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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 500,000
Max Cl/Cd: 78.48 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7003-il-500000.txt
Download as CSV file: xf-sd7003-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7003-085-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6418   0.07188   0.06968  -0.0177   1.0000   0.0135
  -9.500  -0.6941   0.05165   0.04937  -0.0350   1.0000   0.0125
  -9.250  -0.7245   0.04318   0.04055  -0.0399   1.0000   0.0123
  -9.000  -0.7413   0.03550   0.03232  -0.0414   1.0000   0.0121
  -8.750  -0.7418   0.02981   0.02603  -0.0413   1.0000   0.0121
  -8.500  -0.7302   0.02634   0.02210  -0.0406   1.0000   0.0123
  -8.250  -0.7138   0.02376   0.01914  -0.0398   1.0000   0.0125
  -8.000  -0.6944   0.02188   0.01693  -0.0390   1.0000   0.0128
  -7.750  -0.6732   0.02044   0.01524  -0.0382   1.0000   0.0130
  -7.500  -0.6549   0.01799   0.01250  -0.0372   1.0000   0.0137
  -7.250  -0.6325   0.01708   0.01155  -0.0365   1.0000   0.0145
  -7.000  -0.6092   0.01633   0.01071  -0.0358   1.0000   0.0153
  -6.750  -0.5861   0.01541   0.00967  -0.0350   1.0000   0.0162
  -6.500  -0.5626   0.01461   0.00874  -0.0341   1.0000   0.0170
  -6.250  -0.5405   0.01335   0.00737  -0.0332   1.0000   0.0184
  -6.000  -0.5167   0.01275   0.00676  -0.0325   1.0000   0.0202
  -5.750  -0.4923   0.01229   0.00623  -0.0317   1.0000   0.0224
  -5.500  -0.4689   0.01155   0.00548  -0.0309   1.0000   0.0260
  -5.250  -0.4443   0.01135   0.00524  -0.0302   1.0000   0.0296
  -5.000  -0.4206   0.01074   0.00465  -0.0294   1.0000   0.0352
  -4.750  -0.3965   0.01035   0.00424  -0.0287   1.0000   0.0406
  -4.500  -0.3722   0.01011   0.00401  -0.0280   1.0000   0.0472
  -4.250  -0.3484   0.00975   0.00368  -0.0272   1.0000   0.0551
  -4.000  -0.3245   0.00953   0.00344  -0.0264   1.0000   0.0625
  -3.750  -0.2945   0.00927   0.00321  -0.0269   0.9986   0.0725
  -3.500  -0.2544   0.00896   0.00293  -0.0296   0.9945   0.0860
  -3.250  -0.2161   0.00861   0.00267  -0.0318   0.9894   0.1052
  -3.000  -0.1762   0.00825   0.00246  -0.0344   0.9845   0.1382
  -2.750  -0.1391   0.00782   0.00225  -0.0365   0.9776   0.1922
  -2.250  -0.0660   0.00699   0.00193  -0.0403   0.9591   0.3343
  -2.000  -0.0316   0.00660   0.00179  -0.0416   0.9447   0.4101
  -1.750   0.0011   0.00621   0.00167  -0.0425   0.9259   0.4967
  -1.500   0.0298   0.00591   0.00159  -0.0424   0.9005   0.5785
  -1.250   0.0560   0.00573   0.00153  -0.0416   0.8718   0.6460
  -1.000   0.0810   0.00563   0.00151  -0.0406   0.8421   0.7060
  -0.750   0.1056   0.00559   0.00151  -0.0394   0.8125   0.7551
  -0.500   0.1301   0.00558   0.00150  -0.0382   0.7833   0.7977
  -0.250   0.1542   0.00559   0.00151  -0.0370   0.7548   0.8363
   0.000   0.1779   0.00562   0.00151  -0.0356   0.7270   0.8710
   0.250   0.2010   0.00566   0.00151  -0.0340   0.6998   0.9040
   0.500   0.2254   0.00571   0.00150  -0.0328   0.6727   0.9370
   0.750   0.2579   0.00579   0.00147  -0.0334   0.6439   0.9669
   1.000   0.2973   0.00590   0.00144  -0.0358   0.6127   0.9900
   1.250   0.3290   0.00604   0.00144  -0.0366   0.5837   1.0000
   1.500   0.3546   0.00620   0.00146  -0.0361   0.5562   1.0000
   1.750   0.3808   0.00637   0.00150  -0.0357   0.5287   1.0000
   2.000   0.4072   0.00654   0.00156  -0.0353   0.5018   1.0000
   2.250   0.4338   0.00673   0.00163  -0.0350   0.4755   1.0000
   2.500   0.4605   0.00692   0.00170  -0.0347   0.4496   1.0000
   3.000   0.5140   0.00733   0.00191  -0.0342   0.3985   1.0000
   3.250   0.5409   0.00754   0.00202  -0.0340   0.3740   1.0000
