Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 77-W-270S (fx77w270s-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-270S (fx77w270s-il)
Reynolds number: 100,000
Max Cl/Cd: 1.19 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w270s-il-100000.txt
Download as CSV file: xf-fx77w270s-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-270S                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.6219   0.09476   0.08828  -0.0617   0.6549   0.0807
 -14.750  -0.6484   0.08859   0.08192  -0.0636   0.6526   0.0803
 -14.500  -0.6781   0.08277   0.07586  -0.0649   0.6506   0.0800
 -14.250  -0.7072   0.07749   0.07033  -0.0654   0.6484   0.0796
 -14.000  -0.7334   0.07283   0.06542  -0.0654   0.6458   0.0794
 -13.750  -0.7551   0.06880   0.06113  -0.0648   0.6428   0.0794
 -13.500  -0.7718   0.06532   0.05738  -0.0638   0.6396   0.0794
 -13.250  -0.7848   0.06225   0.05403  -0.0625   0.6362   0.0796
 -13.000  -0.7942   0.05952   0.05099  -0.0609   0.6329   0.0798
 -12.750  -0.7998   0.05710   0.04824  -0.0591   0.6296   0.0800
 -12.500  -0.8019   0.05496   0.04577  -0.0572   0.6264   0.0803
 -12.250  -0.8015   0.05296   0.04351  -0.0552   0.6230   0.0806
 -12.000  -0.7841   0.05113   0.04158  -0.0549   0.6186   0.0815
 -11.750  -0.7548   0.04983   0.04032  -0.0556   0.6139   0.0829
 -11.500  -0.7348   0.04859   0.03898  -0.0553   0.6102   0.0842
 -11.250  -0.7182   0.04731   0.03752  -0.0546   0.6072   0.0856
 -11.000  -0.7024   0.04610   0.03607  -0.0536   0.6046   0.0869
 -10.750  -0.6882   0.04499   0.03471  -0.0524   0.6022   0.0882
 -10.500  -0.6519   0.04371   0.03351  -0.0541   0.5993   0.0904
 -10.250  -0.6219   0.04285   0.03270  -0.0549   0.5964   0.0928
 -10.000  -0.5961   0.04200   0.03177  -0.0550   0.5938   0.0956
  -9.750  -0.5668   0.04113   0.03086  -0.0555   0.5910   0.0987
  -9.500  -0.5363   0.04051   0.03033  -0.0561   0.5881   0.1024
  -9.250  -0.5126   0.03984   0.02951  -0.0558   0.5855   0.1065
  -9.000  -0.4767   0.03935   0.02919  -0.0566   0.5827   0.1114
  -8.750  -0.4506   0.03897   0.02869  -0.0564   0.5805   0.1170
  -8.500  -0.4176   0.03862   0.02863  -0.0567   0.5786   0.1240
  -8.250  -0.3916   0.03817   0.02838  -0.0565   0.5769   0.1332
  -8.000  -0.3713   0.03763   0.02806  -0.0558   0.5752   0.1461
  -7.750  -0.3560   0.03696   0.02764  -0.0547   0.5737   0.1644
  -7.500  -0.3459   0.03612   0.02713  -0.0531   0.5723   0.1901
  -7.250  -0.3436   0.03506   0.02647  -0.0507   0.5709   0.2258
  -7.000  -0.3535   0.03381   0.02569  -0.0469   0.5695   0.2726
  -6.750  -0.3768   0.03274   0.02507  -0.0406   0.5684   0.3258
  -6.500  -0.3566   0.03440   0.02804  -0.0359   0.5662   0.4838
  -6.250  -0.3168   0.03759   0.03128  -0.0343   0.5639   0.5422
  -6.000  -0.3283   0.03750   0.03111  -0.0297   0.5630   0.5735
  -5.750  -0.3009   0.03985   0.03334  -0.0279   0.5615   0.5946
  -5.500  -0.2709   0.04235   0.03571  -0.0262   0.5600   0.6134
  -5.250  -0.2455   0.04459   0.03785  -0.0242   0.5587   0.6314
  -5.000  -0.1654   0.04924   0.04239  -0.0275   0.5561   0.6359
  -4.750  -0.4816   0.05545   0.05018  -0.0162   0.6345   0.6156
  -4.500  -0.4402   0.05818   0.05277  -0.0152   0.6305   0.6372
