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

SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 200,000
Max Cl/Cd: 58.13 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7003-il-200000.txt
Download as CSV file: xf-sd7003-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5721   0.07032   0.06673  -0.0324   1.0000   0.0604
  -7.750  -0.5749   0.06555   0.06174  -0.0350   1.0000   0.0606
  -7.500  -0.5719   0.05815   0.05447  -0.0357   1.0000   0.0620
  -7.250  -0.6036   0.03400   0.02865  -0.0390   1.0000   0.0302
  -7.000  -0.5886   0.03008   0.02421  -0.0384   1.0000   0.0302
  -6.750  -0.5716   0.02648   0.02020  -0.0376   1.0000   0.0307
  -6.500  -0.5511   0.02436   0.01787  -0.0369   1.0000   0.0320
  -6.250  -0.5285   0.02332   0.01671  -0.0362   1.0000   0.0347
  -6.000  -0.5055   0.02183   0.01485  -0.0352   1.0000   0.0375
  -5.750  -0.4836   0.01936   0.01211  -0.0342   1.0000   0.0401
  -5.500  -0.4602   0.01839   0.01108  -0.0335   1.0000   0.0442
  -5.250  -0.4363   0.01732   0.00982  -0.0326   1.0000   0.0500
  -5.000  -0.4129   0.01639   0.00891  -0.0318   1.0000   0.0562
  -4.750  -0.3894   0.01540   0.00786  -0.0309   1.0000   0.0640
  -4.500  -0.3652   0.01492   0.00729  -0.0301   1.0000   0.0728
  -4.250  -0.3421   0.01400   0.00645  -0.0293   1.0000   0.0826
  -4.000  -0.3186   0.01333   0.00580  -0.0285   1.0000   0.0940
  -3.750  -0.2951   0.01274   0.00524  -0.0277   1.0000   0.1068
  -3.500  -0.2716   0.01222   0.00479  -0.0269   1.0000   0.1229
  -3.250  -0.2482   0.01173   0.00436  -0.0262   1.0000   0.1446
  -3.000  -0.2250   0.01115   0.00401  -0.0256   1.0000   0.1793
  -2.750  -0.2020   0.01056   0.00376  -0.0250   1.0000   0.2466
  -2.500  -0.1796   0.00999   0.00361  -0.0245   1.0000   0.3433
  -2.250  -0.1578   0.00952   0.00359  -0.0237   1.0000   0.4488
  -2.000  -0.1376   0.00915   0.00367  -0.0225   1.0000   0.5602
  -1.750  -0.0961   0.00880   0.00379  -0.0251   0.9901   0.6866
  -1.500  -0.0560   0.00860   0.00385  -0.0269   0.9790   0.7787
  -1.250  -0.0175   0.00844   0.00386  -0.0282   0.9675   0.8472
  -1.000   0.0227   0.00831   0.00379  -0.0296   0.9567   0.9061
  -0.750   0.0709   0.00817   0.00365  -0.0328   0.9451   0.9547
  -0.500   0.1309   0.00803   0.00344  -0.0387   0.9332   0.9856
  -0.250   0.1857   0.00787   0.00319  -0.0439   0.9151   1.0000
   0.000   0.2189   0.00777   0.00298  -0.0446   0.8858   1.0000
   0.250   0.2449   0.00776   0.00282  -0.0438   0.8538   1.0000
   0.500   0.2676   0.00782   0.00273  -0.0424   0.8211   1.0000
   0.750   0.2904   0.00793   0.00267  -0.0410   0.7890   1.0000
   1.000   0.3137   0.00808   0.00264  -0.0398   0.7576   1.0000
   1.250   0.3377   0.00824   0.00264  -0.0387   0.7266   1.0000
   1.500   0.3621   0.00842   0.00266  -0.0377   0.6959   1.0000
   1.750   0.3869   0.00861   0.00269  -0.0368   0.6653   1.0000
   2.000   0.4120   0.00881   0.00274  -0.0360   0.6348   1.0000
   2.250   0.4372   0.00903   0.00282  -0.0353   0.6046   1.0000
   2.500   0.4626   0.00926   0.00291  -0.0347   0.5744   1.0000
