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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 200,000
Max Cl/Cd: 74.48 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe188-il-200000-n5.txt
Download as CSV file: xf-goe188-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3163   0.09139   0.08820  -0.0256   1.0000   0.0124
  -7.250  -0.3155   0.08884   0.08572  -0.0268   1.0000   0.0126
  -7.000  -0.3121   0.08607   0.08302  -0.0289   1.0000   0.0127
  -6.750  -0.2961   0.08240   0.07937  -0.0348   0.9923   0.0130
  -6.500  -0.2671   0.07791   0.07482  -0.0435   0.9722   0.0132
  -6.250  -0.2380   0.07351   0.07035  -0.0507   0.9494   0.0134
  -6.000  -0.2079   0.06910   0.06583  -0.0571   0.9287   0.0135
  -5.750  -0.1786   0.06485   0.06144  -0.0624   0.9099   0.0136
  -5.500  -0.1519   0.06094   0.05736  -0.0664   0.8917   0.0137
  -5.250  -0.1271   0.05731   0.05354  -0.0692   0.8750   0.0137
  -5.000  -0.1035   0.05392   0.04994  -0.0712   0.8603   0.0137
  -4.750  -0.0800   0.05070   0.04651  -0.0727   0.8476   0.0138
  -4.500  -0.0626   0.04467   0.04030  -0.0748   0.8368   0.0144
  -4.250  -0.0425   0.04095   0.03641  -0.0758   0.8255   0.0150
  -4.000  -0.0205   0.03803   0.03328  -0.0765   0.8131   0.0156
  -3.750   0.0029   0.03545   0.03048  -0.0771   0.7995   0.0165
  -3.500   0.0278   0.03311   0.02789  -0.0775   0.7857   0.0183
  -3.250   0.0549   0.03088   0.02536  -0.0777   0.7728   0.0206
  -3.000   0.0844   0.02900   0.02313  -0.0775   0.7618   0.0232
  -2.750   0.1171   0.02908   0.02266  -0.0766   0.7526   0.0251
  -2.500   0.1413   0.02473   0.01815  -0.0774   0.7441   0.0271
  -2.250   0.1682   0.02300   0.01622  -0.0776   0.7356   0.0299
  -1.750   0.2276   0.01988   0.01245  -0.0766   0.7187   0.0218
  -1.500   0.2574   0.01824   0.01046  -0.0760   0.7109   0.0169
  -1.250   0.2872   0.01743   0.00933  -0.0753   0.7020   0.0146
  -1.000   0.3152   0.01613   0.00783  -0.0751   0.6939   0.0157
  -0.750   0.3430   0.01523   0.00680  -0.0749   0.6850   0.0173
  -0.500   0.3710   0.01442   0.00586  -0.0745   0.6760   0.0169
  -0.250   0.3985   0.01373   0.00507  -0.0741   0.6675   0.0171
   0.000   0.4261   0.01315   0.00445  -0.0739   0.6582   0.0178
   0.250   0.4537   0.01277   0.00399  -0.0738   0.6487   0.0212
   0.500   0.4815   0.01250   0.00354  -0.0737   0.6389   0.0231
   0.750   0.5094   0.01233   0.00322  -0.0736   0.6280   0.0257
   1.000   0.5373   0.01218   0.00297  -0.0735   0.6174   0.0368
   1.500   0.5885   0.00999   0.00286  -0.0725   0.5953   1.0000
   1.750   0.6156   0.01011   0.00283  -0.0724   0.5817   1.0000
   2.000   0.6427   0.01024   0.00283  -0.0723   0.5670   1.0000
   2.250   0.6697   0.01037   0.00286  -0.0722   0.5514   1.0000
   2.500   0.6966   0.01051   0.00291  -0.0721   0.5344   1.0000
   2.750   0.7232   0.01068   0.00297  -0.0719   0.5153   1.0000
   3.000   0.7494   0.01089   0.00305  -0.0717   0.4951   1.0000
   3.250   0.7755   0.01112   0.00315  -0.0715   0.4747   1.0000
   3.500   0.8014   0.01138   0.00331  -0.0712   0.4560   1.0000
   3.750   0.8271   0.01167   0.00348  -0.0710   0.4391   1.0000
   4.000   0.8528   0.01197   0.00369  -0.0708   0.4239   1.0000
   4.250   0.8787   0.01225   0.00393  -0.0706   0.4108   1.0000
   4.500   0.9046   0.01253   0.00418  -0.0704   0.3995   1.0000
   4.750   0.9305   0.01282   0.00445  -0.0703   0.3902   1.0000
