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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 500,000
Max Cl/Cd: 58.48 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf30-il-500000.txt
Download as CSV file: xf-raf30-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.9595   0.10983   0.10673  -0.0170   1.0000   0.0189
 -17.250  -0.9836   0.10100   0.09777  -0.0223   1.0000   0.0191
 -17.000  -1.0172   0.09058   0.08712  -0.0288   1.0000   0.0190
 -16.750  -1.0375   0.08325   0.07962  -0.0331   1.0000   0.0190
 -16.500  -1.0562   0.07664   0.07284  -0.0368   1.0000   0.0190
 -16.250  -1.0689   0.07135   0.06744  -0.0394   1.0000   0.0192
 -16.000  -1.0752   0.06727   0.06328  -0.0414   1.0000   0.0194
 -15.750  -1.0859   0.06266   0.05853  -0.0434   1.0000   0.0195
 -15.500  -1.0906   0.05913   0.05492  -0.0449   1.0000   0.0197
 -15.250  -1.0996   0.05511   0.05075  -0.0462   1.0000   0.0198
 -15.000  -1.1016   0.05223   0.04779  -0.0472   1.0000   0.0202
 -14.750  -1.1064   0.04905   0.04447  -0.0478   1.0000   0.0203
 -14.500  -1.1062   0.04665   0.04198  -0.0481   1.0000   0.0207
 -14.250  -1.1069   0.04428   0.03950  -0.0481   1.0000   0.0211
 -14.000  -1.1084   0.04193   0.03700  -0.0478   1.0000   0.0216
 -13.750  -1.1096   0.03982   0.03473  -0.0472   1.0000   0.0220
 -13.500  -1.1098   0.03766   0.03240  -0.0461   1.0000   0.0223
 -13.250  -1.1090   0.03617   0.03074  -0.0448   1.0000   0.0226
 -13.000  -1.1077   0.03382   0.02822  -0.0432   1.0000   0.0231
 -12.750  -1.0993   0.03207   0.02643  -0.0419   1.0000   0.0236
 -12.500  -1.0910   0.03084   0.02517  -0.0404   1.0000   0.0241
 -12.250  -1.0826   0.02970   0.02397  -0.0387   1.0000   0.0245
 -12.000  -1.0745   0.02878   0.02298  -0.0367   1.0000   0.0252
 -11.750  -1.0651   0.02773   0.02184  -0.0347   1.0000   0.0258
 -11.500  -1.0563   0.02701   0.02103  -0.0323   1.0000   0.0265
 -11.250  -1.0481   0.02637   0.02027  -0.0296   1.0000   0.0272
 -11.000  -1.0399   0.02581   0.01960  -0.0266   1.0000   0.0276
 -10.750  -1.0272   0.02386   0.01760  -0.0249   1.0000   0.0285
 -10.500  -1.0168   0.02292   0.01666  -0.0224   1.0000   0.0292
 -10.250  -1.0040   0.02218   0.01590  -0.0202   1.0000   0.0299
 -10.000  -0.9903   0.02148   0.01515  -0.0181   1.0000   0.0307
  -9.750  -0.9757   0.02085   0.01447  -0.0160   1.0000   0.0317
  -9.500  -0.9602   0.02029   0.01385  -0.0141   1.0000   0.0325
  -9.250  -0.9439   0.01979   0.01328  -0.0121   1.0000   0.0332
  -9.000  -0.9324   0.01877   0.01220  -0.0095   1.0000   0.0340
  -8.750  -0.9215   0.01784   0.01126  -0.0068   1.0000   0.0350
  -8.500  -0.9073   0.01722   0.01063  -0.0045   1.0000   0.0361
  -8.250  -0.8918   0.01670   0.01009  -0.0023   1.0000   0.0372
  -8.000  -0.8764   0.01618   0.00954  -0.0001   1.0000   0.0382
  -7.750  -0.8606   0.01572   0.00902   0.0020   1.0000   0.0391
  -7.500  -0.8444   0.01531   0.00857   0.0042   1.0000   0.0399
  -7.250  -0.8321   0.01468   0.00791   0.0069   1.0000   0.0413
  -7.000  -0.8192   0.01415   0.00738   0.0096   1.0000   0.0429
  -6.750  -0.8053   0.01377   0.00698   0.0121   1.0000   0.0445
