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SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD8020-010-88 (sd8020-il)
Reynolds number: 100,000
Max Cl/Cd: 36.33 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8020-il-100000-n5.txt
Download as CSV file: xf-sd8020-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8020-010-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7123   0.10913   0.10395  -0.0039   1.0000   0.0284
 -12.500  -0.8415   0.07300   0.06746  -0.0286   1.0000   0.0245
 -12.250  -0.8673   0.06553   0.05973  -0.0340   1.0000   0.0242
 -11.750  -0.9034   0.05568   0.04947  -0.0380   1.0000   0.0242
 -11.500  -0.9174   0.05196   0.04556  -0.0378   1.0000   0.0245
 -11.250  -0.9280   0.04887   0.04228  -0.0365   1.0000   0.0247
 -11.000  -0.9350   0.04633   0.03959  -0.0344   1.0000   0.0251
 -10.750  -0.9392   0.04411   0.03720  -0.0319   1.0000   0.0257
 -10.500  -0.9381   0.04204   0.03495  -0.0297   1.0000   0.0265
 -10.250  -0.9338   0.04018   0.03289  -0.0277   1.0000   0.0279
 -10.000  -0.9276   0.03819   0.03062  -0.0257   1.0000   0.0295
  -9.750  -0.9188   0.03611   0.02818  -0.0237   1.0000   0.0313
  -9.500  -0.9073   0.03398   0.02576  -0.0218   1.0000   0.0326
  -9.250  -0.8953   0.03208   0.02378  -0.0202   1.0000   0.0342
  -9.000  -0.8812   0.03075   0.02236  -0.0186   1.0000   0.0365
  -8.750  -0.8656   0.02944   0.02083  -0.0170   1.0000   0.0397
  -8.500  -0.8491   0.02801   0.01917  -0.0153   1.0000   0.0426
  -8.250  -0.8346   0.02661   0.01776  -0.0136   1.0000   0.0456
  -8.000  -0.8182   0.02545   0.01649  -0.0119   1.0000   0.0494
  -7.750  -0.8017   0.02431   0.01524  -0.0101   1.0000   0.0550
  -7.500  -0.7844   0.02338   0.01426  -0.0085   1.0000   0.0623
  -7.250  -0.7677   0.02237   0.01323  -0.0068   1.0000   0.0701
  -7.000  -0.7497   0.02151   0.01228  -0.0052   1.0000   0.0802
  -6.750  -0.7312   0.02075   0.01149  -0.0037   1.0000   0.0925
  -6.500  -0.7127   0.02003   0.01078  -0.0023   1.0000   0.1068
  -6.250  -0.6938   0.01935   0.01013  -0.0008   1.0000   0.1228
  -6.000  -0.6746   0.01870   0.00950   0.0006   1.0000   0.1399
  -5.750  -0.6550   0.01810   0.00888   0.0020   1.0000   0.1589
  -5.500  -0.6357   0.01750   0.00835   0.0034   1.0000   0.1789
  -5.250  -0.6157   0.01698   0.00785   0.0048   1.0000   0.2017
  -5.000  -0.5961   0.01645   0.00741   0.0062   1.0000   0.2268
  -4.750  -0.5763   0.01596   0.00700   0.0076   1.0000   0.2547
  -4.500  -0.5565   0.01551   0.00664   0.0090   1.0000   0.2852
  -4.250  -0.5366   0.01509   0.00629   0.0104   1.0000   0.3176
  -4.000  -0.5169   0.01469   0.00602   0.0119   1.0000   0.3524
  -3.500  -0.4775   0.01398   0.00557   0.0149   1.0000   0.4274
  -3.250  -0.4578   0.01367   0.00538   0.0165   1.0000   0.4667
  -3.000  -0.4382   0.01340   0.00526   0.0181   1.0000   0.5073
  -2.750  -0.4185   0.01317   0.00517   0.0197   1.0000   0.5484
  -2.500  -0.3987   0.01297   0.00513   0.0213   1.0000   0.5895
  -2.250  -0.3786   0.01282   0.00512   0.0229   1.0000   0.6302
  -2.000  -0.3550   0.01272   0.00514   0.0239   0.9986   0.6719
  -1.750  -0.3159   0.01268   0.00522   0.0217   0.9901   0.7179
  -1.500  -0.2752   0.01268   0.00533   0.0194   0.9820   0.7601
  -1.250  -0.2352   0.01267   0.00538   0.0173   0.9725   0.7985
  -1.000  -0.1929   0.01270   0.00547   0.0148   0.9630   0.8321
  -0.750  -0.1455   0.01276   0.00556   0.0113   0.9545   0.8609
