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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 200,000
Max Cl/Cd: 61.62 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx67k150-il-200000.txt
Download as CSV file: xf-fx67k150-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 67-K-150/17 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0540   0.09937   0.09566  -0.0945   0.8145   0.0316
 -10.500  -0.0549   0.09615   0.09246  -0.0969   0.8125   0.0321
 -10.250  -0.0542   0.09280   0.08912  -0.0988   0.8107   0.0323
 -10.000  -0.0541   0.08929   0.08561  -0.1008   0.8091   0.0324
  -9.750  -0.0527   0.08578   0.08211  -0.1023   0.8076   0.0325
  -9.500  -0.0533   0.08194   0.07829  -0.1044   0.8059   0.0326
  -9.250  -0.0487   0.07625   0.07265  -0.1030   0.8039   0.0344
  -9.000  -0.0426   0.07332   0.06974  -0.1035   0.8012   0.0355
  -8.750  -0.0400   0.07012   0.06653  -0.1043   0.7989   0.0369
  -8.500  -0.0407   0.06660   0.06302  -0.1056   0.7968   0.0378
  -8.250  -0.0437   0.06287   0.05930  -0.1072   0.7951   0.0390
  -8.000  -0.1311   0.06793   0.06400  -0.1218   0.7966   0.0330
  -7.750  -0.1282   0.06355   0.05967  -0.1216   0.7948   0.0341
  -7.500  -0.1248   0.06120   0.05730  -0.1211   0.7929   0.0350
  -7.250  -0.1212   0.05912   0.05524  -0.1211   0.7894   0.0367
  -7.000  -0.1197   0.05664   0.05268  -0.1210   0.7862   0.0381
  -6.750  -0.1162   0.05403   0.04992  -0.1206   0.7835   0.0396
  -6.500  -0.1105   0.05355   0.04884  -0.1190   0.7812   0.0449
  -6.250  -0.1105   0.04851   0.04365  -0.1185   0.7788   0.0467
  -6.000  -0.0970   0.04686   0.04219  -0.1186   0.7751   0.0515
  -5.500  -0.0740   0.04246   0.03730  -0.1168   0.7696   0.0627
  -5.250  -0.0592   0.04133   0.03562  -0.1153   0.7678   0.0734
  -5.000  -0.0393   0.03853   0.03294  -0.1152   0.7666   0.0784
  -4.750  -0.0311   0.03786   0.03211  -0.1140   0.7607   0.0895
  -4.500  -0.0145   0.03655   0.03064  -0.1132   0.7579   0.1032
  -4.250   0.0213   0.03166   0.02474  -0.1098   0.7562   0.0406
  -4.000   0.0508   0.02992   0.02250  -0.1083   0.7547   0.0317
  -3.750   0.0776   0.02783   0.02015  -0.1076   0.7536   0.0308
  -3.500   0.0872   0.02790   0.02015  -0.1057   0.7475   0.0309
  -3.250   0.1094   0.02755   0.01963  -0.1047   0.7446   0.0326
  -3.000   0.1319   0.02594   0.01806  -0.1039   0.7428   0.0384
  -2.750   0.1576   0.02508   0.01713  -0.1032   0.7413   0.0436
  -2.500   0.1831   0.02421   0.01624  -0.1027   0.7402   0.0552
  -2.250   0.1803   0.02555   0.01760  -0.0996   0.7322   0.0596
  -2.000   0.2039   0.02499   0.01711  -0.0991   0.7300   0.0911
  -1.750   0.2055   0.02263   0.01733  -0.0942   0.7283   0.7380
  -1.500   0.2246   0.02287   0.01753  -0.0911   0.7271   0.8153
  -1.250   0.2063   0.02485   0.01961  -0.0851   0.7178   0.8350
  -1.000   0.2121   0.02504   0.01984  -0.0791   0.7156   0.8816
  -0.750   0.2189   0.02497   0.01976  -0.0729   0.7142   0.9208
  -0.500   0.1930   0.02680   0.02166  -0.0662   0.7046   0.9422
  -0.250   0.2743   0.02711   0.02176  -0.0753   0.7048   0.9716
   0.000   0.3303   0.02727   0.02174  -0.0809   0.7037   0.9764
   0.250   0.3764   0.02737   0.02171  -0.0848   0.7027   0.9817
   0.500   0.4274   0.02733   0.02155  -0.0895   0.7019   0.9847
   0.750   0.4751   0.02721   0.02132  -0.0935   0.7012   0.9882
   1.000   0.5204   0.02699   0.02102  -0.0969   0.7005   0.9920
   1.250   0.5645   0.02680   0.02075  -0.1001   0.6999   0.9955