   2.750   0.4880   0.00950   0.00301  -0.0340   0.5444   1.0000
   3.000   0.5136   0.00976   0.00315  -0.0334   0.5148   1.0000
   3.250   0.5392   0.01003   0.00330  -0.0329   0.4854   1.0000
   3.500   0.5649   0.01031   0.00346  -0.0324   0.4565   1.0000
   3.750   0.5905   0.01061   0.00365  -0.0319   0.4279   1.0000
   4.000   0.6162   0.01092   0.00388  -0.0314   0.4000   1.0000
   4.250   0.6418   0.01125   0.00411  -0.0310   0.3728   1.0000
   4.500   0.6673   0.01161   0.00437  -0.0305   0.3466   1.0000
   4.750   0.6926   0.01200   0.00466  -0.0301   0.3212   1.0000
   5.000   0.7182   0.01237   0.00498  -0.0297   0.2961   1.0000
   5.250   0.7435   0.01279   0.00533  -0.0293   0.2726   1.0000
   5.500   0.7686   0.01324   0.00570  -0.0288   0.2505   1.0000
   5.750   0.7938   0.01370   0.00613  -0.0284   0.2294   1.0000
   6.000   0.8187   0.01419   0.00657  -0.0280   0.2097   1.0000
   6.250   0.8431   0.01476   0.00705  -0.0275   0.1919   1.0000
   6.500   0.8679   0.01529   0.00758  -0.0270   0.1748   1.0000
   6.750   0.8923   0.01586   0.00817  -0.0265   0.1590   1.0000
   7.000   0.9166   0.01646   0.00877  -0.0260   0.1440   1.0000
   7.250   0.9405   0.01708   0.00940  -0.0255   0.1298   1.0000
   7.500   0.9642   0.01770   0.01002  -0.0250   0.1159   1.0000
   7.750   0.9875   0.01836   0.01072  -0.0244   0.1030   1.0000
   8.000   1.0102   0.01912   0.01150  -0.0238   0.0911   1.0000
   8.250   1.0322   0.02000   0.01239  -0.0231   0.0800   1.0000
   8.500   1.0531   0.02099   0.01338  -0.0223   0.0692   1.0000
   8.750   1.0741   0.02197   0.01441  -0.0215   0.0598   1.0000
   9.000   1.0941   0.02322   0.01580  -0.0205   0.0524   1.0000
   9.250   1.1112   0.02491   0.01747  -0.0193   0.0468   1.0000
   9.500   1.1314   0.02597   0.01873  -0.0183   0.0424   1.0000
   9.750   1.1492   0.02744   0.02022  -0.0173   0.0393   1.0000
  10.000   1.1646   0.03000   0.02291  -0.0161   0.0371   1.0000
  10.250   1.1817   0.03164   0.02482  -0.0149   0.0353   1.0000
  10.500   1.1972   0.03329   0.02670  -0.0136   0.0333   1.0000
  10.750   1.2115   0.03481   0.02835  -0.0125   0.0315   1.0000
  11.000   1.2235   0.03704   0.03067  -0.0113   0.0303   1.0000
  11.250   1.2275   0.04115   0.03507  -0.0099   0.0294   1.0000
  11.500   1.2277   0.04425   0.03851  -0.0079   0.0289   1.0000
  11.750   1.2235   0.04691   0.04149  -0.0057   0.0286   1.0000
  12.000   1.2129   0.04971   0.04455  -0.0033   0.0284   1.0000
  12.250   1.1994   0.05298   0.04808  -0.0020   0.0281   1.0000
  12.500   1.1833   0.05696   0.05232  -0.0022   0.0280   1.0000
  12.750   1.1649   0.06188   0.05747  -0.0039   0.0280   1.0000
  13.000   1.1449   0.06768   0.06349  -0.0070   0.0280   1.0000
  13.250   1.1223   0.07475   0.07076  -0.0115   0.0282   1.0000
  13.500   1.0979   0.08290   0.07910  -0.0173   0.0284   1.0000
  13.750   1.0705   0.09249   0.08884  -0.0237   0.0289   1.0000
<< Back to SD7003-085-88 (sd7003-il)

Polar data table (+)

Polar graphs


<< Back to SD7003-085-88 (sd7003-il)