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RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RAF 30 MOD AIRFOIL (raf30md-il)
Reynolds number: 1,000,000
Max Cl/Cd: 65.38 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf30md-il-1000000-n5.txt
Download as CSV file: xf-raf30md-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 30 MOD AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -1.0078   0.05357   0.05172  -0.0215   1.0000   0.0021
 -12.500  -1.0309   0.04641   0.04439  -0.0270   1.0000   0.0021
 -12.250  -1.0552   0.04134   0.03912  -0.0282   1.0000   0.0021
 -12.000  -1.0770   0.03774   0.03531  -0.0259   1.0000   0.0021
 -11.750  -1.0922   0.03454   0.03185  -0.0225   1.0000   0.0021
 -11.500  -1.1000   0.03097   0.02795  -0.0199   1.0000   0.0022
 -11.250  -1.0969   0.02832   0.02502  -0.0179   1.0000   0.0022
 -11.000  -1.0893   0.02599   0.02242  -0.0161   1.0000   0.0023
 -10.750  -1.0760   0.02434   0.02057  -0.0147   1.0000   0.0024
 -10.500  -1.0602   0.02292   0.01894  -0.0135   1.0000   0.0024
 -10.250  -1.0424   0.02175   0.01762  -0.0125   1.0000   0.0025
 -10.000  -1.0232   0.02075   0.01649  -0.0115   1.0000   0.0026
  -9.750  -1.0041   0.01967   0.01526  -0.0105   1.0000   0.0027
  -9.500  -0.9837   0.01878   0.01425  -0.0096   1.0000   0.0028
  -9.250  -0.9626   0.01798   0.01334  -0.0088   1.0000   0.0030
  -9.000  -0.9413   0.01718   0.01243  -0.0079   1.0000   0.0031
  -8.750  -0.9195   0.01645   0.01158  -0.0071   1.0000   0.0033
  -8.500  -0.8980   0.01565   0.01066  -0.0062   1.0000   0.0034
  -8.250  -0.8757   0.01500   0.00990  -0.0054   1.0000   0.0035
  -8.000  -0.8542   0.01422   0.00900  -0.0044   1.0000   0.0036
  -7.750  -0.8331   0.01337   0.00805  -0.0033   1.0000   0.0040
  -7.500  -0.8104   0.01282   0.00741  -0.0025   1.0000   0.0043
  -7.250  -0.7874   0.01234   0.00688  -0.0016   1.0000   0.0045
  -7.000  -0.7643   0.01190   0.00638  -0.0008   1.0000   0.0049
  -6.750  -0.7411   0.01147   0.00589   0.0000   1.0000   0.0052
  -6.500  -0.7176   0.01110   0.00546   0.0008   1.0000   0.0056
  -6.250  -0.6946   0.01064   0.00494   0.0017   1.0000   0.0061
  -6.000  -0.6713   0.01026   0.00456   0.0025   1.0000   0.0071
  -5.750  -0.6478   0.00994   0.00421   0.0034   1.0000   0.0080
  -5.500  -0.6241   0.00965   0.00386   0.0042   1.0000   0.0087
  -5.250  -0.6007   0.00932   0.00351   0.0051   1.0000   0.0106
  -5.000  -0.5729   0.00904   0.00327   0.0049   0.9991   0.0135
  -4.750  -0.5410   0.00877   0.00305   0.0039   0.9966   0.0198
  -4.500  -0.5092   0.00860   0.00285   0.0029   0.9937   0.0236
  -4.250  -0.4777   0.00846   0.00270   0.0020   0.9902   0.0252
  -4.000  -0.4447   0.00833   0.00256   0.0008   0.9869   0.0259
  -3.750  -0.4136   0.00818   0.00241   0.0000   0.9817   0.0262
  -3.500  -0.3801   0.00793   0.00211  -0.0013   0.9769   0.0279
  -3.250  -0.3467   0.00772   0.00188  -0.0026   0.9694   0.0309
  -3.000  -0.3123   0.00753   0.00168  -0.0041   0.9590   0.0332
  -2.750  -0.2784   0.00737   0.00151  -0.0054   0.9423   0.0367
  -2.500  -0.2487   0.00709   0.00132  -0.0058   0.9163   0.0738
  -2.250  -0.2228   0.00690   0.00117  -0.0054   0.8844   0.1101
  -1.500  -0.1488   0.00631   0.00081  -0.0035   0.8008   0.2631
  -1.250  -0.1240   0.00605   0.00072  -0.0029   0.7800   0.3330
  -1.000  -0.0984   0.00589   0.00066  -0.0025   0.7597   0.3792
  -0.750  -0.0729   0.00574   0.00060  -0.0021   0.7398   0.4310