   1.500   0.6085   0.02661   0.02050  -0.1034   0.6994   0.9988
   1.750   0.5130   0.02948   0.02346  -0.0862   0.6849   1.0000
   2.000   0.5619   0.02884   0.02275  -0.0892   0.6859   1.0000
   2.250   0.5135   0.03095   0.02485  -0.0795   0.6741   1.0000
   2.500   0.5498   0.03078   0.02462  -0.0809   0.6734   1.0000
   2.750   0.5873   0.03055   0.02438  -0.0824   0.6728   1.0000
   3.000   0.5652   0.03286   0.02667  -0.0775   0.6612   1.0000
   3.250   0.5593   0.03470   0.02849  -0.0746   0.6521   1.0000
   3.500   0.5883   0.03483   0.02860  -0.0751   0.6497   1.0000
   3.750   0.6217   0.03472   0.02848  -0.0761   0.6483   1.0000
   4.000   0.6350   0.03569   0.02943  -0.0750   0.6429   1.0000
   4.250   0.6873   0.03457   0.02835  -0.0777   0.6454   1.0000
   4.500   0.6821   0.03636   0.03013  -0.0748   0.6354   1.0000
   4.750   0.7169   0.03611   0.02991  -0.0758   0.6343   1.0000
   5.000   0.7528   0.03576   0.02958  -0.0768   0.6334   1.0000
   5.250   0.7891   0.03540   0.02929  -0.0779   0.6327   1.0000
   5.500   0.6843   0.02472   0.01902  -0.0633   0.5965   1.0000
   5.750   0.7177   0.02433   0.01870  -0.0641   0.5950   1.0000
   6.000   0.7523   0.02381   0.01822  -0.0649   0.5939   1.0000
   6.250   0.7887   0.02316   0.01764  -0.0658   0.5931   1.0000
   6.500   0.8259   0.02241   0.01699  -0.0668   0.5925   1.0000
   6.750   0.8815   0.03945   0.03366  -0.0722   0.5962   1.0000
   7.000   0.9178   0.03874   0.03304  -0.0729   0.5949   1.0000
   7.250   0.9261   0.03984   0.03421  -0.0714   0.5863   1.0000
   7.500   0.9625   0.03879   0.03327  -0.0719   0.5836   1.0000
   7.750   1.0175   0.03592   0.03058  -0.0735   0.5832   1.0000
   8.000   1.0720   0.03299   0.02783  -0.0752   0.5833   1.0000
   8.250   1.2244   0.01987   0.01486  -0.0830   0.5594   1.0000
   8.500   1.2236   0.02000   0.01467  -0.0785   0.4936   1.0000
   8.750   1.2096   0.02160   0.01566  -0.0731   0.4101   1.0000
   9.000   1.1869   0.02425   0.01788  -0.0679   0.3494   1.0000
   9.250   1.1635   0.02727   0.02050  -0.0631   0.2918   1.0000
   9.500   1.1410   0.03050   0.02334  -0.0589   0.2304   1.0000
   9.750   1.1152   0.03426   0.02657  -0.0548   0.1549   1.0000
  10.000   1.0959   0.03786   0.02965  -0.0517   0.0808   1.0000
  10.250   1.0801   0.04142   0.03281  -0.0489   0.0296   1.0000
  10.500   1.0809   0.04379   0.03522  -0.0472   0.0195   1.0000
  10.750   1.0843   0.04598   0.03751  -0.0459   0.0171   1.0000
  11.000   1.0858   0.04841   0.04009  -0.0446   0.0157   1.0000
  11.250   1.0892   0.05073   0.04255  -0.0435   0.0150   1.0000
  11.500   1.0920   0.05314   0.04508  -0.0424   0.0146   1.0000
  11.750   1.0939   0.05569   0.04774  -0.0414   0.0142   1.0000
  12.000   1.0974   0.05808   0.05022  -0.0403   0.0139   1.0000
  12.250   1.1030   0.06025   0.05248  -0.0393   0.0137   1.0000
  12.500   1.1123   0.06203   0.05434  -0.0380   0.0136   1.0000
  12.750   1.1278   0.06322   0.05559  -0.0367   0.0136   1.0000
  13.000   1.1524   0.06378   0.05629  -0.0352   0.0137   1.0000
  13.250   1.1855   0.06434   0.05703  -0.0339   0.0141   1.0000
  13.500   1.2231   0.06610   0.05907  -0.0328   0.0148   1.0000
  13.750   1.2321   0.06872   0.06195  -0.0320   0.0142   1.0000
  14.000   1.2377   0.07167   0.06515  -0.0313   0.0137   1.0000
  14.250   1.2416   0.07529   0.06907  -0.0304   0.0138   1.0000
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