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GOE 434 AIRFOIL (goe434-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 434 AIRFOIL (goe434-il)
Reynolds number: 100,000
Max Cl/Cd: 35.99 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe434-il-100000.txt
Download as CSV file: xf-goe434-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 434 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0215   0.11822   0.11249  -0.0946   0.8944   0.2154
 -10.500   0.0568   0.11426   0.10848  -0.0939   0.8855   0.2170
 -10.250  -0.4067   0.04631   0.03937  -0.1384   0.8691   0.1568
 -10.000  -0.4281   0.04168   0.03413  -0.1421   0.8608   0.1587
  -9.750  -0.4251   0.04062   0.03303  -0.1406   0.8500   0.1607
  -9.500  -0.3976   0.03990   0.03241  -0.1406   0.8444   0.1638
  -9.250  -0.3767   0.03831   0.03067  -0.1415   0.8397   0.1674
  -9.000  -0.3722   0.03714   0.02926  -0.1409   0.8312   0.1705
  -8.750  -0.3591   0.03601   0.02798  -0.1405   0.8240   0.1739
  -8.500  -0.3308   0.03549   0.02763  -0.1404   0.8197   0.1783
  -8.250  -0.3061   0.03428   0.02623  -0.1413   0.8160   0.1841
  -8.000  -0.2905   0.03373   0.02567  -0.1405   0.8101   0.1888
  -7.750  -0.2773   0.03386   0.02594  -0.1387   0.8026   0.1936
  -7.500  -0.2569   0.03303   0.02496  -0.1389   0.7975   0.2016
  -7.250  -0.2283   0.03287   0.02500  -0.1389   0.7939   0.2100
  -7.000  -0.1971   0.03248   0.02467  -0.1394   0.7908   0.2212
  -6.750  -0.1854   0.03282   0.02501  -0.1381   0.7845   0.2320
  -6.500  -0.1766   0.03371   0.02601  -0.1359   0.7772   0.2417
  -6.250  -0.1512   0.03433   0.02676  -0.1351   0.7727   0.2534
  -6.000  -0.1188   0.03463   0.02710  -0.1353   0.7692   0.2666
  -5.750  -0.0847   0.03464   0.02701  -0.1361   0.7662   0.2806
  -5.500  -0.0486   0.03550   0.02801  -0.1357   0.7637   0.2896
  -5.250  -0.0760   0.03728   0.02977  -0.1305   0.7518   0.2941
  -5.000  -0.0513   0.03779   0.03036  -0.1297   0.7472   0.3023
  -4.750  -0.0177   0.03820   0.03079  -0.1296   0.7440   0.3117
  -4.500   0.0195   0.03788   0.03040  -0.1308   0.7416   0.3224
  -4.250   0.0563   0.03839   0.03098  -0.1305   0.7392   0.3303
  -4.000   0.0052   0.04134   0.03402  -0.1229   0.7247   0.3308
  -3.750   0.0356   0.04117   0.03367  -0.1241   0.7209   0.3432
  -3.500   0.0705   0.04165   0.03433  -0.1232   0.7182   0.3500
  -3.250   0.1169   0.04094   0.03339  -0.1259   0.7162   0.3648
  -3.000   0.0542   0.04478   0.03738  -0.1170   0.7012   0.3626
  -2.750   0.0771   0.04517   0.03781  -0.1165   0.6968   0.3702
  -2.500   0.1102   0.04553   0.03828  -0.1157   0.6937   0.3783
  -2.250   0.1613   0.04462   0.03717  -0.1189   0.6919   0.3931
  -2.000   0.1201   0.04804   0.04065  -0.1133   0.6790   0.3939
  -1.750   0.1328   0.04923   0.04196  -0.1114   0.6735   0.3993
  -1.500   0.1635   0.04951   0.04224  -0.1112   0.6700   0.4089
  -1.250   0.2064   0.04887   0.04149  -0.1131   0.6676   0.4206
  -1.000   0.2477   0.04860   0.04131  -0.1127   0.6658   0.4288
  -0.750   0.1951   0.05345   0.04622  -0.1082   0.6510   0.4288
  -0.500   0.2224   0.05392   0.04663  -0.1088   0.6468   0.4378
  -0.250   0.2638   0.05344   0.04601  -0.1108   0.6439   0.4465
   0.000   0.3035   0.05298   0.04561  -0.1109   0.6417   0.4528
   0.250   0.2662   0.05741   0.05009  -0.1077   0.6297   0.4540
   0.500   0.2791   0.05880   0.05148  -0.1073   0.6246   0.4594
   0.750   0.3141   0.05896   0.05152  -0.1088   0.6208   0.4678
   1.000   0.3580   0.05834   0.05086  -0.1100   0.6180   0.4749
   1.250   0.4028   0.05769   0.05025  -0.1103   0.6160   0.4826
   1.500   0.3429   0.06377   0.05641  -0.1068   0.6030   0.4814