  -0.500  -0.0484   0.00550   0.00056  -0.0015   0.7147   0.5100
  -0.250  -0.0243   0.00544   0.00054  -0.0007   0.6682   0.5686
   0.000   0.0001   0.00545   0.00053   0.0000   0.6171   0.6154
   0.250   0.0243   0.00542   0.00054   0.0007   0.5701   0.6703
   0.500   0.0484   0.00550   0.00056   0.0015   0.5087   0.7150
   0.750   0.0730   0.00573   0.00060   0.0021   0.4323   0.7396
   1.000   0.0985   0.00589   0.00066   0.0025   0.3798   0.7599
   1.250   0.1241   0.00606   0.00072   0.0029   0.3314   0.7800
   1.500   0.1490   0.00629   0.00081   0.0034   0.2661   0.8008
   1.750   0.1735   0.00656   0.00091   0.0040   0.1984   0.8248
   2.000   0.1980   0.00676   0.00103   0.0047   0.1463   0.8531
   2.250   0.2228   0.00691   0.00117   0.0054   0.1088   0.8842
   2.500   0.2488   0.00709   0.00132   0.0058   0.0737   0.9161
   2.750   0.2784   0.00737   0.00151   0.0054   0.0367   0.9421
   3.000   0.3123   0.00753   0.00169   0.0041   0.0330   0.9590
   3.250   0.3466   0.00771   0.00188   0.0026   0.0310   0.9694
   3.500   0.3798   0.00793   0.00211   0.0014   0.0280   0.9768
   3.750   0.4134   0.00818   0.00240   0.0001   0.0261   0.9816
   4.000   0.4445   0.00833   0.00256  -0.0007   0.0259   0.9868
   4.250   0.4775   0.00845   0.00269  -0.0019   0.0252   0.9901
   4.500   0.5090   0.00860   0.00285  -0.0028   0.0236   0.9936
   4.750   0.5408   0.00877   0.00304  -0.0038   0.0196   0.9965
   5.000   0.5726   0.00904   0.00327  -0.0048   0.0135   0.9989
   5.250   0.6009   0.00933   0.00351  -0.0051   0.0106   1.0000
   5.500   0.6243   0.00965   0.00385  -0.0042   0.0087   1.0000
   5.750   0.6480   0.00994   0.00421  -0.0034   0.0079   1.0000
   6.000   0.6715   0.01027   0.00456  -0.0026   0.0072   1.0000
   6.250   0.6948   0.01064   0.00495  -0.0017   0.0063   1.0000
   6.500   0.7177   0.01110   0.00546  -0.0008   0.0056   1.0000
   6.750   0.7411   0.01148   0.00590   0.0000   0.0052   1.0000
   7.000   0.7643   0.01192   0.00640   0.0008   0.0049   1.0000
   7.250   0.7874   0.01236   0.00690   0.0017   0.0046   1.0000
   7.500   0.8104   0.01284   0.00743   0.0025   0.0043   1.0000
   7.750   0.8331   0.01338   0.00806   0.0033   0.0040   1.0000
   8.000   0.8546   0.01414   0.00892   0.0043   0.0037   1.0000
   8.250   0.8754   0.01503   0.00994   0.0054   0.0036   1.0000
   8.500   0.8977   0.01569   0.01070   0.0062   0.0034   1.0000
   8.750   0.9194   0.01644   0.01157   0.0071   0.0033   1.0000
   9.000   0.9410   0.01720   0.01244   0.0080   0.0031   1.0000
   9.250   0.9622   0.01802   0.01339   0.0089   0.0030   1.0000
   9.500   0.9834   0.01881   0.01429   0.0097   0.0028   1.0000
   9.750   1.0033   0.01979   0.01540   0.0106   0.0027   1.0000
  10.000   1.0234   0.02069   0.01642   0.0115   0.0026   1.0000
  10.250   1.0415   0.02188   0.01777   0.0126   0.0025   1.0000
  10.500   1.0591   0.02307   0.01911   0.0137   0.0024   1.0000
  10.750   1.0758   0.02433   0.02056   0.0148   0.0024   1.0000
  11.000   1.0890   0.02601   0.02245   0.0162   0.0023   1.0000
  11.250   1.0985   0.02805   0.02472   0.0178   0.0022   1.0000
  11.500   1.0991   0.03105   0.02804   0.0200   0.0022   1.0000
  11.750   1.0935   0.03436   0.03166   0.0225   0.0021   1.0000
  12.000   1.0809   0.03741   0.03495   0.0256   0.0021   1.0000
  12.250   1.0606   0.04083   0.03857   0.0282   0.0021   1.0000
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