  -6.500  -0.7758   0.01336   0.00654   0.0114   0.9980   0.0465
  -6.250  -0.7389   0.01290   0.00606   0.0092   0.9946   0.0498
  -6.000  -0.7041   0.01239   0.00558   0.0074   0.9905   0.0562
  -5.750  -0.6702   0.01168   0.00508   0.0057   0.9858   0.0855
  -5.500  -0.6354   0.01100   0.00466   0.0038   0.9820   0.1320
  -5.250  -0.6044   0.01040   0.00427   0.0027   0.9752   0.1731
  -5.000  -0.5696   0.00978   0.00393   0.0008   0.9710   0.2286
  -4.750  -0.5387   0.00932   0.00365  -0.0001   0.9634   0.2737
  -4.250  -0.4696   0.00852   0.00315  -0.0032   0.9504   0.3513
  -4.000  -0.4343   0.00814   0.00293  -0.0049   0.9428   0.3932
  -3.750  -0.4019   0.00779   0.00274  -0.0060   0.9321   0.4354
  -3.500  -0.3683   0.00754   0.00258  -0.0072   0.9211   0.4708
  -3.250  -0.3367   0.00734   0.00244  -0.0079   0.9083   0.5028
  -3.000  -0.3083   0.00721   0.00234  -0.0079   0.8937   0.5297
  -2.750  -0.2819   0.00712   0.00228  -0.0074   0.8786   0.5555
  -2.500  -0.2563   0.00705   0.00222  -0.0067   0.8636   0.5781
  -2.250  -0.2306   0.00701   0.00216  -0.0060   0.8475   0.5953
  -2.000  -0.2053   0.00698   0.00210  -0.0053   0.8308   0.6114
  -1.750  -0.1804   0.00696   0.00206  -0.0044   0.8154   0.6309
  -1.500  -0.1553   0.00693   0.00204  -0.0036   0.8017   0.6498
  -1.250  -0.1298   0.00691   0.00201  -0.0029   0.7888   0.6653
  -1.000  -0.1040   0.00689   0.00199  -0.0023   0.7763   0.6780
  -0.750  -0.0780   0.00688   0.00196  -0.0017   0.7636   0.6898
  -0.500  -0.0521   0.00687   0.00195  -0.0011   0.7509   0.7021
  -0.250  -0.0260   0.00687   0.00194  -0.0006   0.7387   0.7146
   0.000   0.0000   0.00686   0.00194   0.0000   0.7266   0.7265
   0.250   0.0260   0.00687   0.00194   0.0006   0.7146   0.7386
   0.500   0.0520   0.00687   0.00195   0.0011   0.7021   0.7509
   0.750   0.0780   0.00688   0.00196   0.0017   0.6899   0.7637
   1.000   0.1040   0.00689   0.00199   0.0023   0.6780   0.7763
   1.250   0.1298   0.00691   0.00201   0.0029   0.6653   0.7889
   1.500   0.1553   0.00693   0.00204   0.0036   0.6496   0.8017
   1.750   0.1804   0.00696   0.00206   0.0044   0.6311   0.8153
   2.000   0.2053   0.00698   0.00210   0.0053   0.6111   0.8309
   2.250   0.2306   0.00701   0.00216   0.0060   0.5953   0.8476
   2.500   0.2563   0.00705   0.00222   0.0067   0.5784   0.8636
   2.750   0.2818   0.00712   0.00227   0.0074   0.5552   0.8786
   3.000   0.3083   0.00721   0.00234   0.0079   0.5300   0.8937
   3.250   0.3366   0.00735   0.00244   0.0079   0.5021   0.9083
   3.500   0.3683   0.00754   0.00257   0.0072   0.4704   0.9211
   3.750   0.4020   0.00779   0.00274   0.0060   0.4359   0.9321
   4.000   0.4344   0.00814   0.00293   0.0049   0.3930   0.9428
   4.250   0.4696   0.00852   0.00315   0.0032   0.3511   0.9506
   4.500   0.5032   0.00891   0.00339   0.0019   0.3146   0.9582
   4.750   0.5387   0.00932   0.00365   0.0001   0.2730   0.9634
   5.000   0.5696   0.00978   0.00393  -0.0008   0.2285   0.9710
   5.250   0.6044   0.01041   0.00427  -0.0027   0.1720   0.9752
   5.500   0.6354   0.01101   0.00466  -0.0038   0.1314   0.9821
