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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 100,000
Max Cl/Cd: 63.49 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610bm-il-100000-n5.txt
Download as CSV file: xf-goe610bm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2952   0.10517   0.10078  -0.0314   1.0000   0.0338
  -7.250  -0.2986   0.10354   0.09923  -0.0314   1.0000   0.0339
  -7.000  -0.3025   0.10186   0.09764  -0.0310   1.0000   0.0340
  -6.750  -0.2928   0.09881   0.09462  -0.0342   0.9969   0.0341
  -6.500  -0.2635   0.09384   0.08960  -0.0425   0.9896   0.0341
  -6.250  -0.2332   0.08875   0.08447  -0.0502   0.9825   0.0342
  -6.000  -0.2012   0.08356   0.07919  -0.0579   0.9758   0.0343
  -5.750  -0.1896   0.07693   0.07262  -0.0580   0.9707   0.0354
  -5.500  -0.1678   0.07272   0.06839  -0.0601   0.9639   0.0369
  -5.250  -0.1395   0.06894   0.06457  -0.0648   0.9565   0.0410
  -5.000  -0.0701   0.06414   0.05944  -0.0853   0.9478   0.0478
  -4.750  -0.0323   0.05945   0.05455  -0.0923   0.9394   0.0480
  -4.500  -0.0157   0.05391   0.04908  -0.0937   0.9319   0.0495
  -4.250   0.0168   0.04996   0.04498  -0.0974   0.9250   0.0459
  -4.000   0.0579   0.04623   0.04098  -0.1050   0.9160   0.0642
  -3.750   0.0929   0.04083   0.03538  -0.1083   0.9097   0.0440
  -3.500   0.1310   0.03648   0.03069  -0.1127   0.9005   0.0424
  -3.250   0.1747   0.03236   0.02598  -0.1173   0.8933   0.0461
  -3.000   0.2108   0.02905   0.02217  -0.1198   0.8844   0.0462
  -2.750   0.2462   0.02638   0.01886  -0.1217   0.8752   0.0491
  -2.500   0.2773   0.02445   0.01668  -0.1228   0.8667   0.0515
  -2.250   0.3084   0.02275   0.01454  -0.1234   0.8559   0.0518
  -2.000   0.3386   0.02143   0.01287  -0.1237   0.8452   0.0526
  -1.750   0.3678   0.02053   0.01170  -0.1238   0.8347   0.0557
  -1.500   0.3970   0.01971   0.01060  -0.1236   0.8241   0.0586
  -1.250   0.4255   0.01888   0.00955  -0.1234   0.8118   0.0584
  -1.000   0.4536   0.01819   0.00867  -0.1231   0.7997   0.0584
  -0.750   0.4816   0.01759   0.00794  -0.1228   0.7876   0.0587
  -0.500   0.5092   0.01709   0.00733  -0.1224   0.7754   0.0593
  -0.250   0.5367   0.01669   0.00681  -0.1220   0.7630   0.0602
   0.000   0.5643   0.01639   0.00638  -0.1216   0.7504   0.0616
   0.250   0.5919   0.01614   0.00602  -0.1213   0.7369   0.0638
   0.500   0.6196   0.01595   0.00572  -0.1210   0.7231   0.0687
   0.750   0.6474   0.01585   0.00549  -0.1208   0.7092   0.0775
   1.000   0.6757   0.01531   0.00547  -0.1210   0.6952   0.2505
   1.500   0.7239   0.01401   0.00534  -0.1190   0.6672   1.0000
   1.750   0.7512   0.01419   0.00535  -0.1188   0.6531   1.0000
   2.000   0.7784   0.01438   0.00539  -0.1186   0.6394   1.0000
   2.250   0.8056   0.01457   0.00547  -0.1184   0.6264   1.0000
   2.500   0.8328   0.01478   0.00556  -0.1182   0.6143   1.0000
   2.750   0.8598   0.01500   0.00567  -0.1179   0.6030   1.0000
   3.000   0.8869   0.01523   0.00586  -0.1178   0.5916   1.0000
   3.250   0.9139   0.01549   0.00605  -0.1176   0.5815   1.0000
   3.500   0.9409   0.01575   0.00623  -0.1174   0.5726   1.0000
   3.750   0.9678   0.01604   0.00653  -0.1173   0.5631   1.0000
   4.000   0.9947   0.01635   0.00681  -0.1172   0.5548   1.0000
