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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 500,000
Max Cl/Cd: 101.73 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802a-il-500000.txt
Download as CSV file: xf-goe802a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3150   0.09408   0.09188  -0.0245   1.0000   0.0225
  -8.250  -0.3098   0.09100   0.08883  -0.0267   1.0000   0.0233
  -8.000  -0.3166   0.08886   0.08676  -0.0280   1.0000   0.0237
  -7.750  -0.2926   0.08325   0.08111  -0.0420   0.9913   0.0239
  -7.500  -0.2644   0.07767   0.07546  -0.0528   0.9832   0.0239
  -7.250  -0.2500   0.07332   0.07112  -0.0535   0.9773   0.0241
  -7.000  -0.2327   0.07002   0.06782  -0.0552   0.9693   0.0243
  -6.750  -0.2155   0.06694   0.06471  -0.0576   0.9589   0.0246
  -6.500  -0.1983   0.06390   0.06162  -0.0602   0.9484   0.0250
  -6.250  -0.1819   0.06087   0.05854  -0.0625   0.9364   0.0255
  -6.000  -0.1636   0.05774   0.05532  -0.0649   0.9254   0.0261
  -5.500  -0.1050   0.04990   0.04695  -0.0740   0.9038   0.0285
  -5.250  -0.0890   0.04590   0.04287  -0.0746   0.8942   0.0288
  -5.000  -0.0716   0.04342   0.04036  -0.0746   0.8839   0.0290
  -4.750  -0.0517   0.04122   0.03808  -0.0750   0.8744   0.0294
  -4.500  -0.0297   0.03907   0.03583  -0.0755   0.8646   0.0299
  -4.250  -0.0058   0.03695   0.03358  -0.0761   0.8548   0.0307
  -4.000   0.0278   0.03542   0.03157  -0.0765   0.8452   0.0336
  -3.750   0.0514   0.03216   0.02811  -0.0770   0.8354   0.0340
  -3.500   0.0736   0.02991   0.02581  -0.0772   0.8261   0.0345
  -3.250   0.0980   0.02823   0.02407  -0.0775   0.8156   0.0351
  -3.000   0.1234   0.02679   0.02247  -0.0775   0.8057   0.0363
  -2.750   0.1556   0.02714   0.02234  -0.0767   0.7941   0.0394
  -2.500   0.1791   0.02401   0.01915  -0.0772   0.7830   0.0401
  -2.250   0.2044   0.02260   0.01766  -0.0772   0.7706   0.0410
  -2.000   0.2310   0.02160   0.01653  -0.0772   0.7561   0.0428
  -1.750   0.2600   0.02097   0.01556  -0.0767   0.7410   0.0462
  -1.500   0.2860   0.01962   0.01414  -0.0769   0.7250   0.0471
  -1.250   0.3153   0.02037   0.01458  -0.0762   0.7070   0.0516
  -1.000   0.3415   0.01839   0.01247  -0.0763   0.6889   0.0526
  -0.750   0.3681   0.01733   0.01130  -0.0764   0.6698   0.0540
  -0.500   0.3979   0.01866   0.01226  -0.0756   0.6505   0.0581
  -0.250   0.4238   0.01642   0.00997  -0.0759   0.6330   0.0590
   0.000   0.4509   0.01564   0.00908  -0.0758   0.6154   0.0602
   0.250   0.4787   0.01534   0.00863  -0.0756   0.5988   0.0631
   0.500   0.5072   0.01561   0.00867  -0.0752   0.5831   0.0641
   0.750   0.5333   0.01116   0.00385  -0.0744   0.5717   0.0394
   1.000   0.5598   0.01073   0.00335  -0.0742   0.5574   0.0405
   1.250   0.5873   0.01066   0.00326  -0.0741   0.5431   0.0419
   1.500   0.6148   0.01061   0.00319  -0.0740   0.5294   0.0437
   1.750   0.6421   0.01061   0.00315  -0.0739   0.5153   0.0459
   2.000   0.6697   0.01085   0.00335  -0.0738   0.5001   0.0503
   2.250   0.6974   0.01112   0.00355  -0.0736   0.4850   0.0550
   2.500   0.7254   0.01143   0.00380  -0.0735   0.4705   0.0649
   2.750   0.7535   0.01186   0.00412  -0.0735   0.4570   0.0771
   3.000   0.7810   0.01224   0.00435  -0.0734   0.4438   0.0933
   3.250   0.8073   0.01183   0.00396  -0.0733   0.4306   0.1025
