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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 200,000
Max Cl/Cd: 76.1 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3024-il-200000-n5.txt
Download as CSV file: xf-s3024-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL 3024    9.84%                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3310   0.09718   0.09370  -0.0389   1.0000   0.0261
  -9.000  -0.3300   0.09403   0.09061  -0.0399   1.0000   0.0263
  -8.750  -0.3407   0.09079   0.08746  -0.0426   1.0000   0.0292
  -8.250  -0.3243   0.08031   0.07703  -0.0564   0.9796   0.0296
  -7.750  -0.3070   0.06622   0.06290  -0.0678   0.9620   0.0181
  -7.500  -0.2938   0.06186   0.05850  -0.0733   0.9527   0.0177
  -7.250  -0.2820   0.05606   0.05261  -0.0799   0.9432   0.0170
  -7.000  -0.2733   0.04979   0.04616  -0.0848   0.9331   0.0163
  -6.500  -0.2697   0.03195   0.02693  -0.0888   0.9122   0.0140
  -6.250  -0.2541   0.02881   0.02334  -0.0883   0.9056   0.0139
  -6.000  -0.2359   0.02613   0.02021  -0.0876   0.8999   0.0139
  -5.750  -0.2159   0.02386   0.01747  -0.0868   0.8935   0.0139
  -5.500  -0.1934   0.02202   0.01521  -0.0860   0.8886   0.0140
  -5.250  -0.1709   0.02030   0.01320  -0.0852   0.8830   0.0143
  -5.000  -0.1471   0.01900   0.01170  -0.0846   0.8774   0.0146
  -4.750  -0.1224   0.01798   0.01052  -0.0840   0.8730   0.0151
  -4.500  -0.0976   0.01728   0.00970  -0.0835   0.8671   0.0164
  -4.250  -0.0723   0.01652   0.00879  -0.0829   0.8617   0.0176
  -4.000  -0.0468   0.01573   0.00787  -0.0822   0.8575   0.0181
  -3.750  -0.0222   0.01500   0.00707  -0.0817   0.8511   0.0188
  -3.500   0.0033   0.01441   0.00641  -0.0811   0.8458   0.0199
  -3.250   0.0294   0.01394   0.00585  -0.0806   0.8413   0.0214
  -2.750   0.0817   0.01314   0.00493  -0.0798   0.8296   0.0301
  -2.500   0.1076   0.01264   0.00452  -0.0794   0.8242   0.0539
  -2.250   0.1333   0.01220   0.00426  -0.0790   0.8178   0.1043
  -2.000   0.1587   0.01167   0.00405  -0.0787   0.8129   0.1938
  -1.750   0.1832   0.01117   0.00395  -0.0784   0.8059   0.3036
  -1.500   0.2082   0.01076   0.00381  -0.0778   0.7999   0.3989
  -1.250   0.2318   0.01028   0.00373  -0.0770   0.7934   0.5219
  -1.000   0.2530   0.00974   0.00369  -0.0753   0.7865   0.6744
  -0.750   0.2776   0.00931   0.00367  -0.0737   0.7805   0.8361
  -0.500   0.3304   0.00915   0.00355  -0.0783   0.7736   0.9549
  -0.250   0.3780   0.00908   0.00333  -0.0823   0.7674   0.9937
   0.000   0.4082   0.00910   0.00326  -0.0829   0.7583   1.0000
   0.250   0.4330   0.00912   0.00317  -0.0821   0.7500   1.0000
   0.500   0.4578   0.00916   0.00311  -0.0814   0.7406   1.0000
   0.750   0.4827   0.00920   0.00308  -0.0808   0.7304   1.0000
   1.000   0.5077   0.00925   0.00303  -0.0801   0.7204   1.0000
   1.250   0.5329   0.00930   0.00300  -0.0794   0.7098   1.0000
   1.500   0.5580   0.00937   0.00300  -0.0788   0.6980   1.0000
   1.750   0.5833   0.00944   0.00301  -0.0782   0.6861   1.0000
   2.000   0.6086   0.00952   0.00304  -0.0776   0.6737   1.0000
   2.250   0.6339   0.00961   0.00306  -0.0770   0.6605   1.0000
   2.500   0.6591   0.00972   0.00311  -0.0764   0.6464   1.0000
   2.750   0.6843   0.00984   0.00317  -0.0758   0.6312   1.0000
   3.000   0.7093   0.00997   0.00325  -0.0752   0.6149   1.0000
   3.250   0.7342   0.01013   0.00334  -0.0746   0.5977   1.0000
   3.500   0.7588   0.01031   0.00344  -0.0739   0.5796   1.0000
   3.750   0.7832   0.01051   0.00358  -0.0732   0.5606   1.0000
   4.000   0.8075   0.01073   0.00374  -0.0725   0.5405   1.0000
   4.250   0.8313   0.01098   0.00392  -0.0718   0.5199   1.0000
