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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.4 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe488-il-1000000-n5.txt
Download as CSV file: xf-goe488-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 488 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4962   0.11305   0.11135  -0.0183   1.0000   0.0067
 -11.250  -0.5109   0.10530   0.10360  -0.0214   1.0000   0.0077
 -10.250  -0.7818   0.02028   0.01688  -0.0710   0.9886   0.0077
 -10.000  -0.7572   0.01809   0.01443  -0.0719   0.9869   0.0088
  -9.750  -0.7326   0.01649   0.01262  -0.0722   0.9846   0.0099
  -9.500  -0.7069   0.01544   0.01140  -0.0724   0.9819   0.0114
  -9.250  -0.6767   0.01529   0.01131  -0.0730   0.9803   0.0134
  -9.000  -0.6463   0.01498   0.01095  -0.0738   0.9788   0.0151
  -8.750  -0.6135   0.01528   0.01133  -0.0748   0.9777   0.0161
  -8.500  -0.5812   0.01574   0.01189  -0.0755   0.9762   0.0170
  -8.250  -0.5523   0.01586   0.01202  -0.0757   0.9729   0.0178
  -8.000  -0.5221   0.01585   0.01199  -0.0763   0.9705   0.0188
  -7.750  -0.4911   0.01572   0.01182  -0.0770   0.9685   0.0197
  -7.500  -0.4611   0.01555   0.01161  -0.0776   0.9659   0.0205
  -7.250  -0.4331   0.01530   0.01129  -0.0778   0.9618   0.0210
  -7.000  -0.4026   0.01523   0.01117  -0.0783   0.9586   0.0214
  -6.750  -0.3730   0.01520   0.01111  -0.0788   0.9544   0.0217
  -6.500  -0.3438   0.01514   0.01101  -0.0790   0.9482   0.0219
  -6.250  -0.3209   0.01329   0.00884  -0.0787   0.9397   0.0231
  -6.000  -0.2939   0.01278   0.00824  -0.0787   0.9309   0.0237
  -5.750  -0.2672   0.01248   0.00786  -0.0784   0.9230   0.0242
  -5.500  -0.2408   0.01212   0.00742  -0.0782   0.9147   0.0246
  -5.250  -0.2146   0.01167   0.00686  -0.0778   0.9062   0.0250
  -5.000  -0.1888   0.01120   0.00629  -0.0774   0.8972   0.0252
  -4.750  -0.1627   0.01076   0.00574  -0.0770   0.8897   0.0254
  -4.500  -0.1369   0.01030   0.00518  -0.0765   0.8811   0.0256
  -4.250  -0.1110   0.00987   0.00465  -0.0761   0.8723   0.0258
  -3.750  -0.0591   0.00912   0.00373  -0.0751   0.8544   0.0260
  -3.500  -0.0329   0.00883   0.00336  -0.0747   0.8474   0.0262
  -3.250  -0.0064   0.00858   0.00307  -0.0743   0.8403   0.0265
  -3.000   0.0197   0.00829   0.00270  -0.0738   0.8327   0.0266
  -2.750   0.0458   0.00803   0.00237  -0.0733   0.8234   0.0267
  -2.500   0.0720   0.00781   0.00209  -0.0729   0.8144   0.0268
  -2.250   0.0981   0.00763   0.00185  -0.0724   0.8047   0.0270
  -2.000   0.1246   0.00747   0.00164  -0.0720   0.7941   0.0273
  -1.750   0.1508   0.00734   0.00146  -0.0715   0.7817   0.0278
  -1.500   0.1768   0.00725   0.00131  -0.0710   0.7648   0.0285
  -1.250   0.2022   0.00722   0.00119  -0.0703   0.7390   0.0295
  -1.000   0.2263   0.00729   0.00110  -0.0694   0.6964   0.0303
  -0.750   0.2497   0.00744   0.00105  -0.0684   0.6475   0.0309
  -0.500   0.2739   0.00759   0.00105  -0.0675   0.6078   0.0312
  -0.250   0.2985   0.00768   0.00100  -0.0668   0.5712   0.0323
   0.000   0.3221   0.00788   0.00097  -0.0659   0.5130   0.0338
   0.250   0.3448   0.00818   0.00100  -0.0649   0.4393   0.0359
   0.500   0.3686   0.00843   0.00105  -0.0641   0.3865   0.0384
   0.750   0.3934   0.00859   0.00109  -0.0635   0.3513   0.0421
   1.000   0.4187   0.00867   0.00113  -0.0630   0.3282   0.0600
   1.250   0.4441   0.00864   0.00118  -0.0625   0.3129   0.1113
   1.500   0.4696   0.00860   0.00125  -0.0620   0.3012   0.1702
   1.750   0.4951   0.00852   0.00133  -0.0616   0.2910   0.2468
   2.000   0.5206   0.00843   0.00141  -0.0612   0.2818   0.3206
   2.250   0.5283   0.00699   0.00156  -0.0570   0.2739   0.9189
   2.500   0.5774   0.00708   0.00168  -0.0617   0.2623   0.9742
   2.750   0.6252   0.00724   0.00178  -0.0663   0.2499   0.9920