   3.500   0.8337   0.01140   0.00360  -0.0733   0.4191   0.1153
   3.750   0.8604   0.01099   0.00330  -0.0734   0.4092   0.1275
   4.000   0.8872   0.01103   0.00331  -0.0733   0.3991   0.1317
   4.250   0.9143   0.01111   0.00339  -0.0733   0.3894   0.1342
   4.500   0.9407   0.01127   0.00352  -0.0732   0.3782   0.1384
   4.750   0.9674   0.01139   0.00368  -0.0731   0.3669   0.1882
   5.000   0.9939   0.01155   0.00385  -0.0730   0.3573   0.1984
   5.250   1.0204   0.01172   0.00403  -0.0729   0.3484   0.2095
   5.500   1.0468   0.01187   0.00422  -0.0728   0.3399   0.2242
   5.750   1.0729   0.01205   0.00442  -0.0726   0.3304   0.2430
   6.000   1.0904   0.01092   0.00474  -0.0708   0.3229   0.8947
   6.250   1.1214   0.01108   0.00493  -0.0717   0.3117   1.0000
   6.500   1.1475   0.01128   0.00514  -0.0716   0.3019   1.0000
   6.750   1.1727   0.01156   0.00538  -0.0713   0.2913   1.0000
   7.000   1.1980   0.01183   0.00561  -0.0710   0.2781   1.0000
   7.250   1.2224   0.01217   0.00587  -0.0707   0.2589   1.0000
   7.500   1.2463   0.01256   0.00616  -0.0702   0.2353   1.0000
   8.000   1.2911   0.01361   0.00696  -0.0690   0.1906   1.0000
   8.250   1.3131   0.01415   0.00743  -0.0683   0.1754   1.0000
   8.750   1.3574   0.01513   0.00833  -0.0670   0.1533   1.0000
   9.000   1.3789   0.01565   0.00882  -0.0663   0.1435   1.0000
   9.250   1.4003   0.01614   0.00928  -0.0656   0.1343   1.0000
   9.500   1.4219   0.01660   0.00976  -0.0649   0.1261   1.0000
   9.750   1.4417   0.01719   0.01030  -0.0639   0.1163   1.0000
  10.000   1.4621   0.01769   0.01079  -0.0630   0.1064   1.0000
  10.250   1.4807   0.01830   0.01137  -0.0620   0.0950   1.0000
  10.500   1.4973   0.01903   0.01203  -0.0606   0.0823   1.0000
  10.750   1.5122   0.01981   0.01275  -0.0590   0.0721   1.0000
  11.000   1.5242   0.02065   0.01354  -0.0570   0.0634   1.0000
  11.250   1.5347   0.02151   0.01439  -0.0547   0.0564   1.0000
  11.500   1.5455   0.02239   0.01528  -0.0526   0.0486   1.0000
  11.750   1.5503   0.02373   0.01653  -0.0500   0.0318   1.0000
  12.000   1.5479   0.02567   0.01838  -0.0470   0.0222   1.0000
  12.250   1.5538   0.02712   0.01990  -0.0451   0.0201   1.0000
  12.500   1.5601   0.02861   0.02149  -0.0434   0.0191   1.0000
  12.750   1.5648   0.03030   0.02330  -0.0418   0.0184   1.0000
  13.000   1.5675   0.03227   0.02539  -0.0403   0.0178   1.0000
  13.250   1.5683   0.03451   0.02774  -0.0390   0.0172   1.0000
  13.500   1.5668   0.03711   0.03047  -0.0379   0.0167   1.0000
  13.750   1.5626   0.04013   0.03362  -0.0371   0.0164   1.0000
  14.000   1.5620   0.04292   0.03653  -0.0367   0.0162   1.0000
  14.250   1.5597   0.04602   0.03976  -0.0365   0.0159   1.0000
  14.500   1.5553   0.04950   0.04337  -0.0365   0.0157   1.0000
  14.750   1.5493   0.05335   0.04735  -0.0369   0.0155   1.0000
  15.000   1.5412   0.05756   0.05170  -0.0375   0.0152   1.0000
  15.250   1.5321   0.06210   0.05637  -0.0384   0.0150   1.0000
  15.500   1.5214   0.06700   0.06139  -0.0395   0.0148   1.0000
  15.750   1.5099   0.07208   0.06661  -0.0407   0.0147   1.0000
  16.000   1.4973   0.07745   0.07210  -0.0422   0.0145   1.0000
  16.250   1.4841   0.08300   0.07777  -0.0438   0.0144   1.0000
  16.500   1.4704   0.08870   0.08359  -0.0455   0.0143   1.0000
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