   1.750   0.3756   0.06380   0.05642  -0.1069   0.5972   0.4903
   2.000   0.4361   0.06189   0.05441  -0.1086   0.5934   0.5015
   2.250   0.4819   0.06068   0.05325  -0.1084   0.5891   0.5097
   2.500   0.4568   0.06397   0.05658  -0.1060   0.5735   0.5120
   2.750   0.5202   0.06140   0.05388  -0.1077   0.5701   0.5213
   3.000   0.5808   0.05881   0.05122  -0.1090   0.5683   0.5290
   3.250   0.6366   0.05641   0.04884  -0.1094   0.5672   0.5373
   3.500   0.5826   0.06293   0.05544  -0.1064   0.5487   0.5374
   3.750   0.5988   0.06404   0.05655  -0.1060   0.5415   0.5436
   4.000   0.6837   0.05936   0.05176  -0.1081   0.5449   0.5550
   4.250   0.6486   0.06440   0.05688  -0.1058   0.5282   0.5566
   4.500   0.6414   0.06724   0.05980  -0.1043   0.5164   0.5606
   4.750   0.6748   0.06660   0.05916  -0.1042   0.5110   0.5702
   5.000   0.7210   0.06476   0.05731  -0.1044   0.5084   0.5815
   5.250   0.7694   0.06251   0.05509  -0.1043   0.5069   0.5937
   5.500   0.8218   0.05981   0.05240  -0.1045   0.5059   0.6075
   5.750   0.8002   0.06386   0.05654  -0.1025   0.4894   0.6123
   6.000   0.8338   0.06292   0.05559  -0.1022   0.4845   0.6276
   6.250   0.9004   0.05818   0.05092  -0.1020   0.4873   0.6488
   6.500   0.9502   0.05497   0.04777  -0.1013   0.4869   0.6691
   6.750   0.8806   0.06418   0.05712  -0.0987   0.4567   0.6678
   7.000   0.9258   0.06144   0.05444  -0.0980   0.4548   0.6906
   7.250   0.9731   0.05823   0.05127  -0.0971   0.4538   0.7175
   7.500   0.9783   0.05953   0.05265  -0.0955   0.4415   0.7365
   7.750   1.0233   0.05637   0.04954  -0.0944   0.4394   0.7717
   8.000   1.0754   0.05228   0.04551  -0.0932   0.4384   0.8155
   8.250   1.1289   0.04746   0.04085  -0.0913   0.4374   0.8967
   8.500   1.2170   0.04179   0.03494  -0.0943   0.4354   1.0000
   8.750   1.2337   0.04245   0.03549  -0.0939   0.4221   1.0000
   9.000   1.3219   0.03781   0.03045  -0.0971   0.4148   1.0000
   9.250   1.3213   0.03955   0.03213  -0.0951   0.3999   1.0000
   9.500   1.3373   0.04030   0.03275  -0.0941   0.3871   1.0000
   9.750   1.3901   0.03862   0.03070  -0.0953   0.3767   1.0000
  10.000   1.3747   0.04160   0.03376  -0.0925   0.3647   1.0000
  10.250   1.4057   0.04152   0.03345  -0.0924   0.3558   1.0000
  10.500   1.4043   0.04370   0.03565  -0.0907   0.3465   1.0000
  10.750   1.4383   0.04345   0.03516  -0.0907   0.3390   1.0000
  11.000   1.4268   0.04644   0.03827  -0.0886   0.3312   1.0000
  11.250   1.4619   0.04605   0.03765  -0.0887   0.3246   1.0000
  11.500   1.4581   0.04864   0.04032  -0.0871   0.3185   1.0000
  11.750   1.4625   0.05063   0.04234  -0.0860   0.3127   1.0000
  12.000   1.5031   0.04990   0.04138  -0.0863   0.3075   1.0000
  12.250   1.4952   0.05290   0.04451  -0.0847   0.3027   1.0000
  12.500   1.4864   0.05604   0.04777  -0.0833   0.2976   1.0000
  12.750   1.5158   0.05602   0.04762  -0.0831   0.2928   1.0000
  13.000   1.5443   0.05630   0.04777  -0.0829   0.2884   1.0000
  13.250   1.5086   0.06177   0.05354  -0.0809   0.2844   1.0000
  13.500   1.5003   0.06509   0.05698  -0.0799   0.2799   1.0000
  13.750   1.5523   0.06292   0.05454  -0.0800   0.2753   1.0000
  14.000   1.5568   0.06521   0.05687  -0.0792   0.2715   1.0000
  14.250   1.4868   0.07476   0.06688  -0.0779   0.2678   1.0000
  14.750   1.4617   0.08340   0.07572  -0.0773   0.2602   1.0000
  15.000   1.5850   0.07342   0.06520  -0.0767   0.2566   1.0000
  15.250   0.9834   0.17332   0.16688  -0.1091   0.2230   1.0000
  15.500   0.9506   0.18391   0.17756  -0.1155   0.2131   1.0000
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