   4.250   1.0215   0.01666   0.00713  -0.1170   0.5466   1.0000
   4.500   1.0481   0.01700   0.00748  -0.1169   0.5381   1.0000
   4.750   1.0743   0.01733   0.00781  -0.1166   0.5280   1.0000
   5.000   1.1000   0.01766   0.00817  -0.1162   0.5154   1.0000
   5.250   1.1253   0.01800   0.00854  -0.1158   0.5018   1.0000
   5.500   1.1505   0.01833   0.00897  -0.1154   0.4888   1.0000
   5.750   1.1756   0.01867   0.00938  -0.1149   0.4762   1.0000
   6.000   1.1999   0.01898   0.00977  -0.1143   0.4600   1.0000
   6.250   1.2216   0.01924   0.01002  -0.1132   0.4299   1.0000
   6.500   1.2428   0.01959   0.01037  -0.1122   0.3965   1.0000
   6.750   1.2642   0.02002   0.01080  -0.1112   0.3611   1.0000
   7.000   1.2827   0.02075   0.01130  -0.1099   0.3024   1.0000
   7.250   1.2975   0.02196   0.01211  -0.1082   0.2299   1.0000
   7.500   1.3076   0.02382   0.01346  -0.1061   0.1612   1.0000
   7.750   1.3189   0.02552   0.01486  -0.1042   0.1137   1.0000
   8.000   1.3334   0.02677   0.01608  -0.1025   0.0811   1.0000
   8.250   1.3334   0.02927   0.01808  -0.0991   0.0259   1.0000
   8.500   1.3429   0.03076   0.01965  -0.0967   0.0219   1.0000
   8.750   1.3529   0.03210   0.02120  -0.0943   0.0204   1.0000
   9.000   1.3606   0.03349   0.02281  -0.0916   0.0195   1.0000
   9.250   1.3650   0.03500   0.02453  -0.0886   0.0188   1.0000
   9.500   1.3686   0.03673   0.02648  -0.0858   0.0183   1.0000
   9.750   1.3704   0.03872   0.02867  -0.0832   0.0176   1.0000
  10.000   1.3700   0.04100   0.03117  -0.0808   0.0168   1.0000
  10.250   1.3677   0.04360   0.03397  -0.0786   0.0160   1.0000
  10.500   1.3635   0.04651   0.03708  -0.0767   0.0153   1.0000
  10.750   1.3584   0.04968   0.04044  -0.0751   0.0149   1.0000
  11.000   1.3538   0.05294   0.04388  -0.0738   0.0146   1.0000
  11.250   1.3496   0.05629   0.04746  -0.0727   0.0144   1.0000
  11.500   1.3461   0.05964   0.05095  -0.0715   0.0142   1.0000
  11.750   1.3445   0.06284   0.05427  -0.0703   0.0140   1.0000
  12.000   1.3461   0.06576   0.05731  -0.0688   0.0139   1.0000
  12.250   1.3515   0.06845   0.06011  -0.0670   0.0137   1.0000
  12.500   1.3573   0.07119   0.06297  -0.0656   0.0136   1.0000
  12.750   1.3609   0.07419   0.06617  -0.0648   0.0135   1.0000
  13.000   1.3613   0.07752   0.06973  -0.0643   0.0133   1.0000
  13.250   1.3597   0.08114   0.07358  -0.0642   0.0131   1.0000
  13.500   1.3562   0.08505   0.07774  -0.0644   0.0128   1.0000
  13.750   1.3512   0.08924   0.08217  -0.0649   0.0126   1.0000
  14.000   1.3451   0.09374   0.08690  -0.0657   0.0124   1.0000
  14.250   1.3378   0.09859   0.09198  -0.0669   0.0122   1.0000
  14.500   1.3293   0.10381   0.09745  -0.0686   0.0121   1.0000
  14.750   1.3198   0.10938   0.10325  -0.0707   0.0120   1.0000
  15.000   1.3094   0.11532   0.10941  -0.0733   0.0120   1.0000
  15.250   1.2983   0.12166   0.11598  -0.0764   0.0120   1.0000
  15.500   1.2866   0.12842   0.12295  -0.0800   0.0120   1.0000
  15.750   1.2745   0.13562   0.13036  -0.0842   0.0121   1.0000
  16.000   1.2620   0.14330   0.13824  -0.0890   0.0121   1.0000
  16.250   1.2495   0.15145   0.14657  -0.0943   0.0122   1.0000
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