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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 100,000
Max Cl/Cd: 56.76 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe280-il-100000-n5.txt
Download as CSV file: xf-goe280-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 280 (DAIMLER XI) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3361   0.11302   0.10836  -0.0268   1.0000   0.0272
  -8.250  -0.3350   0.11039   0.10580  -0.0277   1.0000   0.0272
  -8.000  -0.3321   0.10755   0.10301  -0.0290   1.0000   0.0273
  -7.750  -0.3286   0.10465   0.10017  -0.0304   1.0000   0.0273
  -7.500  -0.3252   0.10175   0.09732  -0.0317   1.0000   0.0273
  -7.250  -0.3214   0.09882   0.09444  -0.0328   1.0000   0.0273
  -7.000  -0.3173   0.09587   0.09152  -0.0337   1.0000   0.0273
  -6.750  -0.3126   0.09288   0.08856  -0.0345   1.0000   0.0274
  -6.500  -0.3071   0.08984   0.08552  -0.0352   1.0000   0.0274
  -6.250  -0.3029   0.08604   0.08178  -0.0353   1.0000   0.0275
  -6.000  -0.3042   0.08139   0.07721  -0.0329   1.0000   0.0279
  -5.750  -0.3022   0.07794   0.07379  -0.0312   1.0000   0.0284
  -5.500  -0.2945   0.07455   0.07042  -0.0311   0.9991   0.0290
  -5.250  -0.2641   0.06999   0.06580  -0.0364   0.9933   0.0314
  -5.000  -0.2231   0.06524   0.06092  -0.0449   0.9870   0.0352
  -4.750  -0.1607   0.06157   0.05680  -0.0574   0.9797   0.0385
  -4.500  -0.1187   0.05752   0.05243  -0.0634   0.9741   0.0388
  -4.250  -0.0924   0.05108   0.04600  -0.0672   0.9687   0.0398
  -4.000  -0.0656   0.04717   0.04210  -0.0701   0.9638   0.0437
  -3.750  -0.0177   0.04394   0.03836  -0.0759   0.9572   0.0534
  -3.500   0.0157   0.04003   0.03443  -0.0795   0.9530   0.0577
  -3.000   0.0908   0.03439   0.02824  -0.0862   0.9399   0.0866
  -2.500   0.1751   0.02815   0.02093  -0.0901   0.9261   0.0562
  -2.250   0.2129   0.02626   0.01842  -0.0910   0.9172   0.0535
  -2.000   0.2510   0.02494   0.01669  -0.0923   0.9101   0.0519
  -1.750   0.2814   0.02288   0.01448  -0.0931   0.8987   0.0551
  -1.500   0.3129   0.02171   0.01311  -0.0936   0.8872   0.0567
  -1.250   0.3448   0.02067   0.01174  -0.0937   0.8752   0.0550
  -1.000   0.3752   0.01981   0.01067  -0.0936   0.8619   0.0541
  -0.750   0.4044   0.01903   0.00976  -0.0934   0.8471   0.0538
  -0.500   0.4331   0.01829   0.00893  -0.0931   0.8312   0.0540
  -0.250   0.4615   0.01760   0.00817  -0.0928   0.8145   0.0546
   0.000   0.4896   0.01697   0.00751  -0.0924   0.7971   0.0556
   0.250   0.5169   0.01652   0.00702  -0.0918   0.7778   0.0590
   0.500   0.5445   0.01621   0.00659  -0.0913   0.7581   0.0641
   0.750   0.5721   0.01595   0.00616  -0.0908   0.7381   0.0651
   1.000   0.5993   0.01582   0.00585  -0.0903   0.7161   0.0657
   1.250   0.6267   0.01577   0.00559  -0.0898   0.6943   0.0665
   1.500   0.6537   0.01575   0.00544  -0.0893   0.6706   0.0683
   1.750   0.6804   0.01579   0.00533  -0.0889   0.6462   0.0714
