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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 50,000
Max Cl/Cd: 22.07 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-50000-n5.txt
Download as CSV file: xf-fx74130wp2-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2092   0.11243   0.10579  -0.0890   0.9361   0.1116
 -10.000  -0.2016   0.10935   0.10265  -0.0912   0.9331   0.1167
  -9.750  -0.2175   0.10776   0.10118  -0.0977   0.9286   0.1211
  -9.500  -0.1916   0.10293   0.09626  -0.0954   0.9268   0.1257
  -9.250  -0.1880   0.10025   0.09359  -0.0964   0.9229   0.1302
  -9.000  -0.2068   0.09836   0.09181  -0.1012   0.9177   0.1359
  -8.750  -0.1853   0.09412   0.08752  -0.1007   0.9163   0.1388
  -8.500  -0.1852   0.09160   0.08502  -0.1006   0.9127   0.1408
  -8.250  -0.1973   0.08512   0.07849  -0.1063   0.9070   0.0734
  -8.000  -0.2061   0.08109   0.07443  -0.1088   0.9027   0.0611
  -7.750  -0.2205   0.07929   0.07266  -0.1068   0.8978   0.0591
  -7.500  -0.2353   0.07705   0.07041  -0.1054   0.8933   0.0568
  -7.250  -0.2522   0.07391   0.06705  -0.1058   0.8891   0.0509
  -7.000  -0.2559   0.07179   0.06487  -0.1034   0.8858   0.0497
  -6.750  -0.2670   0.07019   0.06324  -0.0999   0.8815   0.0488
  -6.500  -0.2714   0.06782   0.06077  -0.0979   0.8784   0.0477
  -6.250  -0.2707   0.06507   0.05785  -0.0967   0.8759   0.0463
  -6.000  -0.2693   0.06242   0.05498  -0.0952   0.8732   0.0450
  -5.750  -0.2813   0.06102   0.05344  -0.0904   0.8689   0.0441
  -5.500  -0.2799   0.05843   0.05055  -0.0881   0.8660   0.0429
  -5.250  -0.2704   0.05561   0.04729  -0.0868   0.8638   0.0415
  -5.000  -0.2536   0.05265   0.04373  -0.0861   0.8617   0.0402
  -4.750  -0.2344   0.05046   0.04102  -0.0854   0.8598   0.0394
  -4.500  -0.2293   0.04893   0.03917  -0.0823   0.8568   0.0393
  -4.250  -0.2153   0.04724   0.03711  -0.0806   0.8546   0.0392
  -4.000  -0.1965   0.04531   0.03482  -0.0796   0.8525   0.0394
  -3.750  -0.1738   0.04351   0.03268  -0.0791   0.8505   0.0399
  -3.500  -0.1495   0.04209   0.03104  -0.0791   0.8487   0.0423
  -3.250  -0.1231   0.04100   0.02965  -0.0791   0.8473   0.0459
  -3.000  -0.1008   0.04012   0.02848  -0.0780   0.8455   0.0488
  -2.750  -0.0861   0.03951   0.02764  -0.0755   0.8429   0.0505
  -2.500  -0.0670   0.03884   0.02681  -0.0737   0.8405   0.0528
  -2.250  -0.0467   0.03828   0.02617  -0.0726   0.8383   0.0581
  -1.750   0.1187   0.03461   0.02551  -0.0859   0.8408   0.9996
  -1.500   0.1248   0.03490   0.02551  -0.0830   0.8375   1.0000
  -1.250   0.1379   0.03516   0.02547  -0.0811   0.8347   1.0000
  -1.000   0.1523   0.03547   0.02549  -0.0796   0.8321   1.0000
  -0.750   0.1398   0.03577   0.02567  -0.0735   0.8272   1.0000
  -0.500   0.1471   0.03606   0.02576  -0.0707   0.8234   1.0000
  -0.250   0.1632   0.03638   0.02585  -0.0694   0.8204   1.0000
   0.000   0.1691   0.03671   0.02600  -0.0664   0.8165   1.0000
   0.250   0.1706   0.03700   0.02617  -0.0627   0.8117   1.0000
   0.500   0.1871   0.03739   0.02637  -0.0615   0.8081   1.0000
   0.750   0.2117   0.03785   0.02661  -0.0616   0.8053   1.0000
   1.000   0.2154   0.03828   0.02693  -0.0585   0.7999   1.0000
   1.250   0.2339   0.03876   0.02727  -0.0578   0.7956   1.0000
   1.500   0.2601   0.03931   0.02768  -0.0583   0.7924   1.0000
   1.750   0.2743   0.03987   0.02812  -0.0570   0.7874   1.0000
   2.000   0.2925   0.04044   0.02860  -0.0564   0.7825   1.0000
