Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.69 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15-il-1000000-n5.txt
Download as CSV file: xf-rg15-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-15 8.9%                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8583   0.03412   0.03188  -0.0532   1.0000   0.0028
 -10.500  -0.8622   0.03065   0.02812  -0.0514   1.0000   0.0028
 -10.250  -0.8610   0.02756   0.02474  -0.0495   1.0000   0.0028
 -10.000  -0.8528   0.02530   0.02222  -0.0478   1.0000   0.0029
  -9.750  -0.8373   0.02345   0.02013  -0.0470   0.9997   0.0030
  -9.500  -0.8121   0.02139   0.01778  -0.0482   0.9983   0.0031
  -9.250  -0.7855   0.01965   0.01579  -0.0493   0.9968   0.0032
  -9.000  -0.7572   0.01838   0.01433  -0.0504   0.9955   0.0033
  -8.750  -0.7281   0.01706   0.01281  -0.0516   0.9943   0.0034
  -8.500  -0.7011   0.01604   0.01162  -0.0521   0.9926   0.0035
  -8.250  -0.6732   0.01510   0.01054  -0.0526   0.9906   0.0036
  -8.000  -0.6443   0.01424   0.00954  -0.0533   0.9886   0.0037
  -7.750  -0.6143   0.01354   0.00871  -0.0542   0.9869   0.0038
  -7.500  -0.5834   0.01291   0.00798  -0.0552   0.9853   0.0040
  -7.250  -0.5514   0.01244   0.00743  -0.0564   0.9840   0.0041
  -7.000  -0.5198   0.01148   0.00633  -0.0576   0.9827   0.0047
  -6.750  -0.4950   0.01098   0.00578  -0.0571   0.9783   0.0051
  -6.500  -0.4651   0.01057   0.00532  -0.0577   0.9752   0.0055
  -6.250  -0.4337   0.01018   0.00489  -0.0586   0.9728   0.0061
  -6.000  -0.4013   0.00982   0.00448  -0.0597   0.9708   0.0067
  -5.750  -0.3732   0.00944   0.00407  -0.0598   0.9663   0.0077
  -5.500  -0.3439   0.00915   0.00379  -0.0602   0.9610   0.0090
  -5.250  -0.3110   0.00889   0.00350  -0.0614   0.9571   0.0103
  -5.000  -0.2808   0.00871   0.00327  -0.0619   0.9503   0.0110
  -4.750  -0.2479   0.00836   0.00291  -0.0631   0.9438   0.0134
  -4.500  -0.2167   0.00813   0.00266  -0.0639   0.9345   0.0150
  -4.250  -0.1857   0.00793   0.00240  -0.0645   0.9235   0.0161
  -4.000  -0.1561   0.00777   0.00219  -0.0649   0.9102   0.0171
  -3.750  -0.1281   0.00757   0.00192  -0.0648   0.8949   0.0211
  -3.500  -0.1007   0.00744   0.00173  -0.0647   0.8782   0.0252
  -3.250  -0.0740   0.00726   0.00156  -0.0644   0.8608   0.0400
  -3.000  -0.0475   0.00713   0.00142  -0.0641   0.8429   0.0572
  -2.750  -0.0210   0.00701   0.00129  -0.0638   0.8239   0.0761
  -2.500   0.0052   0.00689   0.00117  -0.0635   0.8047   0.1017
  -2.250   0.0316   0.00677   0.00107  -0.0632   0.7853   0.1304
  -2.000   0.0578   0.00663   0.00098  -0.0629   0.7655   0.1697
  -1.750   0.0835   0.00635   0.00090  -0.0627   0.7460   0.2508
  -1.500   0.1096   0.00614   0.00082  -0.0625   0.7258   0.3207
  -1.000   0.1620   0.00583   0.00073  -0.0620   0.6844   0.4468
  -0.750   0.1876   0.00557   0.00070  -0.0617   0.6634   0.5480
  -0.500   0.2140   0.00550   0.00072  -0.0614   0.6416   0.6065
  -0.250   0.2407   0.00553   0.00074  -0.0612   0.6202   0.6387
   0.000   0.2676   0.00557   0.00076  -0.0609   0.5983   0.6629
   0.250   0.2944   0.00564   0.00079  -0.0607   0.5759   0.6826
   0.500   0.3212   0.00572   0.00083  -0.0605   0.5537   0.6997
   0.750   0.3481   0.00581   0.00087  -0.0602   0.5311   0.7144
   1.000   0.3749   0.00592   0.00093  -0.0600   0.5082   0.7282
   1.250   0.4016   0.00602   0.00098  -0.0598   0.4838   0.7416
   1.500   0.4282   0.00615   0.00105  -0.0595   0.4586   0.7556
   1.750   0.4548   0.00627   0.00113  -0.0592   0.4343   0.7695
   2.000   0.4812   0.00641   0.00122  -0.0590   0.4100   0.7840
   2.250   0.5075   0.00655   0.00132  -0.0586   0.3846   0.7999
   2.500   0.5337   0.00669   0.00142  -0.0583   0.3598   0.8152
   2.750   0.5596   0.00687   0.00153  -0.0580   0.3331   0.8281
   3.000   0.5854   0.00707   0.00167  -0.0576   0.3048   0.8399
   3.250   0.6114   0.00723   0.00179  -0.0572   0.2837   0.8522
