0.01434   0.00632  -0.0049   0.1489   0.9814
   5.750   0.6731   0.01488   0.00676  -0.0063   0.1234   0.9882
   6.000   0.7053   0.01547   0.00723  -0.0078   0.0976   0.9949
   6.500   0.7516   0.01655   0.00814  -0.0069   0.0629   1.0000
   6.750   0.7670   0.01702   0.00860  -0.0048   0.0573   1.0000
   7.000   0.7824   0.01751   0.00909  -0.0027   0.0537   1.0000
   7.250   0.7972   0.01808   0.00965  -0.0004   0.0509   1.0000
   7.500   0.8133   0.01858   0.01020   0.0016   0.0489   1.0000
   7.750   0.8289   0.01911   0.01080   0.0036   0.0468   1.0000
   8.000   0.8439   0.01969   0.01142   0.0057   0.0451   1.0000
   8.250   0.8577   0.02037   0.01211   0.0080   0.0437   1.0000
   8.500   0.8694   0.02121   0.01296   0.0105   0.0424   1.0000
   8.750   0.8837   0.02187   0.01369   0.0127   0.0414   1.0000
   9.000   0.8978   0.02253   0.01444   0.0148   0.0402   1.0000
   9.250   0.9114   0.02324   0.01522   0.0170   0.0390   1.0000
   9.500   0.9241   0.02401   0.01604   0.0192   0.0380   1.0000
   9.750   0.9362   0.02482   0.01690   0.0215   0.0369   1.0000
  10.000   0.9465   0.02568   0.01779   0.0239   0.0359   1.0000
  10.250   0.9543   0.02675   0.01886   0.0266   0.0349   1.0000
  10.500   0.9637   0.02777   0.01996   0.0291   0.0340   1.0000
  10.750   0.9743   0.02868   0.02100   0.0313   0.0333   1.0000
  11.000   0.9844   0.02970   0.02213   0.0334   0.0324   1.0000
  11.250   0.9936   0.03075   0.02329   0.0354   0.0314   1.0000
  11.500   1.0025   0.03188   0.02451   0.0373   0.0305   1.0000
  11.750   1.0104   0.03305   0.02575   0.0390   0.0296   1.0000
  12.000   1.0180   0.03431   0.02705   0.0406   0.0289   1.0000
  12.250   1.0255   0.03590   0.02868   0.0420   0.0282   1.0000
  12.500   1.0307   0.03763   0.03055   0.0433   0.0276   1.0000
  12.750   1.0341   0.03937   0.03250   0.0446   0.0270   1.0000
  13.000   1.0356   0.04131   0.03464   0.0456   0.0262   1.0000
  13.250   1.0365   0.04344   0.03694   0.0464   0.0255   1.0000
  13.500   1.0364   0.04573   0.03938   0.0468   0.0250   1.0000
  13.750   1.0357   0.04813   0.04193   0.0469   0.0244   1.0000
  14.000   1.0337   0.05085   0.04478   0.0468   0.0240   1.0000
  14.250   1.0314   0.05367   0.04772   0.0464   0.0236   1.0000
  14.500   1.0291   0.05662   0.05075   0.0457   0.0232   1.0000
  14.750   1.0242   0.06007   0.05433   0.0448   0.0230   1.0000
  15.000   1.0201   0.06349   0.05782   0.0437   0.0226   1.0000
  15.250   1.0108   0.06781   0.06228   0.0419   0.0224   1.0000
  15.500   0.9950   0.07334   0.06803   0.0392   0.0223   1.0000
  15.750   0.9747   0.08005   0.07498   0.0353   0.0221   1.0000
  16.000   0.9528   0.08751   0.08266   0.0309   0.0220   1.0000
  16.250   0.9279   0.09615   0.09149   0.0255   0.0220   1.0000
  16.500   0.8967   0.10664   0.10218   0.0190   0.0221   1.0000
  16.750   0.8556   0.12023   0.11597   0.0107   0.0222   1.0000
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