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

GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.62 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe225-il-1000000.txt
Download as CSV file: xf-goe225-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 225 (MVA H.35) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0083   0.09624   0.09391  -0.0914   0.8437   0.0264
 -10.750   0.0006   0.09386   0.09151  -0.0921   0.8414   0.0268
 -10.500  -0.3397   0.03647   0.03346  -0.1491   0.8439   0.0260
 -10.250  -0.2975   0.02708   0.02368  -0.1722   0.8409   0.0263
 -10.000  -0.2565   0.02342   0.01978  -0.1823   0.8382   0.0265
  -9.750  -0.2226   0.02165   0.01786  -0.1867   0.8365   0.0269
  -9.500  -0.1904   0.02043   0.01654  -0.1896   0.8347   0.0272
  -9.250  -0.1587   0.01935   0.01535  -0.1920   0.8326   0.0276
  -9.000  -0.1266   0.01818   0.01404  -0.1943   0.8304   0.0279
  -8.750  -0.0949   0.01713   0.01285  -0.1963   0.8284   0.0282
  -8.500  -0.0634   0.01625   0.01184  -0.1979   0.8263   0.0284
  -8.250  -0.0321   0.01548   0.01094  -0.1993   0.8241   0.0287
  -8.000  -0.0009   0.01484   0.01017  -0.2005   0.8217   0.0290
  -7.750   0.0303   0.01427   0.00951  -0.2016   0.8196   0.0293
  -7.500   0.0613   0.01378   0.00894  -0.2025   0.8176   0.0295
  -7.250   0.0922   0.01338   0.00847  -0.2033   0.8152   0.0297
  -7.000   0.1243   0.01230   0.00730  -0.2049   0.8126   0.0303
  -6.750   0.1555   0.01175   0.00672  -0.2059   0.8099   0.0309
  -6.500   0.1865   0.01136   0.00627  -0.2066   0.8074   0.0314
  -6.250   0.2174   0.01103   0.00588  -0.2074   0.8048   0.0318
  -6.000   0.2485   0.01072   0.00553  -0.2081   0.8023   0.0322
  -5.750   0.2795   0.01040   0.00518  -0.2088   0.8002   0.0327
  -5.500   0.3105   0.01011   0.00486  -0.2094   0.7978   0.0332
  -5.250   0.3414   0.00986   0.00456  -0.2101   0.7952   0.0337
  -5.000   0.3721   0.00963   0.00429  -0.2106   0.7923   0.0342
  -4.750   0.4030   0.00938   0.00398  -0.2112   0.7893   0.0347
  -4.500   0.4342   0.00911   0.00365  -0.2119   0.7859   0.0359
  -4.250   0.4650   0.00888   0.00342  -0.2124   0.7833   0.0371
  -4.000   0.4955   0.00870   0.00323  -0.2129   0.7799   0.0384
  -3.750   0.5260   0.00854   0.00304  -0.2133   0.7760   0.0395
  -3.500   0.5565   0.00835   0.00282  -0.2138   0.7719   0.0423
  -3.250   0.5870   0.00820   0.00266  -0.2142   0.7679   0.0477
  -3.000   0.6177   0.00797   0.00258  -0.2148   0.7634   0.0755
  -2.750   0.6475   0.00790   0.00254  -0.2151   0.7578   0.0862
  -2.500   0.6769   0.00788   0.00247  -0.2153   0.7520   0.0915
  -2.250   0.7068   0.00779   0.00243  -0.2156   0.7451   0.0969
  -2.000   0.7360   0.00779   0.00238  -0.2157   0.7369   0.1005
  -1.750   0.7657   0.00772   0.00230  -0.2160   0.7261   0.1050
  -1.500   0.7949   0.00768   0.00222  -0.2161   0.7106   0.1094
  -1.250   0.8229   0.00774   0.00216  -0.2160   0.6854   0.1131
  -1.000   0.8494   0.00795   0.00218  -0.2157   0.6477   0.1158
  -0.750   0.8757   0.00818   0.00224  -0.2154   0.6128   0.1239
  -0.500   0.9024   0.00839   0.00233  -0.2151   0.5884   0.1330
  -0.250   0.9306   0.00840   0.00241  -0.2153   0.5710   0.1909
   0.000   0.9587   0.00845   0.00254  -0.2154   0.5582   0.2499
   0.250   0.9865   0.00856   0.00265  -0.2154   0.5479   0.2704
   0.500   1.0139   0.00872   0.00276  -0.2153   0.5384   0.2826
   0.750   1.0421   0.00881   0.00285  -0.2153   0.5312   0.2949
   1.000   1.0697   0.00894   0.00295  -0.2152   0.5239   0.3038
   1.250   1.0973   0.00906   0.00306  -0.2152   0.5164   0.3140
   1.500   1.1248   0.00918   0.00316  -0.2151   0.5081   0.3238
   1.750   1.1519   0.00932   0.00328  -0.2149   0.5000   0.3344
   2.000   1.1798   0.00940   0.00338  -0.2149   0.4936   0.3452
   2.250   1.2068   0.00954   0.00350  -0.2147   0.4875   0.3568
   2.500   1.2343   0.00963   0.00363  -0.2147   0.4825   0.3724
   2.750   1.2620   0.00970   0.00375  -0.2146   0.4776   0.3936
   3.000   1.2891   0.00981   0.00390  -0.2145   0.4721   0.4199
