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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 200,000
Max Cl/Cd: 74.36 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe187-il-200000.txt
Download as CSV file: xf-goe187-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3791   0.11275   0.10933  -0.0128   1.0000   0.0186
  -8.750  -0.3751   0.11038   0.10701  -0.0160   1.0000   0.0187
  -8.500  -0.3711   0.10776   0.10443  -0.0189   1.0000   0.0188
  -8.250  -0.3669   0.10491   0.10162  -0.0217   1.0000   0.0189
  -8.000  -0.3609   0.09822   0.09497  -0.0192   1.0000   0.0194
  -7.750  -0.3532   0.09418   0.09095  -0.0182   1.0000   0.0198
  -7.500  -0.3482   0.09093   0.08774  -0.0188   1.0000   0.0201
  -7.250  -0.3423   0.08772   0.08457  -0.0202   1.0000   0.0205
  -7.000  -0.3349   0.08446   0.08134  -0.0223   1.0000   0.0209
  -6.750  -0.3269   0.08119   0.07809  -0.0246   1.0000   0.0213
  -6.500  -0.3186   0.07797   0.07490  -0.0268   1.0000   0.0217
  -6.250  -0.3108   0.07485   0.07182  -0.0287   1.0000   0.0222
  -6.000  -0.3037   0.07189   0.06888  -0.0302   1.0000   0.0226
  -5.750  -0.2998   0.06929   0.06632  -0.0307   1.0000   0.0231
  -5.500  -0.3043   0.06750   0.06458  -0.0292   1.0000   0.0234
  -5.250  -0.2608   0.06230   0.05926  -0.0385   0.9942   0.0247
  -5.000  -0.2035   0.05766   0.05437  -0.0494   0.9864   0.0265
  -4.750  -0.1482   0.05429   0.05061  -0.0576   0.9779   0.0272
  -4.500  -0.1084   0.04813   0.04424  -0.0638   0.9713   0.0277
  -4.250  -0.0818   0.04278   0.03893  -0.0673   0.9606   0.0290
  -4.000  -0.0486   0.03929   0.03532  -0.0706   0.9491   0.0307
  -3.750  -0.0132   0.03617   0.03199  -0.0734   0.9366   0.0332
  -3.500   0.0280   0.03501   0.03033  -0.0747   0.9225   0.0379
  -3.250   0.0550   0.03081   0.02587  -0.0759   0.9076   0.0403
  -3.000   0.0785   0.02847   0.02346  -0.0762   0.8915   0.0451
  -2.000   0.1851   0.02214   0.01580  -0.0744   0.8319   0.0815
  -1.750   0.2096   0.02035   0.01394  -0.0742   0.8180   0.0988
  -1.500   0.2354   0.02024   0.01352  -0.0738   0.8041   0.1367
  -1.250   0.2594   0.01777   0.01110  -0.0738   0.7909   0.1698
  -0.750   0.3270   0.01617   0.00839  -0.0702   0.7668   0.0667
  -0.500   0.3558   0.01527   0.00726  -0.0691   0.7546   0.0525
  -0.250   0.3830   0.01433   0.00623  -0.0684   0.7419   0.0499
   0.000   0.4101   0.01383   0.00561  -0.0677   0.7286   0.0520
   0.250   0.4363   0.01296   0.00474  -0.0671   0.7153   0.0547
   0.500   0.4630   0.01254   0.00426  -0.0666   0.7011   0.0585
   1.000   0.5173   0.01207   0.00360  -0.0658   0.6712   0.0929
   1.250   0.5493   0.00994   0.00347  -0.0666   0.6545   1.0000
   1.500   0.5760   0.01007   0.00340  -0.0662   0.6361   1.0000
   1.750   0.6025   0.01022   0.00336  -0.0658   0.6173   1.0000
   2.000   0.6290   0.01038   0.00336  -0.0654   0.5970   1.0000
   2.250   0.6555   0.01055   0.00339  -0.0651   0.5768   1.0000
   2.500   0.6819   0.01075   0.00343  -0.0647   0.5570   1.0000
   2.750   0.7082   0.01093   0.00350  -0.0644   0.5353   1.0000
   3.000   0.7342   0.01115   0.00355  -0.0640   0.5153   1.0000
   3.250   0.7604   0.01138   0.00366  -0.0638   0.4961   1.0000
   3.500   0.7867   0.01164   0.00381  -0.0635   0.4809   1.0000
   3.750   0.8131   0.01192   0.00403  -0.0633   0.4684   1.0000
   4.000   0.8394   0.01221   0.00424  -0.0631   0.4575   1.0000
   4.250   0.8657   0.01252   0.00447  -0.0629   0.4470   1.0000