   2.250   0.3200   0.04105   0.02912  -0.0570   0.7789   1.0000
   2.500   0.3361   0.04168   0.02969  -0.0562   0.7735   1.0000
   2.750   0.3564   0.04231   0.03028  -0.0559   0.7681   1.0000
   3.000   0.3866   0.04295   0.03086  -0.0569   0.7644   1.0000
   3.250   0.3986   0.04364   0.03153  -0.0555   0.7573   1.0000
   3.500   0.4249   0.04429   0.03217  -0.0560   0.7524   1.0000
   3.750   0.4453   0.04499   0.03287  -0.0557   0.7465   1.0000
   4.000   0.4656   0.04568   0.03360  -0.0555   0.7401   1.0000
   4.500   0.5081   0.04709   0.03508  -0.0552   0.7272   1.0000
   4.750   0.5403   0.04768   0.03572  -0.0563   0.7229   1.0000
   5.000   0.5516   0.04847   0.03662  -0.0550   0.7136   1.0000
   5.250   0.5844   0.04901   0.03724  -0.0561   0.7090   1.0000
   5.500   0.5960   0.04980   0.03811  -0.0549   0.6991   1.0000
   5.750   0.6192   0.05043   0.03885  -0.0549   0.6919   1.0000
   6.000   0.6426   0.05100   0.03955  -0.0549   0.6841   1.0000
   6.250   0.6592   0.05170   0.04043  -0.0541   0.6744   1.0000
   6.500   0.6926   0.05196   0.04086  -0.0550   0.6687   1.0000
   6.750   0.7071   0.05264   0.04169  -0.0540   0.6576   1.0000
   7.000   0.7244   0.05324   0.04246  -0.0533   0.6470   1.0000
   7.250   0.7472   0.05361   0.04302  -0.0530   0.6373   1.0000
   7.500   0.7776   0.05358   0.04328  -0.0532   0.6290   1.0000
   7.750   0.7956   0.05393   0.04385  -0.0523   0.6166   1.0000
   8.000   0.8154   0.05411   0.04426  -0.0515   0.6038   1.0000
   8.250   0.8367   0.05411   0.04451  -0.0507   0.5904   1.0000
   8.500   0.8597   0.05385   0.04458  -0.0497   0.5764   1.0000
   8.750   0.8861   0.05309   0.04413  -0.0487   0.5614   1.0000
   9.000   0.9020   0.05290   0.04423  -0.0470   0.5412   1.0000
   9.250   0.9309   0.05114   0.04282  -0.0452   0.5206   1.0000
   9.500   0.9535   0.04939   0.04137  -0.0427   0.4906   1.0000
   9.750   0.9716   0.04825   0.04048  -0.0400   0.4442   1.0000
  10.000   1.0044   0.04551   0.03738  -0.0367   0.3455   1.0000
  10.250   1.0061   0.04696   0.03806  -0.0337   0.2494   1.0000
  10.500   0.9992   0.04987   0.04042  -0.0315   0.1864   1.0000
  10.750   0.9941   0.05297   0.04311  -0.0299   0.1419   1.0000
  11.000   0.9927   0.05591   0.04579  -0.0285   0.1126   1.0000
  11.250   0.9950   0.05861   0.04838  -0.0272   0.0950   1.0000
  11.500   0.9996   0.06113   0.05083  -0.0262   0.0807   1.0000
  11.750   1.0084   0.06333   0.05308  -0.0251   0.0694   1.0000
  12.000   1.0233   0.06510   0.05499  -0.0239   0.0604   1.0000
  12.250   1.0403   0.06683   0.05688  -0.0229   0.0520   1.0000
  12.500   1.0690   0.06808   0.05830  -0.0218   0.0452   1.0000
  12.750   1.0933   0.07024   0.06080  -0.0210   0.0393   1.0000
  13.000   1.1154   0.07300   0.06392  -0.0203   0.0362   1.0000
  13.250   1.1262   0.07621   0.06736  -0.0198   0.0342   1.0000
  13.500   1.1331   0.08011   0.07141  -0.0195   0.0324   1.0000
  13.750   1.1250   0.08438   0.07614  -0.0190   0.0315   1.0000
  14.000   1.1142   0.08907   0.08122  -0.0190   0.0308   1.0000
  14.250   1.1013   0.09412   0.08662  -0.0194   0.0303   1.0000
  14.500   1.0869   0.09952   0.09232  -0.0204   0.0301   1.0000
  14.750   1.0704   0.10546   0.09854  -0.0221   0.0299   1.0000
  15.000   1.0530   0.11192   0.10524  -0.0246   0.0300   1.0000
  15.250   1.0348   0.11899   0.11252  -0.0279   0.0302   1.0000
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