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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.14 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe630-il-1000000-n5.txt
Download as CSV file: xf-goe630-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 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   0.0454   0.09770   0.09481  -0.1145   0.7735   0.0131
 -11.250   0.0526   0.09532   0.09238  -0.1154   0.7632   0.0135
 -11.000   0.0461   0.08996   0.08697  -0.1171   0.7535   0.0150
 -10.500   0.0634   0.08603   0.08297  -0.1186   0.7369   0.0153
 -10.250   0.0722   0.08414   0.08105  -0.1192   0.7289   0.0154
 -10.000   0.0828   0.08251   0.07940  -0.1198   0.7232   0.0156
  -9.750   0.0900   0.08029   0.07717  -0.1206   0.7164   0.0158
  -9.500   0.0989   0.07847   0.07532  -0.1212   0.7113   0.0163
  -9.250   0.1040   0.07591   0.07276  -0.1220   0.7064   0.0167
  -9.000   0.0919   0.07053   0.06738  -0.1238   0.7017   0.0180
  -8.750   0.0996   0.06883   0.06567  -0.1242   0.6957   0.0182
  -7.250   0.0064   0.01663   0.01201  -0.1536   0.6717   0.0240
  -7.000   0.0284   0.01534   0.01047  -0.1531   0.6663   0.0242
  -6.750   0.0519   0.01450   0.00942  -0.1526   0.6607   0.0245
  -6.500   0.0766   0.01379   0.00856  -0.1522   0.6555   0.0246
  -6.250   0.1019   0.01326   0.00789  -0.1517   0.6495   0.0247
  -6.000   0.1263   0.01267   0.00712  -0.1512   0.6429   0.0249
  -5.750   0.1515   0.01207   0.00640  -0.1508   0.6367   0.0253
  -5.500   0.1773   0.01174   0.00599  -0.1503   0.6296   0.0255
  -5.250   0.2035   0.01146   0.00564  -0.1500   0.6234   0.0257
  -5.000   0.2299   0.01123   0.00533  -0.1496   0.6156   0.0260
  -4.750   0.2561   0.01104   0.00507  -0.1492   0.6078   0.0263
  -4.500   0.2826   0.01088   0.00485  -0.1488   0.5992   0.0267
  -4.250   0.3087   0.01069   0.00457  -0.1484   0.5913   0.0270
  -4.000   0.3348   0.01049   0.00429  -0.1479   0.5817   0.0273
  -3.750   0.3607   0.01031   0.00402  -0.1475   0.5722   0.0276
  -3.500   0.3862   0.01018   0.00379  -0.1469   0.5609   0.0279
  -3.250   0.4122   0.01003   0.00357  -0.1464   0.5506   0.0282
  -3.000   0.4381   0.00993   0.00338  -0.1459   0.5412   0.0285
  -2.750   0.4638   0.00985   0.00323  -0.1454   0.5306   0.0287
  -2.500   0.4896   0.00977   0.00308  -0.1449   0.5200   0.0289
  -2.250   0.5146   0.00965   0.00289  -0.1443   0.5086   0.0295
  -2.000   0.5400   0.00961   0.00278  -0.1437   0.4977   0.0300
  -1.750   0.5659   0.00958   0.00271  -0.1432   0.4884   0.0305
  -1.500   0.5913   0.00959   0.00267  -0.1427   0.4792   0.0311
  -1.250   0.6172   0.00958   0.00262  -0.1422   0.4705   0.0318
  -1.000   0.6426   0.00960   0.00258  -0.1417   0.4620   0.0325
  -0.750   0.6682   0.00960   0.00254  -0.1412   0.4534   0.0331
  -0.500   0.6934   0.00963   0.00252  -0.1406   0.4451   0.0336
  -0.250   0.7186   0.00963   0.00248  -0.1400   0.4364   0.0348
   0.000   0.7436   0.00967   0.00249  -0.1394   0.4292   0.0358
   0.250   0.7693   0.00969   0.00250  -0.1389   0.4229   0.0371
   0.500   0.7942   0.00975   0.00252  -0.1383   0.4163   0.0383
   0.750   0.8195   0.00978   0.00254  -0.1378   0.4109   0.0398
   1.000   0.8446   0.00982   0.00257  -0.1372   0.4052   0.0420
   1.250   0.8691   0.00990   0.00263  -0.1365   0.3993   0.0445
   1.500   0.8941   0.00995   0.00267  -0.1360   0.3943   0.0471
   1.750   0.9188   0.01001   0.00272  -0.1353   0.3885   0.0504
   2.000   0.9425   0.01012   0.00279  -0.1346   0.3825   0.0528
   2.250   0.9672   0.01016   0.00285  -0.1339   0.3784   0.0579