   3.500   0.5676   0.00778   0.00215  -0.0338   0.3503   1.0000
   3.750   0.5945   0.00800   0.00229  -0.0336   0.3261   1.0000
   4.000   0.6212   0.00825   0.00246  -0.0333   0.3041   1.0000
   4.250   0.6479   0.00851   0.00263  -0.0331   0.2813   1.0000
   4.500   0.6746   0.00878   0.00282  -0.0329   0.2600   1.0000
   4.750   0.7012   0.00906   0.00303  -0.0327   0.2387   1.0000
   5.000   0.7276   0.00936   0.00325  -0.0324   0.2197   1.0000
   5.250   0.7541   0.00964   0.00349  -0.0322   0.2013   1.0000
   5.500   0.7805   0.00995   0.00374  -0.0319   0.1839   1.0000
   5.750   0.8068   0.01028   0.00402  -0.0317   0.1682   1.0000
   6.000   0.8329   0.01062   0.00431  -0.0314   0.1527   1.0000
   6.250   0.8589   0.01098   0.00462  -0.0311   0.1381   1.0000
   6.500   0.8847   0.01136   0.00496  -0.0308   0.1228   1.0000
   6.750   0.9104   0.01175   0.00530  -0.0305   0.1089   1.0000
   7.000   0.9361   0.01213   0.00566  -0.0302   0.0975   1.0000
   7.250   0.9617   0.01252   0.00604  -0.0299   0.0870   1.0000
   7.500   0.9871   0.01294   0.00647  -0.0296   0.0775   1.0000
   7.750   1.0120   0.01341   0.00693  -0.0292   0.0680   1.0000
   8.000   1.0364   0.01395   0.00743  -0.0287   0.0581   1.0000
   8.250   1.0609   0.01446   0.00793  -0.0283   0.0492   1.0000
   8.500   1.0849   0.01505   0.00852  -0.0278   0.0409   1.0000
   8.750   1.1080   0.01577   0.00928  -0.0272   0.0336   1.0000
   9.000   1.1294   0.01672   0.01025  -0.0264   0.0283   1.0000
   9.250   1.1526   0.01736   0.01096  -0.0257   0.0254   1.0000
   9.500   1.1712   0.01861   0.01225  -0.0247   0.0224   1.0000
   9.750   1.1933   0.01934   0.01309  -0.0239   0.0212   1.0000
  10.000   1.2142   0.02016   0.01401  -0.0231   0.0200   1.0000
  10.250   1.2342   0.02106   0.01500  -0.0222   0.0189   1.0000
  10.500   1.2518   0.02218   0.01619  -0.0211   0.0178   1.0000
  10.750   1.2621   0.02414   0.01829  -0.0192   0.0167   1.0000
  11.000   1.2807   0.02500   0.01927  -0.0182   0.0162   1.0000
  11.250   1.2964   0.02613   0.02053  -0.0169   0.0156   1.0000
  11.500   1.3102   0.02735   0.02188  -0.0155   0.0150   1.0000
  11.750   1.3219   0.02866   0.02332  -0.0139   0.0145   1.0000
  12.000   1.3313   0.02995   0.02472  -0.0122   0.0139   1.0000
  12.250   1.3353   0.03130   0.02615  -0.0097   0.0135   1.0000
  12.500   1.3335   0.03313   0.02809  -0.0072   0.0132   1.0000
  12.750   1.3262   0.03569   0.03079  -0.0050   0.0129   1.0000
  13.000   1.3094   0.03968   0.03497  -0.0036   0.0125   1.0000
  13.250   1.3086   0.04217   0.03763  -0.0036   0.0123   1.0000
  13.500   1.3049   0.04534   0.04097  -0.0041   0.0122   1.0000
  13.750   1.3006   0.04890   0.04469  -0.0054   0.0120   1.0000
  14.000   1.2943   0.05306   0.04901  -0.0073   0.0118   1.0000
  14.250   1.2839   0.05815   0.05428  -0.0098   0.0117   1.0000
  14.500   1.2722   0.06376   0.06005  -0.0129   0.0116   1.0000
  14.750   1.2593   0.06983   0.06629  -0.0165   0.0116   1.0000
  15.000   1.2469   0.07615   0.07275  -0.0204   0.0114   1.0000
  15.250   1.2294   0.08354   0.08031  -0.0248   0.0114   1.0000
  15.500   1.2099   0.09163   0.08855  -0.0297   0.0115   1.0000
  15.750   1.1906   0.10012   0.09719  -0.0349   0.0115   1.0000
  16.000   1.1708   0.10913   0.10635  -0.0405   0.0115   1.0000
  16.250   1.1476   0.11929   0.11666  -0.0468   0.0117   1.0000
  16.500   1.1234   0.13025   0.12777  -0.0535   0.0118   1.0000
  16.750   1.0948   0.14289   0.14056  -0.0613   0.0120   1.0000
  17.000   1.0458   0.16227   0.16008  -0.0730   0.0124   1.0000
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