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SIKORSKY GS-1 AIRFOIL (gs1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY GS-1 AIRFOIL (gs1-il)
Reynolds number: 50,000
Max Cl/Cd: 9.2 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gs1-il-50000.txt
Download as CSV file: xf-gs1-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY GS-1 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2698   0.12850   0.12066  -0.0351   1.0000   0.2301
 -10.500  -0.2741   0.12732   0.11955  -0.0351   1.0000   0.2372
 -10.250  -0.2980   0.12813   0.12052  -0.0356   1.0000   0.2402
 -10.000  -0.2636   0.12141   0.11376  -0.0340   1.0000   0.2466
  -9.750  -0.2666   0.11996   0.11238  -0.0335   1.0000   0.2541
  -9.500  -0.3046   0.12257   0.11519  -0.0332   1.0000   0.2575
  -9.250  -0.2653   0.11499   0.10756  -0.0319   1.0000   0.2625
  -9.000  -0.2632   0.11292   0.10556  -0.0306   1.0000   0.2693
  -8.750  -0.2977   0.11465   0.10748  -0.0290   1.0000   0.2749
  -8.500  -0.2737   0.10928   0.10212  -0.0276   1.0000   0.2802
  -8.250  -0.2751   0.10765   0.10057  -0.0255   1.0000   0.2884
  -8.000  -0.3154   0.10954   0.10266  -0.0226   1.0000   0.2931
  -7.750  -0.2908   0.10446   0.09759  -0.0210   1.0000   0.2993
  -7.500  -0.2987   0.10332   0.09655  -0.0184   1.0000   0.3070
  -7.250  -0.3434   0.10523   0.09867  -0.0145   1.0000   0.3114
  -7.000  -0.3280   0.10103   0.09449  -0.0128   1.0000   0.3163
  -6.750  -0.3300   0.09934   0.09287  -0.0101   1.0000   0.3231
  -6.500  -0.3703   0.10054   0.09425  -0.0059   1.0000   0.3292
  -6.250  -0.4249   0.10227   0.09621  -0.0012   1.0000   0.3310
  -6.000  -0.3731   0.09609   0.08994  -0.0010   1.0000   0.3410
  -5.750  -0.4104   0.09659   0.09058   0.0034   1.0000   0.3469
  -5.500  -0.4398   0.09565   0.08978   0.0059   1.0000   0.3511
  -5.250  -0.4245   0.09286   0.08700   0.0086   1.0000   0.3606
  -5.000  -0.4695   0.09287   0.08715   0.0092   1.0000   0.3688
  -4.750  -0.4486   0.08951   0.08380   0.0130   1.0000   0.3768
  -4.500  -0.4708   0.06127   0.05446  -0.0331   1.0000   0.2065
  -4.250  -0.4531   0.05563   0.04837  -0.0377   1.0000   0.2043
  -4.000  -0.4388   0.05348   0.04618  -0.0379   0.9997   0.2084
  -3.750  -0.3955   0.05051   0.04290  -0.0439   0.9900   0.2154
  -3.500  -0.3501   0.04679   0.03857  -0.0510   0.9808   0.2255
  -3.250  -0.3110   0.04483   0.03620  -0.0553   0.9706   0.2378
  -3.000  -0.2772   0.04401   0.03533  -0.0575   0.9601   0.2499
  -2.750  -0.2388   0.04305   0.03413  -0.0607   0.9503   0.2658
  -2.500  -0.2035   0.04230   0.03319  -0.0632   0.9398   0.2829
  -2.250  -0.1730   0.04173   0.03246  -0.0647   0.9295   0.3002
  -2.000  -0.1307   0.04151   0.03210  -0.0679   0.9201   0.3223
  -1.750  -0.1080   0.04116   0.03168  -0.0679   0.9090   0.3400
  -1.500  -0.0747   0.04104   0.03145  -0.0695   0.8993   0.3628
  -1.250  -0.0424   0.04089   0.03114  -0.0710   0.8891   0.3872