  -4.250  -0.3910   0.06173   0.05623  -0.0149   0.6286   0.6568
  -4.000  -0.3362   0.06547   0.05987  -0.0154   0.6274   0.6750
  -3.750  -0.5153   0.06450   0.05912  -0.0030   0.6607   0.6599
  -3.500  -0.4892   0.06690   0.06145  -0.0005   0.6553   0.6774
  -3.250  -0.4548   0.06984   0.06432   0.0014   0.6523   0.6959
  -3.000  -0.4751   0.07051   0.06499   0.0074   0.6400   0.7034
  -2.750  -0.4580   0.07188   0.06628   0.0101   0.6339   0.7175
  -2.500  -0.4328   0.07321   0.06746   0.0109   0.6306   0.7325
  -2.250  -0.3951   0.07570   0.06989   0.0120   0.6285   0.7406
  -2.000  -0.4292   0.07513   0.06930   0.0180   0.6151   0.7483
  -1.750  -0.4088   0.07629   0.07039   0.0204   0.6098   0.7605
  -1.500  -0.3801   0.07839   0.07242   0.0230   0.6068   0.7795
  -1.250  -0.3360   0.08168   0.07565   0.0240   0.6049   0.8001
  -1.000  -0.3808   0.08070   0.07471   0.0312   0.5919   0.8053
  -0.750  -0.3725   0.08077   0.07467   0.0335   0.5873   0.8189
  -0.500  -0.3351   0.08254   0.07634   0.0327   0.5842   0.8245
  -0.250  -0.2999   0.08416   0.07784   0.0315   0.5823   0.8313
   0.000  -0.2768   0.08506   0.07859   0.0314   0.5810   0.8380
   0.250  -0.2354   0.08769   0.08109   0.0290   0.5800   0.8414
   0.500  -0.3079   0.08378   0.07727   0.0386   0.5625   0.8458
   0.750  -0.2781   0.08494   0.07832   0.0377   0.5602   0.8494
   1.000  -0.2456   0.08645   0.07971   0.0361   0.5587   0.8524
   1.250  -0.2093   0.08861   0.08175   0.0341   0.5577   0.8555
   1.500  -0.2727   0.08596   0.07915   0.0403   0.5432   0.8587
   1.750  -0.2465   0.08685   0.07994   0.0387   0.5398   0.8604
   2.000  -0.2152   0.08819   0.08118   0.0372   0.5375   0.8623
   2.250  -0.1795   0.09016   0.08306   0.0357   0.5359   0.8643
   2.500  -0.1394   0.09290   0.08571   0.0334   0.5349   0.8660
   2.750  -0.1994   0.09065   0.08354   0.0385   0.5211   0.8681
   3.000  -0.1754   0.09185   0.08467   0.0375   0.5178   0.8702
   3.250  -0.1455   0.09342   0.08617   0.0359   0.5155   0.8720
   3.500  -0.1100   0.09557   0.08822   0.0338   0.5139   0.8736
   3.750  -0.0699   0.09844   0.09101   0.0312   0.5128   0.8754
   4.000  -0.0260   0.10227   0.09476   0.0282   0.5120   0.8768
   4.250  -0.0987   0.09831   0.09090   0.0331   0.4968   0.8780
   4.500  -0.0705   0.10001   0.09254   0.0312   0.4942   0.8790
   4.750  -0.0373   0.10219   0.09465   0.0290   0.4924   0.8804
   5.000   0.0012   0.10507   0.09746   0.0264   0.4912   0.8820
   5.250   0.0423   0.10868   0.10102   0.0239   0.4903   0.8832
   5.500  -0.0221   0.10599   0.09843   0.0278   0.4773   0.8841
   5.750   0.0013   0.10761   0.10002   0.0266   0.4742   0.8851
   6.000   0.0292   0.10961   0.10198   0.0250   0.4720   0.8863
   6.250   0.0625   0.11223   0.10456   0.0231   0.4705   0.8876
   6.500   0.1009   0.11567   0.10796   0.0208   0.4695   0.8892
   6.750   0.1427   0.12002   0.11227   0.0183   0.4688   0.8914
   7.000   0.0691   0.11611   0.10848   0.0223   0.4557   0.8926
   7.250   0.0929   0.11799   0.11034   0.0209   0.4529   0.8943
<< Back to FX 77-W-270S (fx77w270s-il)

Polar data table (+)

Polar graphs


<< Back to FX 77-W-270S (fx77w270s-il)