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

US1000ROOT (us1000root-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: US1000ROOT (us1000root-il)
Reynolds number: 1,000,000
Max Cl/Cd: 52.28 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-us1000root-il-1000000.txt
Download as CSV file: xf-us1000root-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: US1000ROOT                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.9426   0.08384   0.07967  -0.0184   1.0000   0.0025
 -15.500  -0.9491   0.07959   0.07536  -0.0198   1.0000   0.0026
 -15.250  -0.9616   0.07459   0.07027  -0.0213   1.0000   0.0025
 -15.000  -0.9703   0.07011   0.06571  -0.0227   1.0000   0.0025
 -14.750  -0.9860   0.06482   0.06032  -0.0242   1.0000   0.0025
 -14.500  -0.9916   0.06089   0.05632  -0.0254   1.0000   0.0025
 -14.250  -1.0125   0.05514   0.05044  -0.0270   1.0000   0.0026
 -14.000  -1.0031   0.05318   0.04845  -0.0275   1.0000   0.0025
 -13.750  -1.0043   0.04995   0.04516  -0.0283   1.0000   0.0025
 -13.500  -1.0163   0.04557   0.04067  -0.0293   1.0000   0.0025
 -13.250  -1.0361   0.04043   0.03538  -0.0303   1.0000   0.0025
 -13.000  -1.0430   0.03696   0.03181  -0.0306   1.0000   0.0025
 -12.750  -1.0355   0.03514   0.02995  -0.0307   1.0000   0.0026
 -12.500  -1.0528   0.03107   0.02571  -0.0303   1.0000   0.0026
 -12.250  -1.0473   0.02933   0.02393  -0.0297   1.0000   0.0026
 -12.000  -1.0502   0.02704   0.02152  -0.0286   1.0000   0.0026
 -11.750  -1.0498   0.02519   0.01959  -0.0272   1.0000   0.0026
 -11.500  -1.0485   0.02357   0.01789  -0.0254   1.0000   0.0027
 -11.250  -1.0440   0.02229   0.01655  -0.0236   1.0000   0.0028
 -11.000  -1.0384   0.02119   0.01540  -0.0216   1.0000   0.0028
 -10.750  -1.0338   0.02016   0.01431  -0.0192   1.0000   0.0029
 -10.500  -1.0297   0.01925   0.01335  -0.0163   1.0000   0.0031
 -10.250  -1.0237   0.01855   0.01259  -0.0133   1.0000   0.0030
 -10.000  -1.0163   0.01802   0.01203  -0.0102   1.0000   0.0031
  -9.750  -0.9792   0.01731   0.01129  -0.0132   0.9973   0.0033
  -9.500  -0.9616   0.01649   0.01041  -0.0120   0.9509   0.0035
  -9.250  -0.9116   0.01573   0.00959  -0.0175   0.9406   0.0037
  -9.000  -0.8584   0.01499   0.00879  -0.0236   0.9316   0.0040
  -8.750  -0.8032   0.01432   0.00804  -0.0302   0.9195   0.0050
  -8.500  -0.7721   0.01164   0.00586  -0.0344   0.9006   0.1136
  -8.250  -0.7367   0.01104   0.00534  -0.0369   0.8875   0.1369
  -8.000  -0.7205   0.01015   0.00472  -0.0356   0.8744   0.1919
  -7.750  -0.6970   0.00988   0.00450  -0.0350   0.8646   0.2099
  -7.500  -0.6740   0.00968   0.00430  -0.0343   0.8550   0.2239
  -7.250  -0.6547   0.00949   0.00415  -0.0326   0.8453   0.2363
  -7.000  -0.6324   0.00942   0.00402  -0.0315   0.8361   0.2385
  -6.750  -0.6123   0.00926   0.00387  -0.0300   0.8272   0.2489
  -6.500  -0.5913   0.00913   0.00374  -0.0286   0.8177   0.2572
  -6.250  -0.5695   0.00902   0.00361  -0.0274   0.8079   0.2637
  -6.000  -0.5476   0.00892   0.00349  -0.0262   0.7975   0.2714
  -5.750  -0.5260   0.00881   0.00338  -0.0249   0.7862   0.2785
  -5.500  -0.5027   0.00875   0.00326  -0.0239   0.7741   0.2822
  -5.250  -0.4818   0.00862   0.00312  -0.0224   0.7616   0.2875
  -5.000  -0.4597   0.00855   0.00300  -0.0212   0.7467   0.2926
  -4.750  -0.4367   0.00850   0.00290  -0.0201   0.7322   0.2976
  -4.500  -0.4154   0.00841   0.00277  -0.0187   0.7153   0.3030
  -4.250  -0.3927   0.00836   0.00267  -0.0176   0.6988   0.3080
  -4.000  -0.3701   0.00833   0.00257  -0.0164   0.6814   0.3130
  -3.750  -0.3482   0.00827   0.00248  -0.0152   0.6641   0.3194
  -3.500  -0.3250   0.00826   0.00241  -0.0141   0.6450   0.3249
  -3.250  -0.3029   0.00821   0.00232  -0.0129   0.6270   0.3314
  -3.000  -0.2800   0.00819   0.00226  -0.0118   0.6091   0.3380
  -2.750  -0.2577   0.00817   0.00219  -0.0106   0.5907   0.3451
