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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 100,000
Max Cl/Cd: 59.47 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe180-il-100000-n5.txt
Download as CSV file: xf-goe180-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3435   0.09481   0.09009  -0.0284   1.0000   0.0576
  -7.500  -0.3539   0.09302   0.08842  -0.0321   1.0000   0.0585
  -7.250  -0.3555   0.09019   0.08566  -0.0366   1.0000   0.0589
  -7.000  -0.3533   0.08692   0.08240  -0.0396   1.0000   0.0590
  -6.750  -0.3518   0.08289   0.07847  -0.0340   1.0000   0.0599
  -6.500  -0.3489   0.08020   0.07583  -0.0315   1.0000   0.0609
  -6.250  -0.3466   0.07762   0.07329  -0.0305   1.0000   0.0620
  -6.000  -0.3437   0.07495   0.07066  -0.0305   1.0000   0.0632
  -5.750  -0.2908   0.06880   0.06411  -0.0507   0.9915   0.0712
  -5.500  -0.2683   0.05846   0.05368  -0.0551   0.9865   0.0492
  -5.250  -0.2389   0.05421   0.04931  -0.0589   0.9798   0.0458
  -5.000  -0.2006   0.04811   0.04289  -0.0664   0.9727   0.0462
  -4.750  -0.1617   0.04228   0.03667  -0.0727   0.9661   0.0465
  -4.500  -0.1266   0.03743   0.03140  -0.0769   0.9582   0.0460
  -4.250  -0.0849   0.03237   0.02557  -0.0816   0.9527   0.0477
  -4.000  -0.0505   0.02911   0.02171  -0.0838   0.9441   0.0481
  -3.750  -0.0110   0.02630   0.01839  -0.0867   0.9388   0.0484
  -3.500   0.0223   0.02432   0.01612  -0.0882   0.9296   0.0493
  -3.250   0.0597   0.02310   0.01476  -0.0904   0.9226   0.0519
  -3.000   0.0942   0.02172   0.01308  -0.0916   0.9128   0.0533
  -2.750   0.1298   0.02037   0.01144  -0.0928   0.9029   0.0540
  -2.500   0.1671   0.01919   0.01003  -0.0944   0.8936   0.0551
  -2.250   0.1999   0.01829   0.00896  -0.0950   0.8804   0.0564
  -2.000   0.2321   0.01753   0.00808  -0.0955   0.8662   0.0580
  -1.750   0.2634   0.01692   0.00745  -0.0960   0.8507   0.0615
  -1.500   0.2940   0.01643   0.00692  -0.0962   0.8333   0.0654
  -1.250   0.3226   0.01598   0.00638  -0.0959   0.8130   0.0688
  -1.000   0.3520   0.01555   0.00587  -0.0958   0.7922   0.0736
  -0.750   0.3812   0.01520   0.00543  -0.0956   0.7707   0.0840
  -0.500   0.4098   0.01483   0.00508  -0.0954   0.7487   0.1113
  -0.250   0.4385   0.01444   0.00486  -0.0954   0.7273   0.1951
   0.000   0.4602   0.01297   0.00488  -0.0943   0.7070   0.6675
   0.250   0.4934   0.01253   0.00463  -0.0943   0.6870   1.0000
   0.500   0.5211   0.01271   0.00453  -0.0940   0.6690   1.0000
   0.750   0.5483   0.01291   0.00449  -0.0937   0.6523   1.0000
   1.000   0.5753   0.01312   0.00448  -0.0933   0.6361   1.0000
   1.250   0.6021   0.01334   0.00451  -0.0929   0.6212   1.0000
   1.750   0.6555   0.01381   0.00466  -0.0922   0.5944   1.0000
   2.000   0.6821   0.01405   0.00479  -0.0919   0.5825   1.0000
   2.250   0.7087   0.01430   0.00492  -0.0915   0.5712   1.0000
   2.500   0.7351   0.01457   0.00506  -0.0912   0.5603   1.0000
   2.750   0.7614   0.01481   0.00525  -0.0908   0.5491   1.0000