   3.250   1.3155   0.00997   0.00407  -0.2142   0.4667   0.4433
   3.500   1.3431   0.01004   0.00419  -0.2142   0.4626   0.4631
   3.750   1.3699   0.01016   0.00434  -0.2140   0.4575   0.4814
   4.000   1.3957   0.01033   0.00452  -0.2136   0.4518   0.4991
   4.250   1.4224   0.01045   0.00467  -0.2134   0.4468   0.5151
   4.500   1.4489   0.01056   0.00482  -0.2132   0.4415   0.5278
   4.750   1.4743   0.01074   0.00501  -0.2127   0.4359   0.5401
   5.000   1.5001   0.01089   0.00518  -0.2124   0.4303   0.5524
   5.250   1.5256   0.01104   0.00535  -0.2120   0.4228   0.5648
   5.500   1.5498   0.01126   0.00556  -0.2113   0.4142   0.5773
   5.750   1.5744   0.01144   0.00576  -0.2108   0.4049   0.5914
   6.000   1.5982   0.01165   0.00599  -0.2101   0.3970   0.6084
   6.250   1.6221   0.01185   0.00623  -0.2094   0.3881   0.6346
   6.500   1.6424   0.01168   0.00654  -0.2081   0.3788   0.9120
   6.750   1.6623   0.01197   0.00679  -0.2066   0.3682   1.0000
   7.000   1.6839   0.01226   0.00706  -0.2055   0.3577   1.0000
   7.250   1.7030   0.01265   0.00739  -0.2039   0.3450   1.0000
   7.500   1.7193   0.01311   0.00779  -0.2019   0.3291   1.0000
   7.750   1.7333   0.01366   0.00825  -0.1994   0.3122   1.0000
   8.000   1.7453   0.01436   0.00883  -0.1966   0.2909   1.0000
   8.250   1.7558   0.01519   0.00953  -0.1938   0.2682   1.0000
   8.500   1.7677   0.01599   0.01022  -0.1912   0.2492   1.0000
   8.750   1.7806   0.01675   0.01091  -0.1889   0.2347   1.0000
   9.000   1.7935   0.01753   0.01163  -0.1867   0.2219   1.0000
   9.250   1.8057   0.01838   0.01242  -0.1844   0.2097   1.0000
   9.500   1.8203   0.01911   0.01313  -0.1825   0.2004   1.0000
   9.750   1.8334   0.01993   0.01393  -0.1805   0.1910   1.0000
  10.000   1.8449   0.02089   0.01483  -0.1783   0.1808   1.0000
  10.250   1.8581   0.02175   0.01568  -0.1764   0.1716   1.0000
  10.500   1.8692   0.02276   0.01667  -0.1743   0.1621   1.0000
  10.750   1.8780   0.02396   0.01780  -0.1720   0.1508   1.0000
  11.000   1.8855   0.02527   0.01906  -0.1696   0.1376   1.0000
  11.250   1.8900   0.02683   0.02053  -0.1669   0.1209   1.0000
  11.500   1.8792   0.02957   0.02305  -0.1626   0.0888   1.0000
  11.750   1.8630   0.03287   0.02617  -0.1580   0.0596   1.0000
  12.000   1.8637   0.03490   0.02820  -0.1554   0.0524   1.0000
  12.250   1.8691   0.03661   0.02994  -0.1533   0.0490   1.0000
  12.500   1.8721   0.03857   0.03193  -0.1511   0.0456   1.0000
  12.750   1.8796   0.04018   0.03359  -0.1494   0.0434   1.0000
  13.000   1.8840   0.04209   0.03555  -0.1476   0.0411   1.0000
  13.250   1.8863   0.04427   0.03776  -0.1457   0.0384   1.0000
  13.500   1.8929   0.04608   0.03963  -0.1442   0.0366   1.0000
  13.750   1.8961   0.04829   0.04187  -0.1426   0.0344   1.0000
  14.000   1.8979   0.05067   0.04429  -0.1410   0.0322   1.0000
  14.250   1.9016   0.05292   0.04660  -0.1397   0.0302   1.0000
  14.500   1.9014   0.05565   0.04937  -0.1382   0.0283   1.0000
  14.750   1.9027   0.05831   0.05208  -0.1370   0.0266   1.0000
  15.000   1.9033   0.06109   0.05492  -0.1359   0.0251   1.0000
  15.250   1.9004   0.06436   0.05824  -0.1348   0.0236   1.0000
  15.500   1.8994   0.06745   0.06141  -0.1339   0.0225   1.0000
  15.750   1.8978   0.07069   0.06472  -0.1331   0.0216   1.0000
  16.000   1.8940   0.07428   0.06838  -0.1324   0.0206   1.0000
  16.250   1.8869   0.07836   0.07253  -0.1318   0.0197   1.0000
  16.500   1.8829   0.08207   0.07634  -0.1314   0.0191   1.0000
  16.750   1.8792   0.08575   0.08010  -0.1311   0.0185   1.0000
  17.000   1.8738   0.08970   0.08414  -0.1309   0.0179   1.0000
  17.250   1.8671   0.09388   0.08839  -0.1308   0.0174   1.0000
  17.500   1.8584   0.09838   0.09298  -0.1309   0.0169   1.0000
  17.750   1.8468   0.10333   0.09801  -0.1312   0.0164   1.0000
<< Back to GOE 225 (MVA H.35) AIRFOIL (goe225-il)

Polar data table (+)

Polar graphs


<< Back to GOE 225 (MVA H.35) AIRFOIL (goe225-il)