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

Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.85 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe765-il-1000000.txt
Download as CSV file: xf-goe765-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Gottingen 765 airfoil (recovered). Thick: .144 L
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -1.1684   0.08554   0.08239  -0.0283   1.0000   0.0185
 -18.750  -1.2043   0.07599   0.07267  -0.0338   1.0000   0.0184
 -18.500  -1.2340   0.06720   0.06371  -0.0392   1.0000   0.0185
 -18.250  -1.2463   0.06110   0.05750  -0.0432   1.0000   0.0187
 -18.000  -1.2601   0.05518   0.05144  -0.0469   1.0000   0.0188
 -17.750  -1.2741   0.04983   0.04594  -0.0497   1.0000   0.0188
 -17.500  -1.2770   0.04633   0.04235  -0.0511   1.0000   0.0190
 -17.250  -1.2831   0.04285   0.03875  -0.0519   1.0000   0.0191
 -17.000  -1.2854   0.04009   0.03590  -0.0520   1.0000   0.0193
 -16.750  -1.2863   0.03768   0.03338  -0.0516   1.0000   0.0195
 -16.500  -1.2852   0.03564   0.03124  -0.0508   1.0000   0.0197
 -16.250  -1.2817   0.03392   0.02943  -0.0497   1.0000   0.0199
 -16.000  -1.2774   0.03235   0.02777  -0.0484   1.0000   0.0201
 -15.750  -1.2733   0.03086   0.02618  -0.0468   1.0000   0.0203
 -15.500  -1.2651   0.02971   0.02495  -0.0453   1.0000   0.0205
 -15.250  -1.2575   0.02857   0.02372  -0.0435   1.0000   0.0206
 -15.000  -1.2581   0.02697   0.02202  -0.0409   1.0000   0.0209
 -14.750  -1.2544   0.02570   0.02070  -0.0384   1.0000   0.0213
 -14.500  -1.2481   0.02461   0.01955  -0.0359   1.0000   0.0214
 -14.250  -1.2366   0.02386   0.01876  -0.0340   1.0000   0.0218
 -14.000  -1.2233   0.02321   0.01808  -0.0321   1.0000   0.0222
 -13.750  -1.2108   0.02252   0.01734  -0.0301   1.0000   0.0225
 -13.500  -1.1977   0.02186   0.01662  -0.0280   1.0000   0.0229
 -13.250  -1.1837   0.02126   0.01596  -0.0261   1.0000   0.0233
 -13.000  -1.1685   0.02071   0.01536  -0.0242   1.0000   0.0236
 -12.750  -1.1529   0.02020   0.01478  -0.0223   1.0000   0.0239
 -12.500  -1.1389   0.01958   0.01411  -0.0201   1.0000   0.0241
 -12.250  -1.1287   0.01875   0.01325  -0.0174   1.0000   0.0247
 -12.000  -1.1141   0.01817   0.01264  -0.0152   1.0000   0.0252
 -11.750  -1.0973   0.01771   0.01216  -0.0133   1.0000   0.0257
 -11.500  -1.0789   0.01735   0.01178  -0.0117   1.0000   0.0263
 -11.250  -1.0615   0.01692   0.01132  -0.0098   1.0000   0.0268
 -11.000  -1.0429   0.01656   0.01092  -0.0081   1.0000   0.0273
 -10.750  -1.0238   0.01623   0.01055  -0.0065   1.0000   0.0278
 -10.500  -0.9813   0.01532   0.00960  -0.0102   0.9556   0.0289
 -10.250  -0.9401   0.01485   0.00906  -0.0133   0.9213   0.0300
 -10.000  -0.9202   0.01462   0.00871  -0.0116   0.8916   0.0308
  -9.750  -0.9012   0.01442   0.00839  -0.0098   0.8721   0.0316
  -9.250  -0.8647   0.01370   0.00755  -0.0059   0.8424   0.0337
  -9.000  -0.8440   0.01344   0.00725  -0.0044   0.8306   0.0348
  -8.750  -0.8230   0.01323   0.00696  -0.0029   0.8193   0.0360
  -8.500  -0.8022   0.01293   0.00661  -0.0015   0.8089   0.0373
  -8.250  -0.7811   0.01265   0.00631   0.0000   0.7992   0.0391
  -8.000  -0.7588   0.01244   0.00606   0.0012   0.7895   0.0406
  -7.750  -0.7366   0.01222   0.00578   0.0024   0.7805   0.0424
  -7.500  -0.7142   0.01193   0.00549   0.0036   0.7715   0.0446
  -7.250  -0.6909   0.01176   0.00527   0.0047   0.7628   0.0467