   4.500   0.8921   0.01279   0.00474  -0.0628   0.4362   1.0000
   4.750   0.9183   0.01309   0.00501  -0.0626   0.4265   1.0000
   5.000   0.9445   0.01343   0.00533  -0.0624   0.4181   1.0000
   5.250   0.9708   0.01368   0.00565  -0.0622   0.4085   1.0000
   5.500   0.9969   0.01400   0.00598  -0.0620   0.4003   1.0000
   5.750   1.0228   0.01430   0.00630  -0.0618   0.3915   1.0000
   6.000   1.0486   0.01457   0.00668  -0.0616   0.3821   1.0000
   6.250   1.0741   0.01487   0.00702  -0.0613   0.3727   1.0000
   6.500   1.0994   0.01514   0.00735  -0.0610   0.3624   1.0000
   6.750   1.1246   0.01538   0.00771  -0.0607   0.3510   1.0000
   7.000   1.1495   0.01564   0.00811  -0.0603   0.3392   1.0000
   7.250   1.1740   0.01589   0.00847  -0.0599   0.3252   1.0000
   7.500   1.1972   0.01616   0.00876  -0.0593   0.3050   1.0000
   7.750   1.2202   0.01641   0.00909  -0.0586   0.2729   1.0000
   8.000   1.2401   0.01703   0.00956  -0.0577   0.2177   1.0000
   8.250   1.2563   0.01820   0.01043  -0.0565   0.1739   1.0000
   8.500   1.2738   0.01925   0.01139  -0.0553   0.1498   1.0000
   8.750   1.2928   0.02011   0.01224  -0.0544   0.1314   1.0000
   9.000   1.3118   0.02093   0.01302  -0.0534   0.1087   1.0000
   9.250   1.3246   0.02234   0.01423  -0.0518   0.0795   1.0000
   9.500   1.3339   0.02407   0.01561  -0.0496   0.0328   1.0000
   9.750   1.3423   0.02574   0.01733  -0.0471   0.0262   1.0000
  10.000   1.3514   0.02719   0.01899  -0.0447   0.0240   1.0000
  10.250   1.3555   0.02880   0.02078  -0.0418   0.0223   1.0000
  10.500   1.3527   0.03071   0.02284  -0.0383   0.0209   1.0000
  10.750   1.3450   0.03321   0.02552  -0.0351   0.0197   1.0000
  11.000   1.3419   0.03565   0.02811  -0.0330   0.0191   1.0000
  11.250   1.3404   0.03818   0.03080  -0.0315   0.0188   1.0000
  11.500   1.3383   0.04098   0.03375  -0.0303   0.0184   1.0000
  11.750   1.3363   0.04392   0.03684  -0.0294   0.0181   1.0000
  12.000   1.3347   0.04693   0.04002  -0.0286   0.0178   1.0000
  12.250   1.3339   0.04994   0.04316  -0.0277   0.0176   1.0000
  12.500   1.3338   0.05292   0.04628  -0.0268   0.0174   1.0000
  12.750   1.3346   0.05590   0.04941  -0.0258   0.0173   1.0000
  13.000   1.3356   0.05896   0.05264  -0.0248   0.0172   1.0000
  13.250   1.3357   0.06224   0.05611  -0.0240   0.0172   1.0000
  13.500   1.3334   0.06588   0.05995  -0.0236   0.0170   1.0000
  13.750   1.3286   0.06985   0.06412  -0.0238   0.0168   1.0000
  14.000   1.3216   0.07416   0.06864  -0.0244   0.0165   1.0000
  14.250   1.3130   0.07880   0.07348  -0.0255   0.0163   1.0000
  14.500   1.3027   0.08378   0.07867  -0.0268   0.0162   1.0000
  14.750   1.2913   0.08916   0.08425  -0.0287   0.0160   1.0000
  15.000   1.2784   0.09505   0.09036  -0.0311   0.0160   1.0000
  15.250   1.2640   0.10148   0.09699  -0.0340   0.0161   1.0000
  15.500   1.2484   0.10845   0.10418  -0.0375   0.0162   1.0000
  15.750   1.2320   0.11592   0.11186  -0.0415   0.0164   1.0000
  16.000   1.2149   0.12389   0.12001  -0.0461   0.0166   1.0000
  16.250   1.1972   0.13232   0.12862  -0.0512   0.0168   1.0000
  16.500   1.1785   0.14150   0.13798  -0.0569   0.0171   1.0000
  16.750   1.1591   0.15144   0.14807  -0.0632   0.0175   1.0000
  17.000   1.1381   0.16249   0.15923  -0.0702   0.0182   1.0000
  17.250   1.1163   0.17436   0.17118  -0.0774   0.0191   1.0000
  17.500   1.1063   0.18343   0.18030  -0.0825   0.0197   1.0000
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