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

BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.02 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707b-il-1000000.txt
Download as CSV file: xf-b707b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .19 SPAN AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.750  -1.2134   0.09052   0.08786  -0.0094   1.0000   0.0057
 -18.500  -1.2439   0.08131   0.07846  -0.0146   1.0000   0.0056
 -18.250  -1.2616   0.07459   0.07159  -0.0183   1.0000   0.0056
 -18.000  -1.2765   0.06863   0.06550  -0.0213   1.0000   0.0057
 -17.750  -1.2886   0.06348   0.06019  -0.0236   1.0000   0.0056
 -17.500  -1.2962   0.05918   0.05578  -0.0253   1.0000   0.0057
 -17.250  -1.3015   0.05541   0.05192  -0.0266   1.0000   0.0058
 -17.000  -1.2958   0.05316   0.04964  -0.0272   1.0000   0.0060
 -16.750  -1.2878   0.05126   0.04773  -0.0277   1.0000   0.0061
 -16.500  -1.2828   0.04908   0.04551  -0.0281   1.0000   0.0062
 -15.500  -1.2177   0.04613   0.04270  -0.0285   1.0000   0.0092
 -15.250  -1.2134   0.04418   0.04071  -0.0285   1.0000   0.0090
 -15.000  -1.2304   0.03983   0.03605  -0.0278   1.0000   0.0097
 -14.750  -1.2355   0.03695   0.03297  -0.0268   1.0000   0.0101
 -14.500  -1.2355   0.03468   0.03053  -0.0257   1.0000   0.0104
 -14.250  -1.2033   0.03257   0.02816  -0.0304   0.9053   0.0106
 -14.000  -1.1988   0.03239   0.02736  -0.0276   0.7282   0.0108
 -13.000  -1.1494   0.03076   0.02555  -0.0226   0.6797   0.0116
 -12.750  -1.1389   0.03025   0.02499  -0.0210   0.6749   0.0119
 -12.500  -1.1283   0.02981   0.02449  -0.0192   0.6698   0.0122
 -12.250  -1.1159   0.02977   0.02442  -0.0173   0.6664   0.0127
 -12.000  -1.1070   0.02901   0.02357  -0.0151   0.6629   0.0129
 -11.750  -1.0956   0.02933   0.02383  -0.0127   0.6605   0.0135
 -11.500  -1.0870   0.02900   0.02341  -0.0099   0.6578   0.0136
 -11.250  -1.0820   0.02976   0.02409  -0.0059   0.6555   0.0139
 -11.000  -1.0727   0.02771   0.02184  -0.0039   0.6535   0.0142
 -10.750  -1.0571   0.02636   0.02050  -0.0028   0.6519   0.0148
 -10.500  -1.0388   0.02645   0.02070  -0.0016   0.6505   0.0156
 -10.250  -1.0219   0.02584   0.02003  -0.0001   0.6490   0.0159
 -10.000  -1.0042   0.02574   0.01987   0.0014   0.6471   0.0166
  -9.750  -0.9863   0.02569   0.01973   0.0030   0.6447   0.0171
  -9.250  -0.9514   0.02310   0.01687   0.0054   0.6417   0.0185
  -9.000  -0.9300   0.02248   0.01628   0.0061   0.6404   0.0191
  -8.750  -0.9088   0.02216   0.01595   0.0070   0.6390   0.0200
  -8.500  -0.8907   0.02453   0.01825   0.0091   0.6375   0.0216
  -8.250  -0.8691   0.02238   0.01594   0.0097   0.6365   0.0218
  -8.000  -0.8458   0.02146   0.01494   0.0104   0.6358   0.0218
  -7.750  -0.8214   0.01990   0.01329   0.0107   0.6350   0.0220
  -7.500  -0.7973   0.01917   0.01251   0.0112   0.6341   0.0220
  -7.250  -0.7729   0.01852   0.01181   0.0118   0.6332   0.0220
  -7.000  -0.7485   0.01779   0.01104   0.0123   0.6321   0.0220
  -6.750  -0.7241   0.01715   0.01036   0.0129   0.6307   0.0220
  -6.500  -0.6998   0.01657   0.00975   0.0135   0.6292   0.0219