   2.000   0.7068   0.01586   0.00527  -0.0883   0.6200   0.0774
   2.250   0.7277   0.01443   0.00539  -0.0871   0.5936   0.7414
   2.500   0.7522   0.01429   0.00523  -0.0859   0.5645   1.0000
   2.750   0.7776   0.01460   0.00528  -0.0852   0.5370   1.0000
   3.000   0.8032   0.01493   0.00539  -0.0848   0.5132   1.0000
   3.250   0.8291   0.01525   0.00556  -0.0844   0.4932   1.0000
   3.500   0.8548   0.01558   0.00579  -0.0840   0.4741   1.0000
   3.750   0.8805   0.01590   0.00604  -0.0837   0.4542   1.0000
   4.000   0.9060   0.01623   0.00630  -0.0834   0.4343   1.0000
   4.250   0.9312   0.01658   0.00658  -0.0830   0.4145   1.0000
   4.500   0.9564   0.01693   0.00692  -0.0826   0.3941   1.0000
   4.750   0.9812   0.01732   0.00726  -0.0822   0.3735   1.0000
   5.000   1.0058   0.01772   0.00763  -0.0818   0.3524   1.0000
   5.250   1.0300   0.01816   0.00807  -0.0813   0.3312   1.0000
   5.500   1.0533   0.01867   0.00850  -0.0807   0.3056   1.0000
   5.750   1.0743   0.01939   0.00896  -0.0799   0.2652   1.0000
   6.000   1.0943   0.02026   0.00949  -0.0791   0.2214   1.0000
   6.250   1.1153   0.02105   0.01010  -0.0784   0.1897   1.0000
   6.500   1.1364   0.02183   0.01070  -0.0778   0.1630   1.0000
   6.750   1.1568   0.02268   0.01137  -0.0770   0.1382   1.0000
   7.000   1.1779   0.02344   0.01206  -0.0762   0.1210   1.0000
   7.250   1.1979   0.02431   0.01284  -0.0753   0.0976   1.0000
   7.750   1.2283   0.02710   0.01533  -0.0722   0.0220   1.0000
   8.000   1.2448   0.02832   0.01668  -0.0707   0.0194   1.0000
   8.250   1.2612   0.02948   0.01806  -0.0691   0.0175   1.0000
   8.500   1.2775   0.03061   0.01942  -0.0676   0.0166   1.0000
   8.750   1.2924   0.03183   0.02088  -0.0659   0.0161   1.0000
   9.000   1.3052   0.03321   0.02251  -0.0640   0.0156   1.0000
   9.250   1.3154   0.03472   0.02427  -0.0618   0.0153   1.0000
   9.500   1.3233   0.03627   0.02613  -0.0594   0.0150   1.0000
   9.750   1.3265   0.03793   0.02803  -0.0565   0.0145   1.0000
  10.000   1.3275   0.03986   0.03020  -0.0537   0.0140   1.0000
  10.250   1.3265   0.04204   0.03262  -0.0512   0.0137   1.0000
  10.500   1.3234   0.04452   0.03533  -0.0490   0.0134   1.0000
  10.750   1.3186   0.04732   0.03836  -0.0473   0.0133   1.0000
  11.000   1.3124   0.05050   0.04176  -0.0461   0.0132   1.0000
  11.250   1.3048   0.05412   0.04559  -0.0455   0.0132   1.0000
  11.500   1.2960   0.05821   0.04989  -0.0456   0.0131   1.0000
  11.750   1.2864   0.06273   0.05461  -0.0463   0.0131   1.0000
  12.000   1.2761   0.06766   0.05974  -0.0475   0.0130   1.0000
  12.250   1.2654   0.07291   0.06517  -0.0491   0.0130   1.0000
  12.500   1.2547   0.07837   0.07081  -0.0510   0.0130   1.0000
  12.750   1.2444   0.08389   0.07649  -0.0529   0.0130   1.0000
  13.000   1.2349   0.08931   0.08206  -0.0548   0.0130   1.0000
  13.250   1.2270   0.09446   0.08734  -0.0564   0.0130   1.0000
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