   3.500   0.6368   0.00743   0.00194  -0.0568   0.2582   0.8657
   3.750   0.6621   0.00760   0.00209  -0.0563   0.2370   0.8810
   4.000   0.6865   0.00783   0.00225  -0.0556   0.2107   0.8991
   4.250   0.7095   0.00808   0.00245  -0.0546   0.1810   0.9209
   4.500   0.7332   0.00829   0.00263  -0.0537   0.1580   0.9521
   4.750   0.7654   0.00863   0.00286  -0.0549   0.1285   1.0000
   5.000   0.7905   0.00900   0.00310  -0.0546   0.1036   1.0000
   5.250   0.8153   0.00938   0.00337  -0.0541   0.0806   1.0000
   5.500   0.8406   0.00972   0.00365  -0.0538   0.0642   1.0000
   5.750   0.8661   0.01003   0.00391  -0.0535   0.0533   1.0000
   6.000   0.8909   0.01041   0.00422  -0.0530   0.0395   1.0000
   6.250   0.9158   0.01078   0.00454  -0.0526   0.0296   1.0000
   6.500   0.9406   0.01115   0.00486  -0.0522   0.0215   1.0000
   6.750   0.9649   0.01157   0.00526  -0.0517   0.0139   1.0000
   7.000   0.9887   0.01204   0.00569  -0.0511   0.0078   1.0000
   7.250   1.0130   0.01246   0.00611  -0.0506   0.0056   1.0000
   7.500   1.0372   0.01288   0.00657  -0.0500   0.0045   1.0000
   7.750   1.0616   0.01327   0.00700  -0.0495   0.0042   1.0000
   8.000   1.0856   0.01368   0.00747  -0.0489   0.0040   1.0000
   8.250   1.1091   0.01414   0.00800  -0.0483   0.0038   1.0000
   8.500   1.1323   0.01462   0.00854  -0.0477   0.0036   1.0000
   8.750   1.1550   0.01515   0.00913  -0.0469   0.0033   1.0000
   9.000   1.1773   0.01569   0.00972  -0.0462   0.0031   1.0000
   9.250   1.1987   0.01632   0.01042  -0.0453   0.0029   1.0000
   9.500   1.2189   0.01707   0.01125  -0.0442   0.0026   1.0000
   9.750   1.2372   0.01799   0.01229  -0.0428   0.0024   1.0000
  10.000   1.2533   0.01911   0.01356  -0.0411   0.0023   1.0000
  10.250   1.2726   0.01981   0.01435  -0.0400   0.0023   1.0000
  10.500   1.2907   0.02059   0.01522  -0.0388   0.0023   1.0000
  10.750   1.3080   0.02140   0.01612  -0.0374   0.0022   1.0000
  11.000   1.3239   0.02229   0.01711  -0.0358   0.0022   1.0000
  11.250   1.3382   0.02323   0.01817  -0.0341   0.0021   1.0000
  11.500   1.3510   0.02420   0.01924  -0.0322   0.0021   1.0000
  11.750   1.3589   0.02524   0.02040  -0.0294   0.0021   1.0000
  12.000   1.3636   0.02644   0.02173  -0.0263   0.0020   1.0000
  12.250   1.3718   0.02742   0.02280  -0.0240   0.0019   1.0000
  12.500   1.3755   0.02873   0.02424  -0.0213   0.0019   1.0000
  12.750   1.3754   0.03038   0.02603  -0.0185   0.0019   1.0000
  13.000   1.3792   0.03182   0.02760  -0.0165   0.0018   1.0000
  13.250   1.3770   0.03386   0.02978  -0.0144   0.0018   1.0000
  13.500   1.3727   0.03626   0.03233  -0.0128   0.0018   1.0000
  13.750   1.3710   0.03862   0.03482  -0.0118   0.0017   1.0000
  14.000   1.3613   0.04208   0.03844  -0.0112   0.0017   1.0000
  14.250   1.3615   0.04472   0.04118  -0.0113   0.0016   1.0000
  14.500   1.3416   0.05020   0.04688  -0.0125   0.0017   1.0000
  14.750   1.3385   0.05391   0.05069  -0.0138   0.0016   1.0000
  15.000   1.3229   0.05984   0.05679  -0.0165   0.0017   1.0000
  15.250   1.3071   0.06634   0.06345  -0.0199   0.0017   1.0000
  15.500   1.2893   0.07367   0.07093  -0.0241   0.0016   1.0000
  15.750   1.2685   0.08208   0.07950  -0.0290   0.0016   1.0000
  16.000   1.2374   0.09304   0.09064  -0.0354   0.0017   1.0000
  16.250   1.2091   0.10398   0.10174  -0.0418   0.0017   1.0000
  16.500   1.1907   0.11305   0.11092  -0.0470   0.0017   1.0000
  16.750   1.1599   0.12537   0.12338  -0.0541   0.0017   1.0000
  17.000   1.1353   0.13656   0.13468  -0.0605   0.0018   1.0000
  17.250   1.1094   0.14858   0.14680  -0.0674   0.0018   1.0000
  17.500   1.0813   0.16176   0.16009  -0.0750   0.0019   1.0000
  17.750   1.0575   0.17450   0.17293  -0.0822   0.0019   1.0000
<< Back to RG-15 8.9% (rg15-il)

Polar data table (+)

Polar graphs


<< Back to RG-15 8.9% (rg15-il)