  -6.250  -0.6760   0.01585   0.00900   0.0141   0.6275   0.0220
  -6.000  -0.6549   0.01482   0.00796   0.0152   0.6263   0.0226
  -5.750  -0.6325   0.01425   0.00738   0.0161   0.6251   0.0230
  -5.500  -0.6094   0.01379   0.00689   0.0170   0.6239   0.0230
  -5.250  -0.5850   0.01348   0.00652   0.0177   0.6225   0.0225
  -5.000  -0.5602   0.01323   0.00623   0.0184   0.6210   0.0222
  -4.750  -0.5351   0.01295   0.00596   0.0189   0.6200   0.0220
  -4.500  -0.5099   0.01266   0.00566   0.0195   0.6171   0.0218
  -4.250  -0.4860   0.01226   0.00526   0.0203   0.6143   0.0216
  -4.000  -0.4633   0.01177   0.00474   0.0213   0.6126   0.0214
  -3.750  -0.4394   0.01139   0.00433   0.0221   0.6093   0.0213
  -3.500  -0.4149   0.01108   0.00397   0.0228   0.6045   0.0211
  -3.250  -0.3896   0.01076   0.00365   0.0234   0.6005   0.0210
  -3.000  -0.3640   0.01048   0.00335   0.0239   0.5961   0.0209
  -2.750  -0.3381   0.01025   0.00309   0.0244   0.5921   0.0209
  -2.500  -0.3119   0.01004   0.00286   0.0248   0.5880   0.0209
  -2.250  -0.2853   0.00983   0.00265   0.0252   0.5832   0.0209
  -2.000  -0.2587   0.00965   0.00245   0.0255   0.5774   0.0211
  -1.750  -0.2318   0.00949   0.00227   0.0258   0.5702   0.0212
  -1.500  -0.2048   0.00934   0.00210   0.0261   0.5564   0.0216
  -1.250  -0.1818   0.00975   0.00202   0.0268   0.3971   0.0222
  -1.000  -0.1561   0.00987   0.00200   0.0272   0.3486   0.0237
  -0.500  -0.1054   0.00994   0.00192   0.0280   0.2692   0.0593
  -0.250  -0.0786   0.00992   0.00190   0.0282   0.2603   0.0706
   0.000  -0.0523   0.00984   0.00187   0.0285   0.2522   0.0913
   0.250  -0.0369   0.00872   0.00161   0.0305   0.2453   0.3677
   0.500  -0.0130   0.00846   0.00156   0.0312   0.2356   0.4309
   0.750   0.0066   0.00793   0.00147   0.0326   0.2156   0.5645
   1.000   0.0284   0.00816   0.00157   0.0336   0.1370   0.6143
   1.250   0.0517   0.00836   0.00169   0.0344   0.0900   0.6455
   1.500   0.0771   0.00837   0.00177   0.0349   0.0841   0.6720
   1.750   0.1022   0.00835   0.00185   0.0355   0.0822   0.7020
   2.000   0.1273   0.00834   0.00196   0.0361   0.0811   0.7316
   2.250   0.1512   0.00831   0.00207   0.0370   0.0798   0.7682
   2.500   0.1759   0.00834   0.00221   0.0377   0.0784   0.7966
   2.750   0.2010   0.00841   0.00235   0.0383   0.0767   0.8169
   3.000   0.2263   0.00853   0.00253   0.0389   0.0745   0.8343
   3.250   0.2515   0.00867   0.00273   0.0395   0.0726   0.8526
   3.500   0.2760   0.00887   0.00301   0.0402   0.0706   0.8733
   3.750   0.3024   0.00892   0.00311   0.0405   0.0700   0.8911
   4.000   0.3293   0.00900   0.00323   0.0407   0.0691   0.9046
   4.250   0.3568   0.00912   0.00338   0.0408   0.0680   0.9168
   4.500   0.3850   0.00926   0.00354   0.0407   0.0665   0.9277
   4.750   0.4126   0.00941   0.00370   0.0407   0.0652   0.9385
   5.000   0.4437   0.00959   0.00388   0.0399   0.0636   0.9465
   5.250   0.4729   0.00982   0.00410   0.0395   0.0619   0.9548
   5.500   0.5056   0.01020   0.00450   0.0383   0.0597   0.9605