  -0.500  -0.0987   0.01280   0.00562   0.0079   0.9440   0.8852
  -0.250  -0.0491   0.01285   0.00567   0.0039   0.9330   0.9039
   0.000   0.0000   0.01286   0.00568   0.0000   0.9198   0.9198
   0.250   0.0493   0.01285   0.00567  -0.0039   0.9039   0.9330
   0.500   0.0988   0.01280   0.00562  -0.0079   0.8852   0.9441
   0.750   0.1456   0.01276   0.00556  -0.0113   0.8610   0.9546
   1.000   0.1929   0.01270   0.00547  -0.0148   0.8322   0.9630
   1.250   0.2352   0.01267   0.00538  -0.0173   0.7985   0.9724
   1.500   0.2751   0.01268   0.00532  -0.0194   0.7601   0.9819
   1.750   0.3159   0.01268   0.00522  -0.0217   0.7177   0.9901
   2.000   0.3552   0.01272   0.00514  -0.0239   0.6723   0.9987
   2.250   0.3786   0.01282   0.00512  -0.0229   0.6307   1.0000
   2.500   0.3987   0.01297   0.00513  -0.0213   0.5897   1.0000
   2.750   0.4185   0.01316   0.00517  -0.0197   0.5485   1.0000
   3.000   0.4382   0.01340   0.00526  -0.0181   0.5075   1.0000
   3.250   0.4578   0.01367   0.00538  -0.0165   0.4669   1.0000
   3.500   0.4775   0.01398   0.00557  -0.0149   0.4273   1.0000
   4.000   0.5169   0.01469   0.00602  -0.0119   0.3525   1.0000
   4.250   0.5366   0.01509   0.00629  -0.0104   0.3178   1.0000
   4.500   0.5565   0.01551   0.00664  -0.0090   0.2854   1.0000
   4.750   0.5763   0.01596   0.00700  -0.0076   0.2546   1.0000
   5.000   0.5961   0.01645   0.00741  -0.0062   0.2268   1.0000
   5.250   0.6157   0.01698   0.00785  -0.0048   0.2016   1.0000
   5.500   0.6357   0.01750   0.00835  -0.0034   0.1789   1.0000
   5.750   0.6550   0.01810   0.00888  -0.0020   0.1587   1.0000
   6.000   0.6746   0.01870   0.00950  -0.0006   0.1396   1.0000
   6.250   0.6938   0.01934   0.01013   0.0008   0.1224   1.0000
   6.500   0.7126   0.02003   0.01079   0.0023   0.1067   1.0000
   6.750   0.7312   0.02076   0.01149   0.0037   0.0924   1.0000
   7.000   0.7497   0.02152   0.01228   0.0052   0.0801   1.0000
   7.250   0.7676   0.02238   0.01323   0.0068   0.0701   1.0000
   7.500   0.7844   0.02339   0.01426   0.0086   0.0625   1.0000
   7.750   0.8017   0.02431   0.01525   0.0101   0.0552   1.0000
   8.000   0.8182   0.02545   0.01648   0.0118   0.0497   1.0000
   8.250   0.8346   0.02661   0.01776   0.0135   0.0457   1.0000
   8.500   0.8494   0.02798   0.01915   0.0153   0.0427   1.0000
   8.750   0.8656   0.02946   0.02084   0.0170   0.0400   1.0000
   9.000   0.8813   0.03075   0.02236   0.0185   0.0366   1.0000
   9.250   0.8955   0.03208   0.02379   0.0201   0.0343   1.0000
   9.500   0.9076   0.03394   0.02573   0.0218   0.0327   1.0000
   9.750   0.9190   0.03610   0.02817   0.0237   0.0314   1.0000
  10.000   0.9279   0.03823   0.03065   0.0256   0.0298   1.0000
  10.250   0.9341   0.04018   0.03289   0.0277   0.0280   1.0000
  10.500   0.9382   0.04209   0.03502   0.0297   0.0266   1.0000
  10.750   0.9393   0.04415   0.03725   0.0318   0.0257   1.0000
  11.000   0.9352   0.04636   0.03961   0.0344   0.0251   1.0000
  11.250   0.9281   0.04893   0.04235   0.0365   0.0247   1.0000
  11.500   0.9178   0.05198   0.04557   0.0377   0.0244   1.0000
  11.750   0.9036   0.05574   0.04953   0.0379   0.0242   1.0000
  12.250   0.8677   0.06557   0.05979   0.0338   0.0242   1.0000
  12.500   0.8432   0.07281   0.06726   0.0287   0.0244   1.0000
  12.750   0.7123   0.10943   0.10425   0.0037   0.0290   1.0000
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