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GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 482 AIRFOIL (goe482-il)
Reynolds number: 500,000
Max Cl/Cd: 107.28 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe482-il-500000.txt
Download as CSV file: xf-goe482-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 482 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2069   0.09426   0.09070  -0.1334   0.7824   0.0425
 -10.750   0.2181   0.09249   0.08888  -0.1340   0.7771   0.0437
 -10.500   0.1926   0.08808   0.08451  -0.1386   0.7723   0.0467
 -10.250   0.2074   0.08545   0.08188  -0.1382   0.7672   0.0471
 -10.000   0.2256   0.08381   0.08018  -0.1378   0.7622   0.0475
  -9.750   0.2409   0.08236   0.07872  -0.1377   0.7572   0.0482
  -9.500   0.2521   0.08071   0.07707  -0.1379   0.7514   0.0494
  -9.250   0.2308   0.07689   0.07325  -0.1422   0.7460   0.0529
  -9.000   0.2346   0.07344   0.06978  -0.1427   0.7408   0.0534
  -8.750   0.2511   0.07205   0.06839  -0.1419   0.7344   0.0538
  -8.500   0.2656   0.07066   0.06696  -0.1416   0.7282   0.0543
  -8.250   0.2776   0.06914   0.06543  -0.1415   0.7220   0.0549
  -8.000   0.2875   0.06751   0.06380  -0.1415   0.7151   0.0560
  -7.750   0.2935   0.06562   0.06187  -0.1419   0.7084   0.0576
  -7.500   0.2493   0.05945   0.05578  -0.1459   0.7018   0.0606
  -7.250   0.2625   0.05811   0.05441  -0.1448   0.6940   0.0610
  -7.000   0.2760   0.05695   0.05323  -0.1442   0.6862   0.0615
  -6.750   0.2877   0.05558   0.05183  -0.1440   0.6774   0.0620
  -6.500   0.2729   0.04132   0.03743  -0.1690   0.6712   0.0690
  -6.250   0.2903   0.04077   0.03691  -0.1670   0.6619   0.0694
  -6.000   0.3085   0.04050   0.03659  -0.1656   0.6533   0.0698
  -5.750   0.3323   0.02100   0.01547  -0.1909   0.6469   0.0610
  -5.500   0.3596   0.01980   0.01397  -0.1917   0.6379   0.0608
  -5.250   0.3871   0.01848   0.01244  -0.1925   0.6284   0.0610
  -5.000   0.4141   0.01750   0.01130  -0.1930   0.6197   0.0616
  -4.750   0.4419   0.01673   0.01039  -0.1933   0.6109   0.0620
  -4.500   0.4694   0.01610   0.00959  -0.1935   0.6028   0.0623
  -4.250   0.4973   0.01554   0.00890  -0.1937   0.5946   0.0626
  -4.000   0.5247   0.01513   0.00834  -0.1938   0.5874   0.0631
  -3.750   0.5529   0.01469   0.00783  -0.1939   0.5803   0.0637
  -3.500   0.5804   0.01436   0.00738  -0.1940   0.5735   0.0643
  -3.250   0.6083   0.01407   0.00699  -0.1940   0.5677   0.0649
  -3.000   0.6363   0.01382   0.00668  -0.1941   0.5616   0.0659
  -2.750   0.6639   0.01365   0.00640  -0.1940   0.5561   0.0668
  -2.500   0.6917   0.01347   0.00615  -0.1940   0.5510   0.0675
  -2.250   0.7198   0.01330   0.00593  -0.1940   0.5459   0.0681
  -2.000   0.7475   0.01317   0.00573  -0.1940   0.5412   0.0687
  -1.750   0.7750   0.01283   0.00532  -0.1941   0.5365   0.0700
  -1.500   0.8031   0.01264   0.00515  -0.1942   0.5324   0.0714
  -1.250   0.8310   0.01253   0.00504  -0.1942   0.5279   0.0728
  -1.000   0.8586   0.01250   0.00497  -0.1942   0.5236   0.0747
  -0.750   0.8859   0.01254   0.00494  -0.1941   0.5194   0.0766
  -0.500   0.9138   0.01252   0.00490  -0.1941   0.5158   0.0780
  -0.250   0.9418   0.01238   0.00478  -0.1943   0.5120   0.0810
   0.000   0.9693   0.01236   0.00475  -0.1942   0.5079   0.0843
   0.250   0.9963   0.01242   0.00475  -0.1941   0.5038   0.0882
   0.500   1.0238   0.01246   0.00479  -0.1941   0.4999   0.0969
   0.750   1.0514   0.01234   0.00485  -0.1942   0.4964   0.1404
   1.000   1.0789   0.01220   0.00494  -0.1944   0.4927   0.2235
   1.250   1.1057   0.01217   0.00512  -0.1944   0.4890   0.3276
   1.500   1.1318   0.01235   0.00529  -0.1942   0.4852   0.3652
   1.750   1.1581   0.01246   0.00544  -0.1939   0.4816   0.3887
   2.000   1.1840   0.01252   0.00556  -0.1936   0.4779   0.4099
   2.250   1.2096   0.01261   0.00567  -0.1933   0.4739   0.4277
   2.500   1.2348   0.01274   0.00580  -0.1929   0.4702   0.4458