  -1.000  -0.0169   0.04086   0.03116  -0.0713   0.8789   0.4089
  -0.750   0.0199   0.04089   0.03118  -0.0731   0.8695   0.4386
  -0.500   0.0382   0.04097   0.03124  -0.0723   0.8591   0.4631
  -0.250   0.0812   0.04100   0.03133  -0.0747   0.8503   0.5027
   0.000   0.0942   0.04123   0.03158  -0.0732   0.8396   0.5322
   0.250   0.1306   0.04129   0.03177  -0.0746   0.8306   0.5792
   0.500   0.1495   0.04147   0.03208  -0.0737   0.8203   0.6239
   0.750   0.1785   0.04140   0.03237  -0.0737   0.8117   0.6915
   1.000   0.2125   0.04079   0.03271  -0.0746   0.8013   1.0000
   1.250   0.2506   0.04187   0.03318  -0.0790   0.7911   1.0000
   1.500   0.2859   0.04281   0.03376  -0.0811   0.7816   1.0000
   1.750   0.3007   0.04401   0.03476  -0.0806   0.7715   1.0000
   2.000   0.3392   0.04489   0.03541  -0.0825   0.7626   1.0000
   2.250   0.3450   0.04631   0.03671  -0.0809   0.7526   1.0000
   2.500   0.3885   0.04708   0.03732  -0.0831   0.7439   1.0000
   2.750   0.3864   0.04875   0.03890  -0.0808   0.7339   1.0000
   3.000   0.4330   0.04949   0.03951  -0.0831   0.7257   1.0000
   3.250   0.4249   0.05140   0.04138  -0.0804   0.7156   1.0000
   3.500   0.4683   0.05222   0.04210  -0.0822   0.7073   1.0000
   3.750   0.4601   0.05431   0.04416  -0.0798   0.6980   1.0000
   4.000   0.5009   0.05519   0.04496  -0.0812   0.6893   1.0000
   4.250   0.4921   0.05748   0.04724  -0.0790   0.6808   1.0000
   4.500   0.5364   0.05828   0.04799  -0.0806   0.6720   1.0000
   4.750   0.5218   0.06092   0.05063  -0.0782   0.6640   1.0000
   5.000   0.5645   0.06180   0.05148  -0.0796   0.6553   1.0000
   5.250   0.5500   0.06464   0.05432  -0.0775   0.6481   1.0000
   5.500   0.5712   0.06632   0.05600  -0.0777   0.6403   1.0000
   5.750   0.5802   0.06854   0.05822  -0.0771   0.6329   1.0000
   6.000   0.5809   0.07111   0.06080  -0.0764   0.6273   1.0000
   6.250   0.6197   0.07240   0.06210  -0.0773   0.6183   1.0000
   6.500   0.6067   0.07571   0.06543  -0.0762   0.6152   1.0000
   6.750   0.6048   0.07874   0.06850  -0.0758   0.6132   1.0000
   7.000   0.6076   0.08198   0.07177  -0.0761   0.6147   1.0000
   7.250   0.6182   0.08533   0.07516  -0.0769   0.6175   1.0000
   7.500   0.5440   0.09356   0.08350  -0.0784   0.7062   1.0000
   7.750   0.5521   0.09525   0.08522  -0.0778   0.6942   1.0000
   8.000   0.5644   0.09796   0.08796  -0.0781   0.6866   1.0000
   8.250   0.5867   0.10059   0.09063  -0.0788   0.6745   1.0000
   8.500   0.5865   0.10256   0.09264  -0.0780   0.6659   1.0000
   8.750   0.6168   0.10603   0.09617  -0.0795   0.6560   1.0000
   9.000   0.6124   0.10753   0.09771  -0.0783   0.6446   1.0000
   9.250   0.6522   0.11232   0.10257  -0.0808   0.6369   1.0000
   9.500   0.6406   0.11293   0.10323  -0.0790   0.6240   1.0000
   9.750   0.6525   0.11596   0.10633  -0.0793   0.6153   1.0000
  10.000   0.6786   0.11931   0.10977  -0.0803   0.6026   1.0000
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