   5.750   0.5343   0.01022   0.00451   0.0381   0.0591   0.9679
   6.000   0.5710   0.01030   0.00457   0.0361   0.0577   0.9701
   6.250   0.6068   0.01040   0.00464   0.0343   0.0552   0.9723
   6.500   0.6411   0.01057   0.00473   0.0327   0.0515   0.9747
   6.750   0.6733   0.01076   0.00491   0.0316   0.0491   0.9778
   7.000   0.7022   0.01097   0.00508   0.0312   0.0449   0.9818
   7.250   0.7367   0.01133   0.00532   0.0294   0.0325   0.9831
   7.500   0.7693   0.01195   0.00589   0.0278   0.0200   0.9851
   7.750   0.8027   0.01234   0.00630   0.0263   0.0190   0.9872
   8.000   0.8353   0.01269   0.00668   0.0250   0.0184   0.9897
   8.250   0.8660   0.01306   0.00710   0.0240   0.0179   0.9923
   8.500   0.8980   0.01348   0.00756   0.0227   0.0173   0.9941
   8.750   0.9316   0.01390   0.00802   0.0211   0.0171   0.9957
   9.000   0.9644   0.01439   0.00856   0.0195   0.0167   0.9975
   9.250   0.9968   0.01494   0.00917   0.0180   0.0162   0.9992
   9.500   1.0217   0.01553   0.00981   0.0179   0.0157   1.0000
   9.750   1.0353   0.01610   0.01044   0.0201   0.0153   1.0000
  10.000   1.0472   0.01678   0.01118   0.0226   0.0149   1.0000
  10.250   1.0568   0.01759   0.01206   0.0253   0.0145   1.0000
  10.500   1.0631   0.01859   0.01314   0.0285   0.0141   1.0000
  10.750   1.0770   0.01907   0.01367   0.0306   0.0140   1.0000
  11.000   1.0896   0.01962   0.01428   0.0328   0.0138   1.0000
  11.250   1.1015   0.02021   0.01492   0.0350   0.0136   1.0000
  11.500   1.1116   0.02090   0.01567   0.0374   0.0133   1.0000
  11.750   1.1156   0.02159   0.01642   0.0408   0.0130   1.0000
  12.000   1.1189   0.02239   0.01728   0.0440   0.0127   1.0000
  12.250   1.1236   0.02336   0.01832   0.0463   0.0124   1.0000
  12.500   1.1282   0.02457   0.01960   0.0481   0.0121   1.0000
  12.750   1.1317   0.02604   0.02114   0.0495   0.0118   1.0000
  13.000   1.1322   0.02792   0.02309   0.0505   0.0116   1.0000
  13.250   1.1242   0.03066   0.02592   0.0514   0.0113   1.0000
  13.500   1.1220   0.03308   0.02843   0.0520   0.0111   1.0000
  13.750   1.1341   0.03427   0.02971   0.0521   0.0109   1.0000
  14.000   1.1385   0.03620   0.03173   0.0522   0.0107   1.0000
  14.250   1.1447   0.03804   0.03365   0.0523   0.0104   1.0000
  14.500   1.1456   0.04041   0.03612   0.0522   0.0102   1.0000
  14.750   1.1452   0.04299   0.03879   0.0519   0.0100   1.0000
  15.000   1.1412   0.04609   0.04198   0.0513   0.0098   1.0000
  15.250   1.1363   0.04941   0.04541   0.0504   0.0097   1.0000
  15.500   1.1285   0.05337   0.04948   0.0490   0.0096   1.0000
  15.750   1.1199   0.05794   0.05417   0.0469   0.0094   1.0000
  16.000   1.1066   0.06432   0.06069   0.0431   0.0093   1.0000
  16.250   1.0935   0.07099   0.06748   0.0391   0.0093   1.0000
  16.500   1.0783   0.07781   0.07442   0.0352   0.0092   1.0000
  16.750   1.0594   0.08483   0.08154   0.0316   0.0093   1.0000
  17.000   1.0407   0.09183   0.08864   0.0280   0.0092   1.0000
<< Back to BOEING 707 .19 SPAN AIRFOIL (b707b-il)

Polar data table (+)

Polar graphs


<< Back to BOEING 707 .19 SPAN AIRFOIL (b707b-il)