   2.750   1.2603   0.01293   0.00599  -0.1926   0.4662   0.4672
   3.000   1.2852   0.01296   0.00615  -0.1922   0.4630   0.4967
   3.250   1.3099   0.01301   0.00635  -0.1918   0.4592   0.5521
   3.500   1.3339   0.01306   0.00655  -0.1912   0.4555   0.6254
   3.750   1.3549   0.01298   0.00680  -0.1900   0.4518   0.7816
   4.000   1.3777   0.01293   0.00694  -0.1891   0.4480   1.0000
   4.250   1.4010   0.01309   0.00710  -0.1884   0.4442   1.0000
   4.500   1.4236   0.01327   0.00726  -0.1876   0.4401   1.0000
   4.750   1.4445   0.01351   0.00744  -0.1865   0.4361   1.0000
   5.000   1.4655   0.01381   0.00768  -0.1854   0.4322   1.0000
   5.250   1.4855   0.01400   0.00789  -0.1841   0.4287   1.0000
   5.500   1.5053   0.01422   0.00812  -0.1829   0.4248   1.0000
   5.750   1.5243   0.01450   0.00837  -0.1815   0.4210   1.0000
   6.000   1.5431   0.01486   0.00867  -0.1802   0.4171   1.0000
   6.250   1.5623   0.01514   0.00898  -0.1789   0.4136   1.0000
   6.500   1.5811   0.01543   0.00929  -0.1776   0.4097   1.0000
   6.750   1.5989   0.01577   0.00963  -0.1762   0.4057   1.0000
   7.000   1.6159   0.01620   0.01001  -0.1747   0.4018   1.0000
   7.250   1.6337   0.01661   0.01043  -0.1734   0.3981   1.0000
   7.500   1.6513   0.01699   0.01084  -0.1721   0.3945   1.0000
   7.750   1.6685   0.01742   0.01129  -0.1708   0.3909   1.0000
   8.000   1.6846   0.01792   0.01177  -0.1693   0.3873   1.0000
   8.250   1.7015   0.01849   0.01229  -0.1681   0.3834   1.0000
   8.500   1.7171   0.01898   0.01286  -0.1666   0.3802   1.0000
   8.750   1.7313   0.01955   0.01346  -0.1651   0.3756   1.0000
   9.000   1.7436   0.02026   0.01415  -0.1634   0.3707   1.0000
   9.250   1.7562   0.02102   0.01490  -0.1618   0.3659   1.0000
   9.500   1.7700   0.02170   0.01565  -0.1604   0.3617   1.0000
   9.750   1.7827   0.02249   0.01646  -0.1589   0.3573   1.0000
  10.000   1.7933   0.02345   0.01738  -0.1573   0.3527   1.0000
  10.250   1.8057   0.02432   0.01831  -0.1560   0.3485   1.0000
  10.500   1.8183   0.02521   0.01925  -0.1547   0.3441   1.0000
  10.750   1.8279   0.02630   0.02035  -0.1532   0.3394   1.0000
  11.000   1.8370   0.02747   0.02150  -0.1517   0.3350   1.0000
  11.250   1.8498   0.02843   0.02256  -0.1506   0.3315   1.0000
  11.500   1.8594   0.02962   0.02379  -0.1493   0.3267   1.0000
  11.750   1.8666   0.03101   0.02517  -0.1478   0.3221   1.0000
  12.000   1.8751   0.03236   0.02656  -0.1465   0.3180   1.0000
  12.250   1.8857   0.03358   0.02787  -0.1455   0.3138   1.0000
  12.500   1.8924   0.03514   0.02946  -0.1442   0.3091   1.0000
  12.750   1.8959   0.03698   0.03129  -0.1428   0.3043   1.0000
  13.000   1.9046   0.03850   0.03290  -0.1418   0.2994   1.0000
  13.250   1.9077   0.04052   0.03496  -0.1406   0.2931   1.0000
  13.500   1.9083   0.04282   0.03728  -0.1393   0.2868   1.0000
  13.750   1.9126   0.04490   0.03943  -0.1384   0.2801   1.0000
  14.000   1.9084   0.04785   0.04237  -0.1371   0.2732   1.0000
  14.250   1.9107   0.05027   0.04487  -0.1363   0.2650   1.0000
  14.500   1.9039   0.05371   0.04832  -0.1353   0.2561   1.0000
  14.750   1.8928   0.05777   0.05239  -0.1343   0.2442   1.0000
  15.000   1.8805   0.06213   0.05675  -0.1335   0.2309   1.0000
  15.250   1.8619   0.06739   0.06199  -0.1329   0.2159   1.0000
  15.500   1.8388   0.07342   0.06799  -0.1324   0.2004   1.0000
  15.750   1.8135   0.07994   0.07450  -0.1323   0.1847   1.0000
  16.000   1.7877   0.08674   0.08127  -0.1324   0.1705   1.0000
  16.250   1.7632   0.09353   0.08805  -0.1329   0.1575   1.0000
  16.500   1.7395   0.10038   0.09490  -0.1335   0.1448   1.0000
  16.750   1.7170   0.10722   0.10173  -0.1345   0.1310   1.0000
  17.000   1.6922   0.11453   0.10899  -0.1358   0.1142   1.0000
  17.250   1.6629   0.12270   0.11708  -0.1375   0.0937   1.0000
  17.500   1.6334   0.13102   0.12532  -0.1397   0.0709   1.0000
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