   5.750   0.6702   0.01170   0.00509  -0.0057   0.0835   0.9859
   6.000   0.7042   0.01239   0.00558  -0.0074   0.0561   0.9905
   6.250   0.7391   0.01290   0.00605  -0.0092   0.0499   0.9946
   6.500   0.7759   0.01336   0.00654  -0.0114   0.0465   0.9981
   6.750   0.8053   0.01377   0.00697  -0.0121   0.0445   1.0000
   7.000   0.8191   0.01415   0.00738  -0.0096   0.0430   1.0000
   7.250   0.8320   0.01468   0.00791  -0.0069   0.0413   1.0000
   7.500   0.8444   0.01531   0.00857  -0.0041   0.0399   1.0000
   7.750   0.8606   0.01572   0.00902  -0.0020   0.0392   1.0000
   8.000   0.8763   0.01619   0.00955   0.0002   0.0382   1.0000
   8.250   0.8921   0.01667   0.01006   0.0023   0.0371   1.0000
   8.500   0.9073   0.01721   0.01062   0.0045   0.0361   1.0000
   8.750   0.9215   0.01784   0.01126   0.0068   0.0350   1.0000
   9.000   0.9321   0.01880   0.01223   0.0096   0.0340   1.0000
   9.250   0.9441   0.01976   0.01326   0.0121   0.0332   1.0000
   9.500   0.9601   0.02031   0.01387   0.0141   0.0326   1.0000
   9.750   0.9757   0.02086   0.01448   0.0160   0.0317   1.0000
  10.000   0.9904   0.02150   0.01517   0.0181   0.0308   1.0000
  10.250   1.0044   0.02216   0.01587   0.0202   0.0299   1.0000
  10.500   1.0171   0.02291   0.01665   0.0224   0.0292   1.0000
  10.750   1.0274   0.02388   0.01762   0.0249   0.0285   1.0000
  11.000   1.0401   0.02579   0.01958   0.0266   0.0276   1.0000
  11.250   1.0479   0.02629   0.02020   0.0296   0.0271   1.0000
  11.500   1.0565   0.02696   0.02098   0.0323   0.0265   1.0000
  11.750   1.0658   0.02781   0.02193   0.0346   0.0258   1.0000
  12.000   1.0751   0.02880   0.02300   0.0366   0.0253   1.0000
  12.250   1.0834   0.02975   0.02402   0.0386   0.0247   1.0000
  12.500   1.0916   0.03088   0.02522   0.0403   0.0241   1.0000
  12.750   1.0999   0.03206   0.02642   0.0418   0.0236   1.0000
  13.000   1.1084   0.03381   0.02820   0.0431   0.0231   1.0000
  13.250   1.1095   0.03606   0.03063   0.0447   0.0226   1.0000
  13.500   1.1105   0.03771   0.03245   0.0460   0.0223   1.0000
  13.750   1.1104   0.03970   0.03461   0.0470   0.0219   1.0000
  14.000   1.1108   0.04157   0.03661   0.0476   0.0213   1.0000
  14.250   1.1087   0.04415   0.03936   0.0480   0.0211   1.0000
  14.500   1.1102   0.04622   0.04151   0.0478   0.0205   1.0000
  14.750   1.1084   0.04893   0.04434   0.0476   0.0203   1.0000
  15.000   1.1036   0.05212   0.04766   0.0470   0.0201   1.0000
  15.250   1.1033   0.05477   0.05038   0.0460   0.0197   1.0000
  15.500   1.0931   0.05897   0.05475   0.0447   0.0197   1.0000
  15.750   1.0872   0.06269   0.05857   0.0432   0.0195   1.0000
  16.000   1.0834   0.06625   0.06218   0.0416   0.0192   1.0000
  16.250   1.0685   0.07168   0.06779   0.0390   0.0192   1.0000
  16.500   1.0593   0.07640   0.07260   0.0367   0.0190   1.0000
  16.750   1.0415   0.08277   0.07911   0.0333   0.0188   1.0000
  17.000   1.0212   0.09010   0.08661   0.0289   0.0189   1.0000
  17.250   0.9964   0.09865   0.09534   0.0237   0.0189   1.0000
  17.500   0.9577   0.11072   0.10765   0.0160   0.0190   1.0000
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