   4.500   0.8549   0.01125   0.00412  -0.0710   0.4987   1.0000
   4.750   0.8782   0.01154   0.00436  -0.0702   0.4764   1.0000
   5.000   0.9011   0.01186   0.00461  -0.0694   0.4536   1.0000
   5.250   0.9235   0.01222   0.00489  -0.0685   0.4297   1.0000
   5.500   0.9458   0.01258   0.00521  -0.0676   0.4062   1.0000
   5.750   0.9674   0.01299   0.00554  -0.0666   0.3830   1.0000
   6.000   0.9890   0.01340   0.00589  -0.0656   0.3593   1.0000
   6.250   1.0100   0.01385   0.00628  -0.0646   0.3365   1.0000
   6.500   1.0307   0.01431   0.00671  -0.0636   0.3143   1.0000
   6.750   1.0511   0.01479   0.00715  -0.0625   0.2937   1.0000
   7.000   1.0709   0.01531   0.00761  -0.0613   0.2711   1.0000
   7.250   1.0893   0.01590   0.00812  -0.0600   0.2452   1.0000
   7.500   1.1068   0.01655   0.00868  -0.0586   0.2178   1.0000
   7.750   1.1235   0.01725   0.00925  -0.0571   0.1903   1.0000
   8.250   1.1568   0.01862   0.01049  -0.0542   0.1469   1.0000
   8.500   1.1713   0.01941   0.01118  -0.0525   0.1248   1.0000
   8.750   1.1848   0.02019   0.01191  -0.0506   0.1049   1.0000
   9.000   1.1960   0.02108   0.01271  -0.0484   0.0846   1.0000
   9.250   1.2067   0.02203   0.01358  -0.0462   0.0665   1.0000
   9.500   1.2169   0.02305   0.01454  -0.0441   0.0500   1.0000
   9.750   1.2249   0.02427   0.01568  -0.0418   0.0344   1.0000
  10.000   1.2321   0.02558   0.01696  -0.0396   0.0234   1.0000
  10.250   1.2408   0.02681   0.01826  -0.0376   0.0193   1.0000
  10.750   1.2572   0.02943   0.02104  -0.0339   0.0155   1.0000
  11.000   1.2650   0.03081   0.02254  -0.0322   0.0144   1.0000
  11.250   1.2702   0.03244   0.02426  -0.0305   0.0134   1.0000
  11.500   1.2744   0.03420   0.02614  -0.0289   0.0129   1.0000
  11.750   1.2790   0.03598   0.02807  -0.0274   0.0126   1.0000
  12.000   1.2825   0.03791   0.03018  -0.0261   0.0122   1.0000
  12.250   1.2849   0.04001   0.03241  -0.0249   0.0121   1.0000
  12.500   1.2857   0.04236   0.03492  -0.0239   0.0118   1.0000
  12.750   1.2859   0.04485   0.03755  -0.0231   0.0116   1.0000
  13.000   1.2849   0.04758   0.04042  -0.0225   0.0114   1.0000
  13.250   1.2835   0.05046   0.04344  -0.0221   0.0112   1.0000
  13.500   1.2807   0.05363   0.04675  -0.0219   0.0110   1.0000
  13.750   1.2782   0.05688   0.05013  -0.0219   0.0109   1.0000
  14.000   1.2751   0.06035   0.05374  -0.0222   0.0107   1.0000
  14.250   1.2715   0.06404   0.05756  -0.0227   0.0106   1.0000
  14.500   1.2684   0.06779   0.06144  -0.0234   0.0105   1.0000
  14.750   1.2645   0.07174   0.06555  -0.0243   0.0104   1.0000
  15.000   1.2600   0.07595   0.06988  -0.0253   0.0103   1.0000
  15.250   1.2558   0.08021   0.07426  -0.0266   0.0101   1.0000
  15.500   1.2503   0.08472   0.07888  -0.0280   0.0099   1.0000
  15.750   1.2457   0.08923   0.08353  -0.0295   0.0099   1.0000
  16.000   1.2398   0.09407   0.08849  -0.0312   0.0097   1.0000
  16.250   1.2337   0.09925   0.09386  -0.0335   0.0096   1.0000
  16.500   1.2277   0.10446   0.09924  -0.0358   0.0095   1.0000
  16.750   1.2200   0.11022   0.10519  -0.0387   0.0094   1.0000
  17.000   1.2116   0.11626   0.11141  -0.0418   0.0093   1.0000
  17.250   1.2033   0.12241   0.11773  -0.0451   0.0093   1.0000
  17.500   1.1945   0.12877   0.12426  -0.0486   0.0093   1.0000
  17.750   1.1843   0.13567   0.13133  -0.0526   0.0092   1.0000
  18.000   1.1744   0.14271   0.13853  -0.0568   0.0092   1.0000
  18.250   1.1631   0.15034   0.14632  -0.0615   0.0092   1.0000
  18.500   1.1518   0.15820   0.15434  -0.0664   0.0093   1.0000
  18.750   1.1397   0.16658   0.16287  -0.0717   0.0093   1.0000
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