  -2.500  -0.2347   0.00817   0.00214  -0.0095   0.5714   0.3525
  -2.250  -0.2119   0.00815   0.00209  -0.0085   0.5541   0.3600
  -2.000  -0.1886   0.00815   0.00205  -0.0075   0.5382   0.3677
  -1.750  -0.1656   0.00813   0.00201  -0.0064   0.5230   0.3756
  -1.500  -0.1419   0.00814   0.00198  -0.0055   0.5088   0.3836
  -1.250  -0.1189   0.00813   0.00195  -0.0045   0.4952   0.3921
  -1.000  -0.0951   0.00814   0.00194  -0.0036   0.4818   0.4004
  -0.750  -0.0720   0.00814   0.00192  -0.0025   0.4698   0.4102
  -0.500  -0.0486   0.00814   0.00191  -0.0016   0.4588   0.4195
   0.000  -0.0008   0.00812   0.00190   0.0002   0.4387   0.4388
   0.500   0.0471   0.00814   0.00191   0.0019   0.4193   0.4587
   0.750   0.0704   0.00814   0.00192   0.0029   0.4103   0.4701
   1.000   0.0936   0.00814   0.00194   0.0039   0.4006   0.4823
   1.250   0.1173   0.00813   0.00196   0.0048   0.3921   0.4955
   1.500   0.1404   0.00814   0.00199   0.0059   0.3837   0.5088
   1.750   0.1641   0.00813   0.00201   0.0068   0.3757   0.5229
   2.000   0.1871   0.00815   0.00205   0.0078   0.3679   0.5379
   2.250   0.2104   0.00815   0.00209   0.0088   0.3600   0.5541
   2.500   0.2331   0.00817   0.00215   0.0099   0.3526   0.5717
   2.750   0.2562   0.00818   0.00220   0.0110   0.3449   0.5897
   3.000   0.2787   0.00820   0.00226   0.0121   0.3379   0.6080
   3.250   0.3013   0.00821   0.00233   0.0133   0.3308   0.6266
   3.500   0.3211   0.00835   0.00239   0.0149   0.3037   0.6446
   3.750   0.3428   0.00841   0.00247   0.0162   0.2937   0.6645
   4.000   0.3651   0.00845   0.00256   0.0174   0.2864   0.6819
   4.250   0.3860   0.00857   0.00266   0.0188   0.2713   0.6985
   4.500   0.4072   0.00867   0.00277   0.0202   0.2595   0.7155
   4.750   0.4238   0.00897   0.00294   0.0224   0.2264   0.7310
   5.000   0.4427   0.00917   0.00310   0.0242   0.2074   0.7473
   5.500   0.4398   0.01132   0.00446   0.0348   0.0178   0.7741
   5.750   0.4569   0.01156   0.00470   0.0370   0.0045   0.7867
   6.000   0.4754   0.01170   0.00487   0.0388   0.0045   0.7987
   6.250   0.4943   0.01187   0.00509   0.0406   0.0042   0.8096
   6.500   0.5141   0.01205   0.00532   0.0421   0.0041   0.8204
   6.750   0.5344   0.01227   0.00559   0.0435   0.0040   0.8304
   7.000   0.5548   0.01249   0.00586   0.0448   0.0040   0.8406
   7.250   0.5782   0.01274   0.00617   0.0455   0.0040   0.8501
   7.500   0.6022   0.01301   0.00650   0.0459   0.0040   0.8604
   7.750   0.6277   0.01332   0.00687   0.0459   0.0040   0.8714
   8.000   0.6596   0.01367   0.00731   0.0445   0.0040   0.8827
   8.250   0.6999   0.01404   0.00774   0.0413   0.0040   0.8939
   8.500   0.7463   0.01462   0.00844   0.0366   0.0040   0.9073
   8.750   0.7970   0.01533   0.00928   0.0308   0.0041   0.9230
   9.000   0.8495   0.01625   0.01030   0.0245   0.0042   0.9353
   9.250   0.9002   0.01732   0.01147   0.0185   0.0042   0.9450
   9.500   0.9192   0.01849   0.01273   0.0188   0.0043   0.9960
   9.750   0.9544   0.01957   0.01388   0.0156   0.0044   1.0000
  10.000   0.9603   0.02032   0.01467   0.0184   0.0044   1.0000
  10.250   0.9651   0.02124   0.01563   0.0210   0.0045   1.0000
  10.500   0.9701   0.02230   0.01674   0.0232   0.0045   1.0000
  10.750   0.9760   0.02344   0.01793   0.0251   0.0046   1.0000
  11.000   0.9800   0.02481   0.01937   0.0268   0.0046   1.0000
  11.250   0.9836   0.02637   0.02100   0.0282   0.0048   1.0000
  11.500   0.9752   0.02904   0.02383   0.0299   0.0052   1.0000
  11.750   0.9756   0.03122   0.02608   0.0306   0.0052   1.0000
  12.000   0.9723   0.03391   0.02887   0.0310   0.0053   1.0000
  12.250   0.9678   0.03692   0.03197   0.0311   0.0054   1.0000
  12.500   0.9555   0.04087   0.03603   0.0309   0.0056   1.0000
  12.750   0.9218   0.04671   0.04196   0.0312   0.0062   1.0000
<< Back to US1000ROOT (us1000root-il)

Polar data table (+)

Polar graphs


<< Back to US1000ROOT (us1000root-il)