  -7.000  -0.6676   0.01150   0.00499   0.0057   0.7542   0.0491
  -6.750  -0.6441   0.01129   0.00476   0.0067   0.7457   0.0519
  -6.500  -0.6197   0.01110   0.00455   0.0075   0.7375   0.0547
  -6.250  -0.5962   0.01087   0.00431   0.0085   0.7288   0.0584
  -6.000  -0.5715   0.01070   0.00413   0.0093   0.7207   0.0620
  -5.750  -0.5476   0.01048   0.00391   0.0102   0.7120   0.0669
  -5.500  -0.5229   0.01031   0.00373   0.0110   0.7038   0.0715
  -5.250  -0.4985   0.01012   0.00355   0.0118   0.6954   0.0773
  -5.000  -0.4741   0.00994   0.00337   0.0126   0.6875   0.0842
  -4.750  -0.4492   0.00977   0.00322   0.0134   0.6794   0.0919
  -4.500  -0.4248   0.00962   0.00306   0.0142   0.6714   0.1004
  -4.250  -0.3999   0.00942   0.00292   0.0149   0.6641   0.1118
  -4.000  -0.3755   0.00925   0.00278   0.0158   0.6562   0.1241
  -3.750  -0.3507   0.00909   0.00265   0.0165   0.6485   0.1374
  -3.500  -0.3261   0.00892   0.00253   0.0173   0.6402   0.1533
  -3.250  -0.3016   0.00877   0.00241   0.0181   0.6326   0.1712
  -3.000  -0.2768   0.00860   0.00231   0.0188   0.6243   0.1910
  -2.750  -0.2528   0.00844   0.00221   0.0197   0.6160   0.2142
  -2.500  -0.2283   0.00826   0.00212   0.0205   0.6084   0.2420
  -2.250  -0.2044   0.00810   0.00203   0.0214   0.5998   0.2697
  -2.000  -0.1802   0.00792   0.00195   0.0223   0.5916   0.3014
  -1.750  -0.1571   0.00773   0.00187   0.0233   0.5832   0.3393
  -1.500  -0.1360   0.00743   0.00177   0.0248   0.5753   0.3981
  -1.250  -0.1207   0.00693   0.00164   0.0274   0.5668   0.5047
  -1.000  -0.1154   0.00627   0.00150   0.0322   0.5596   0.6465
  -0.750  -0.1105   0.00576   0.00144   0.0374   0.5519   0.7635
  -0.500  -0.0894   0.00559   0.00149   0.0392   0.5433   0.8346
  -0.250  -0.0584   0.00559   0.00157   0.0388   0.5338   0.8667
   0.000  -0.0266   0.00567   0.00164   0.0382   0.5244   0.8848
   0.250   0.0020   0.00575   0.00170   0.0383   0.5147   0.8975
   0.500   0.0319   0.00587   0.00179   0.0381   0.5049   0.9078
   0.750   0.0653   0.00602   0.00190   0.0372   0.4943   0.9155
   1.000   0.0930   0.00620   0.00205   0.0375   0.4847   0.9244
   1.500   0.1682   0.00663   0.00239   0.0338   0.4623   0.9319
   1.750   0.2086   0.00689   0.00258   0.0312   0.4509   0.9341
   2.000   0.2436   0.00712   0.00275   0.0299   0.4398   0.9367
   2.250   0.2599   0.00724   0.00284   0.0326   0.4306   0.9431
   2.500   0.3019   0.00750   0.00304   0.0297   0.4190   0.9437
   2.750   0.3425   0.00775   0.00324   0.0270   0.4075   0.9443
   3.000   0.3822   0.00798   0.00343   0.0246   0.3970   0.9449
   3.250   0.4209   0.00824   0.00362   0.0224   0.3860   0.9458
   3.500   0.4561   0.00839   0.00375   0.0209   0.3762   0.9467
   3.750   0.4884   0.00855   0.00386   0.0199   0.3665   0.9479
   4.000   0.5192   0.00867   0.00395   0.0193   0.3578   0.9492
   4.250   0.5482   0.00880   0.00405   0.0190   0.3490   0.9509
   4.500   0.5581   0.00889   0.00413   0.0228   0.3420   0.9571
   4.750   0.5911   0.00902   0.00422   0.0216   0.3330   0.9576
   5.000   0.6238   0.00913   0.00431   0.0205   0.3245   0.9581
   5.250   0.6558   0.00928   0.00442   0.0195   0.3157   0.9587
   5.500   0.6879   0.00941   0.00453   0.0185   0.3062   0.9594
   5.750   0.7194   0.00956   0.00466   0.0176   0.2973   0.9603
   6.000   0.7501   0.00973   0.00479   0.0168   0.2875   0.9612
   6.250   0.7801   0.00988   0.00492   0.0162   0.2782   0.9623