   3.000   0.6613   0.00741   0.00187  -0.0682   0.2360   0.9982
   3.250   0.6902   0.00772   0.00200  -0.0686   0.1989   1.0000
   3.500   0.7105   0.00812   0.00220  -0.0672   0.1574   1.0000
   3.750   0.7329   0.00838   0.00236  -0.0660   0.1384   1.0000
   4.000   0.7552   0.00865   0.00254  -0.0649   0.1190   1.0000
   4.250   0.7771   0.00898   0.00275  -0.0638   0.0965   1.0000
   4.500   0.7974   0.00949   0.00304  -0.0623   0.0561   1.0000
   4.750   0.8207   0.00973   0.00325  -0.0614   0.0477   1.0000
   5.000   0.8441   0.00995   0.00345  -0.0605   0.0412   1.0000
   5.250   0.8654   0.01041   0.00377  -0.0593   0.0193   1.0000
   5.500   0.8889   0.01066   0.00402  -0.0584   0.0139   1.0000
   5.750   0.9123   0.01094   0.00432  -0.0575   0.0119   1.0000
   6.000   0.9354   0.01125   0.00465  -0.0566   0.0101   1.0000
   6.250   0.9588   0.01154   0.00498  -0.0557   0.0092   1.0000
   6.500   0.9823   0.01182   0.00529  -0.0549   0.0086   1.0000
   6.750   1.0056   0.01213   0.00562  -0.0540   0.0080   1.0000
   7.000   1.0286   0.01245   0.00596  -0.0532   0.0073   1.0000
   7.250   1.0511   0.01285   0.00638  -0.0522   0.0067   1.0000
   7.500   1.0728   0.01334   0.00693  -0.0512   0.0062   1.0000
   7.750   1.0955   0.01370   0.00733  -0.0503   0.0059   1.0000
   8.000   1.1177   0.01412   0.00779  -0.0493   0.0057   1.0000
   8.250   1.1395   0.01457   0.00828  -0.0483   0.0054   1.0000
   8.500   1.1611   0.01501   0.00876  -0.0473   0.0051   1.0000
   8.750   1.1823   0.01548   0.00928  -0.0462   0.0049   1.0000
   9.000   1.2031   0.01599   0.00984  -0.0451   0.0047   1.0000
   9.250   1.2233   0.01652   0.01042  -0.0439   0.0045   1.0000
   9.500   1.2399   0.01739   0.01136  -0.0422   0.0041   1.0000
   9.750   1.2591   0.01796   0.01199  -0.0409   0.0040   1.0000
  10.000   1.2783   0.01850   0.01259  -0.0396   0.0039   1.0000
  10.250   1.2955   0.01918   0.01336  -0.0380   0.0037   1.0000
  10.500   1.3117   0.01991   0.01416  -0.0362   0.0036   1.0000
  10.750   1.3271   0.02064   0.01498  -0.0344   0.0035   1.0000
  11.000   1.3404   0.02148   0.01590  -0.0323   0.0034   1.0000
  11.250   1.3513   0.02227   0.01680  -0.0297   0.0033   1.0000
  11.500   1.3615   0.02304   0.01765  -0.0270   0.0032   1.0000
  11.750   1.3720   0.02380   0.01848  -0.0246   0.0031   1.0000
  12.000   1.3792   0.02478   0.01956  -0.0218   0.0031   1.0000
  12.250   1.3892   0.02561   0.02044  -0.0195   0.0030   1.0000
  12.500   1.3929   0.02688   0.02183  -0.0167   0.0029   1.0000
  12.750   1.4014   0.02785   0.02288  -0.0146   0.0029   1.0000
  13.000   1.4048   0.02923   0.02436  -0.0122   0.0029   1.0000
  13.250   1.4055   0.03090   0.02614  -0.0097   0.0028   1.0000
  13.500   1.4102   0.03232   0.02764  -0.0080   0.0027   1.0000
  13.750   1.4091   0.03431   0.02975  -0.0061   0.0027   1.0000
  14.000   1.4052   0.03671   0.03228  -0.0044   0.0027   1.0000
  14.250   1.3985   0.03959   0.03531  -0.0032   0.0027   1.0000
  14.500   1.3883   0.04309   0.03897  -0.0025   0.0026   1.0000
  14.750   1.3732   0.04758   0.04363  -0.0027   0.0025   1.0000
  15.000   1.3650   0.05172   0.04791  -0.0037   0.0025   1.0000
  15.250   1.3520   0.05696   0.05331  -0.0056   0.0025   1.0000
  15.500   1.3357   0.06323   0.05973  -0.0084   0.0025   1.0000
  15.750   1.3213   0.06971   0.06637  -0.0118   0.0025   1.0000
  16.000   1.3034   0.07719   0.07400  -0.0158   0.0025   1.0000
  16.250   1.2925   0.08353   0.08046  -0.0192   0.0025   1.0000
  16.500   1.2676   0.09239   0.08947  -0.0238   0.0025   1.0000
  16.750   1.2541   0.09930   0.09649  -0.0275   0.0025   1.0000
  17.250   1.2137   0.11601   0.11342  -0.0363   0.0025   1.0000
  17.500   1.1944   0.12464   0.12217  -0.0410   0.0025   1.0000
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