   2.500   0.9915   0.01022   0.00292  -0.1333   0.3740   0.0652
   2.750   1.0149   0.01027   0.00303  -0.1324   0.3694   0.0927
   3.000   1.0377   0.01032   0.00315  -0.1315   0.3652   0.1370
   3.250   1.0612   0.01033   0.00328  -0.1308   0.3618   0.1969
   3.500   1.0838   0.01031   0.00342  -0.1298   0.3581   0.2730
   3.750   1.1035   0.01016   0.00363  -0.1284   0.3540   0.4667
   4.250   1.1940   0.00974   0.00418  -0.1369   0.3451   1.0000
   4.500   1.2168   0.00989   0.00431  -0.1360   0.3415   1.0000
   4.750   1.2387   0.01006   0.00446  -0.1349   0.3381   1.0000
   5.000   1.2587   0.01025   0.00462  -0.1335   0.3346   1.0000
   5.250   1.2792   0.01041   0.00477  -0.1321   0.3321   1.0000
   5.500   1.3004   0.01056   0.00492  -0.1309   0.3298   1.0000
   5.750   1.3212   0.01073   0.00509  -0.1297   0.3272   1.0000
   6.000   1.3417   0.01091   0.00527  -0.1284   0.3245   1.0000
   6.250   1.3619   0.01112   0.00547  -0.1271   0.3217   1.0000
   6.500   1.3814   0.01136   0.00569  -0.1257   0.3188   1.0000
   6.750   1.4020   0.01157   0.00591  -0.1246   0.3162   1.0000
   7.000   1.4232   0.01177   0.00612  -0.1236   0.3142   1.0000
   7.250   1.4440   0.01198   0.00636  -0.1225   0.3118   1.0000
   7.500   1.4644   0.01222   0.00661  -0.1214   0.3095   1.0000
   7.750   1.4842   0.01249   0.00689  -0.1203   0.3071   1.0000
   8.000   1.5033   0.01280   0.00719  -0.1191   0.3045   1.0000
   8.250   1.5218   0.01314   0.00754  -0.1178   0.3013   1.0000
   8.500   1.5425   0.01340   0.00782  -0.1169   0.2978   1.0000
   8.750   1.5605   0.01378   0.00819  -0.1156   0.2913   1.0000
   9.000   1.5768   0.01425   0.00864  -0.1141   0.2861   1.0000
   9.250   1.5963   0.01459   0.00901  -0.1131   0.2809   1.0000
   9.500   1.6136   0.01504   0.00946  -0.1119   0.2760   1.0000
   9.750   1.6294   0.01558   0.00999  -0.1105   0.2709   1.0000
  10.000   1.6467   0.01606   0.01048  -0.1093   0.2639   1.0000
  10.250   1.6613   0.01670   0.01111  -0.1079   0.2576   1.0000
  10.500   1.6774   0.01727   0.01169  -0.1067   0.2516   1.0000
  10.750   1.6916   0.01796   0.01238  -0.1053   0.2449   1.0000
  11.000   1.7043   0.01877   0.01317  -0.1038   0.2355   1.0000
  11.250   1.7127   0.01986   0.01421  -0.1019   0.2220   1.0000
  11.500   1.7172   0.02124   0.01552  -0.0996   0.2047   1.0000
  12.000   1.7031   0.02582   0.01981  -0.0935   0.1547   1.0000
  12.250   1.6937   0.02846   0.02233  -0.0906   0.1321   1.0000
  12.500   1.6730   0.03218   0.02588  -0.0872   0.1002   1.0000
  12.750   1.6592   0.03554   0.02915  -0.0847   0.0803   1.0000
  13.000   1.6523   0.03847   0.03206  -0.0829   0.0675   1.0000
  13.250   1.6346   0.04252   0.03603  -0.0808   0.0471   1.0000
  13.500   1.6125   0.04727   0.04073  -0.0789   0.0280   1.0000
  13.750   1.6057   0.05064   0.04412  -0.0779   0.0216   1.0000
  14.000   1.6039   0.05352   0.04705  -0.0771   0.0192   1.0000
  14.250   1.6010   0.05661   0.05019  -0.0765   0.0171   1.0000
  14.500   1.5998   0.05957   0.05321  -0.0759   0.0158   1.0000
  14.750   1.5980   0.06264   0.05635  -0.0755   0.0150   1.0000
  15.000   1.5946   0.06594   0.05972  -0.0751   0.0141   1.0000
  15.250   1.5914   0.06928   0.06313  -0.0748   0.0135   1.0000
  15.500   1.5885   0.07263   0.06657  -0.0746   0.0131   1.0000
  15.750   1.5839   0.07625   0.07026  -0.0745   0.0124   1.0000
  16.000   1.5786   0.07994   0.07403  -0.0745   0.0120   1.0000
  16.250   1.5728   0.08378   0.07794  -0.0745   0.0117   1.0000
  16.500   1.5652   0.08787   0.08210  -0.0746   0.0111   1.0000
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