   3.000   0.7878   0.01507   0.00546  -0.0905   0.5393   1.0000
   3.250   0.8144   0.01535   0.00567  -0.0902   0.5311   1.0000
   3.500   0.8407   0.01561   0.00595  -0.0899   0.5217   1.0000
   3.750   0.8668   0.01589   0.00619  -0.0895   0.5125   1.0000
   4.000   0.8926   0.01617   0.00645  -0.0891   0.5022   1.0000
   4.250   0.9183   0.01644   0.00676  -0.0887   0.4917   1.0000
   4.500   0.9437   0.01672   0.00704  -0.0882   0.4810   1.0000
   4.750   0.9688   0.01700   0.00731  -0.0876   0.4694   1.0000
   5.000   0.9935   0.01727   0.00765  -0.0870   0.4563   1.0000
   5.250   1.0181   0.01755   0.00798  -0.0864   0.4431   1.0000
   5.500   1.0425   0.01784   0.00832  -0.0858   0.4298   1.0000
   5.750   1.0666   0.01813   0.00869  -0.0851   0.4155   1.0000
   6.000   1.0905   0.01844   0.00907  -0.0844   0.4009   1.0000
   6.250   1.1141   0.01877   0.00947  -0.0836   0.3848   1.0000
   6.500   1.1371   0.01912   0.00988  -0.0828   0.3671   1.0000
   6.750   1.1595   0.01951   0.01032  -0.0819   0.3484   1.0000
   7.000   1.1818   0.01994   0.01082  -0.0810   0.3282   1.0000
   7.250   1.2032   0.02043   0.01133  -0.0800   0.3095   1.0000
   7.500   1.2239   0.02101   0.01191  -0.0789   0.2930   1.0000
   7.750   1.2442   0.02165   0.01259  -0.0777   0.2788   1.0000
   8.000   1.2642   0.02234   0.01332  -0.0766   0.2664   1.0000
   8.250   1.2839   0.02308   0.01413  -0.0754   0.2555   1.0000
   8.500   1.3017   0.02390   0.01497  -0.0740   0.2413   1.0000
   8.750   1.3171   0.02479   0.01586  -0.0724   0.2214   1.0000
   9.000   1.3305   0.02575   0.01678  -0.0706   0.1997   1.0000
   9.250   1.3471   0.02650   0.01767  -0.0692   0.1793   1.0000
   9.500   1.3616   0.02737   0.01859  -0.0676   0.1574   1.0000
   9.750   1.3719   0.02852   0.01966  -0.0655   0.1317   1.0000
  10.000   1.3771   0.03006   0.02107  -0.0629   0.1040   1.0000
  10.250   1.3749   0.03204   0.02279  -0.0594   0.0595   1.0000
  10.500   1.3693   0.03441   0.02499  -0.0559   0.0463   1.0000
  10.750   1.3672   0.03660   0.02729  -0.0530   0.0400   1.0000
  11.000   1.3618   0.03917   0.02995  -0.0504   0.0363   1.0000
  11.250   1.3605   0.04154   0.03250  -0.0485   0.0334   1.0000
  11.500   1.3570   0.04425   0.03539  -0.0470   0.0313   1.0000
  11.750   1.3513   0.04737   0.03868  -0.0459   0.0300   1.0000
  12.000   1.3430   0.05101   0.04247  -0.0453   0.0290   1.0000
  12.250   1.3324   0.05517   0.04678  -0.0452   0.0282   1.0000
  12.500   1.3264   0.05902   0.05082  -0.0455   0.0274   1.0000
  12.750   1.3199   0.06308   0.05508  -0.0460   0.0266   1.0000
  13.000   1.3128   0.06734   0.05952  -0.0467   0.0257   1.0000
  13.250   1.3053   0.07174   0.06408  -0.0475   0.0249   1.0000
  13.500   1.2976   0.07623   0.06872  -0.0485   0.0242   1.0000
  13.750   1.2898   0.08080   0.07342  -0.0495   0.0235   1.0000
  14.000   1.2823   0.08537   0.07811  -0.0506   0.0229   1.0000
  14.250   1.2755   0.08984   0.08268  -0.0517   0.0223   1.0000
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