   6.500   0.8086   0.01009   0.00508   0.0159   0.2674   0.9638
   6.750   0.8358   0.01025   0.00523   0.0159   0.2578   0.9658
   7.000   0.8474   0.01046   0.00542   0.0191   0.2500   0.9705
   7.250   0.8786   0.01064   0.00556   0.0182   0.2389   0.9711
   7.500   0.9099   0.01084   0.00573   0.0172   0.2277   0.9717
   7.750   0.9405   0.01110   0.00594   0.0162   0.2154   0.9724
   8.000   0.9705   0.01138   0.00617   0.0154   0.2038   0.9733
   8.250   0.9991   0.01168   0.00641   0.0148   0.1909   0.9743
   8.500   1.0268   0.01196   0.00666   0.0145   0.1795   0.9756
   8.750   1.0526   0.01229   0.00695   0.0144   0.1677   0.9772
   9.000   1.0754   0.01266   0.00727   0.0150   0.1561   0.9796
   9.250   1.0914   0.01308   0.00765   0.0170   0.1456   0.9829
   9.500   1.1199   0.01348   0.00798   0.0162   0.1325   0.9836
   9.750   1.1475   0.01393   0.00837   0.0155   0.1201   0.9844
  10.250   1.1996   0.01491   0.00924   0.0146   0.0979   0.9869
  10.500   1.2242   0.01542   0.00971   0.0144   0.0888   0.9886
  10.750   1.2462   0.01594   0.01021   0.0147   0.0809   0.9906
  11.000   1.2628   0.01653   0.01077   0.0161   0.0742   0.9931
  11.250   1.2857   0.01714   0.01134   0.0159   0.0672   0.9943
  11.500   1.3098   0.01768   0.01188   0.0155   0.0616   0.9956
  11.750   1.3300   0.01825   0.01245   0.0156   0.0566   0.9976
  12.000   1.3461   0.01896   0.01314   0.0163   0.0521   0.9996
  12.250   1.3477   0.01959   0.01382   0.0197   0.0500   1.0000
  12.500   1.3422   0.02042   0.01469   0.0240   0.0481   1.0000
  12.750   1.3371   0.02147   0.01576   0.0278   0.0459   1.0000
  13.000   1.3374   0.02243   0.01677   0.0307   0.0443   1.0000
  13.250   1.3375   0.02353   0.01791   0.0334   0.0426   1.0000
  13.500   1.3355   0.02489   0.01930   0.0360   0.0408   1.0000
  13.750   1.3355   0.02625   0.02069   0.0382   0.0392   1.0000
  14.000   1.3373   0.02760   0.02209   0.0400   0.0379   1.0000
  14.250   1.3369   0.02921   0.02374   0.0418   0.0365   1.0000
  14.500   1.3339   0.03113   0.02570   0.0434   0.0351   1.0000
  14.750   1.3350   0.03285   0.02748   0.0447   0.0340   1.0000
  15.000   1.3353   0.03471   0.02940   0.0457   0.0329   1.0000
  15.250   1.3338   0.03683   0.03156   0.0467   0.0318   1.0000
  15.500   1.3299   0.03925   0.03403   0.0474   0.0308   1.0000
  15.750   1.3252   0.04186   0.03670   0.0480   0.0300   1.0000
  16.000   1.3257   0.04409   0.03900   0.0483   0.0292   1.0000
  16.250   1.3227   0.04678   0.04176   0.0485   0.0284   1.0000
  16.500   1.3194   0.04959   0.04463   0.0485   0.0279   1.0000
  16.750   1.3124   0.05293   0.04803   0.0483   0.0271   1.0000
  17.000   1.3022   0.05675   0.05191   0.0478   0.0264   1.0000
  17.250   1.2963   0.06016   0.05541   0.0473   0.0258   1.0000
  17.500   1.2918   0.06349   0.05881   0.0467   0.0254   1.0000
  17.750   1.2860   0.06701   0.06242   0.0460   0.0248   1.0000
  18.000   1.2785   0.07085   0.06634   0.0451   0.0245   1.0000
  18.250   1.2693   0.07499   0.07055   0.0440   0.0240   1.0000
  18.500   1.2586   0.07942   0.07505   0.0427   0.0237   1.0000
  18.750   1.2465   0.08409   0.07980   0.0413   0.0231   1.0000
  19.000   1.2318   0.08925   0.08502   0.0396   0.0227   1.0000
<< Back to Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il)

Polar data table (+)

Polar graphs


<< Back to Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il)