   5.000   0.9565   0.01310   0.00475  -0.0702   0.3815   1.0000
   5.250   0.9826   0.01338   0.00506  -0.0700   0.3739   1.0000
   5.500   1.0084   0.01367   0.00538  -0.0699   0.3663   1.0000
   5.750   1.0343   0.01396   0.00574  -0.0697   0.3592   1.0000
   6.000   1.0598   0.01427   0.00610  -0.0695   0.3517   1.0000
   6.250   1.0851   0.01457   0.00647  -0.0693   0.3412   1.0000
   6.500   1.1098   0.01490   0.00686  -0.0690   0.3282   1.0000
   6.750   1.1342   0.01524   0.00724  -0.0687   0.3148   1.0000
   7.000   1.1586   0.01559   0.00766  -0.0683   0.3029   1.0000
   7.250   1.1828   0.01595   0.00810  -0.0680   0.2920   1.0000
   7.500   1.2073   0.01629   0.00857  -0.0676   0.2807   1.0000
   7.750   1.2309   0.01667   0.00909  -0.0671   0.2664   1.0000
   8.000   1.2516   0.01724   0.00959  -0.0664   0.2327   1.0000
   8.250   1.2662   0.01839   0.01038  -0.0649   0.1734   1.0000
   8.500   1.2786   0.01983   0.01149  -0.0632   0.1131   1.0000
   8.750   1.2837   0.02193   0.01310  -0.0607   0.0549   1.0000
   9.000   1.2924   0.02357   0.01453  -0.0584   0.0177   1.0000
   9.250   1.3017   0.02506   0.01602  -0.0560   0.0105   1.0000
   9.500   1.3122   0.02631   0.01753  -0.0539   0.0087   1.0000
   9.750   1.3173   0.02771   0.01914  -0.0510   0.0078   1.0000
  10.000   1.3174   0.02947   0.02111  -0.0477   0.0072   1.0000
  10.250   1.3205   0.03115   0.02298  -0.0453   0.0069   1.0000
  10.500   1.3225   0.03304   0.02507  -0.0432   0.0064   1.0000
  10.750   1.3232   0.03521   0.02741  -0.0415   0.0059   1.0000
  11.000   1.3223   0.03770   0.03006  -0.0403   0.0055   1.0000
  11.250   1.3187   0.04064   0.03315  -0.0393   0.0052   1.0000
  11.500   1.3115   0.04413   0.03680  -0.0387   0.0050   1.0000
  11.750   1.3049   0.04773   0.04055  -0.0382   0.0049   1.0000
  12.000   1.3013   0.05111   0.04409  -0.0380   0.0048   1.0000
  12.250   1.2968   0.05470   0.04784  -0.0379   0.0047   1.0000
  12.500   1.2919   0.05839   0.05170  -0.0379   0.0046   1.0000
  12.750   1.2868   0.06217   0.05563  -0.0380   0.0045   1.0000
  13.000   1.2817   0.06601   0.05962  -0.0382   0.0044   1.0000
  13.250   1.2766   0.06989   0.06365  -0.0383   0.0043   1.0000
  13.500   1.2718   0.07384   0.06776  -0.0386   0.0043   1.0000
  13.750   1.2672   0.07789   0.07196  -0.0391   0.0042   1.0000
  14.000   1.2623   0.08207   0.07631  -0.0396   0.0041   1.0000
  14.250   1.2571   0.08644   0.08085  -0.0404   0.0041   1.0000
  14.500   1.2514   0.09104   0.08563  -0.0414   0.0040   1.0000
  14.750   1.2449   0.09590   0.09067  -0.0427   0.0040   1.0000
  15.000   1.2377   0.10103   0.09597  -0.0444   0.0039   1.0000
  15.250   1.2299   0.10643   0.10155  -0.0465   0.0039   1.0000
  15.500   1.2217   0.11206   0.10735  -0.0488   0.0038   1.0000
  15.750   1.2132   0.11792   0.11337  -0.0515   0.0038   1.0000
  16.000   1.2041   0.12403   0.11970  -0.0545   0.0037   1.0000
  16.250   1.1956   0.13016   0.12597  -0.0576   0.0037   1.0000
  16.500   1.1850   0.13708   0.13308  -0.0613   0.0037   1.0000
  16.750   1.1759   0.14384   0.13998  -0.0651   0.0036   1.0000
  17.000   1.1665   0.15096   0.14726  -0.0693   0.0036   1.0000
  17.250   1.1553   0.15892   0.15538  -0.0741   0.0037   1.0000
  17.500   1.1418   0.16817   0.16477  -0.0797   0.0038   1.0000
  17.750   1.1301   0.17734   0.17409  -0.0853   0.0039   1.0000
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