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ULTIMATE (ultimate-il)

ULTIMATE - Carl Goldberg R/C Ultimate Bipe airfoil


Airfoil ultimate-il
Details Dat file Parser  
(ultimate-il) ULTIMATE
Carl Goldberg R/C Ultimate Bipe airfoil
Max thickness 12.8% at 34.2% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  ULTIMATE
 1.000000       0.002886
 0.997540       0.002863
 0.990700       0.003094
 0.980370       0.004027
 0.966980       0.005805
 0.950440       0.008274
 0.930640       0.011103
 0.907750       0.013982
 0.882020       0.016972
 0.853700       0.020447
 0.823090       0.024581
 0.790480       0.029046
 0.756160       0.033444
 0.720430       0.037602
 0.683590       0.041508
 0.645940       0.045227
 0.607780       0.048794
 0.569370       0.052159
 0.530990       0.055209
 0.492650       0.057869
 0.454350       0.060114
 0.416380       0.061916
 0.378870       0.063171
 0.342040       0.063718
 0.306090       0.063459
 0.271200       0.062388
 0.237600       0.060562
 0.205490       0.058079
 0.175040       0.055033
 0.146480       0.051474
 0.119990       0.047391
 0.095760       0.042768
 0.073950       0.037669
 0.054680       0.032282
 0.038110       0.026863
 0.024330       0.021542
 0.013380       0.016225
 0.005480       0.010723
 0.000980       0.004912
 0.000000       0.000533
 0.000980      -0.003898
 0.005480      -0.009945
 0.013380      -0.015812
 0.024330      -0.021543
 0.038110      -0.027258
 0.054680      -0.032984
 0.073950      -0.038571
 0.095760      -0.043818
 0.119990      -0.048597
 0.146480      -0.052838
 0.175040      -0.056512
 0.205490      -0.059595
 0.237600      -0.062030
 0.271200      -0.063725
 0.306090      -0.064621
 0.342040      -0.064754
 0.378870      -0.064245
 0.416380      -0.063248
 0.454350      -0.061870
 0.492650      -0.060119
 0.530990      -0.057952
 0.569370      -0.055317
 0.607780      -0.052206
 0.645940      -0.048690
 0.683590      -0.044885
 0.720430      -0.040929
 0.756160      -0.036957
 0.790480      -0.033065
 0.823090      -0.029257
 0.853700      -0.025505
 0.882020      -0.021977
 0.907750      -0.018951
 0.930640      -0.016575
 0.950440      -0.014660
 0.966980      -0.012681
 0.980370      -0.010169
 0.990700      -0.007092
 0.997540      -0.004180
 0.999983      -0.002918
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Lednicer format dat file
Selig format dat file

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Polars for ULTIMATE (ultimate-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ultimate-il50,000928.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ultimate-il50,000527.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ultimate-il100,000939 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ultimate-il100,000536.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ultimate-il200,000947.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ultimate-il200,000542 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ultimate-il500,000955.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ultimate-il500,000553.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ultimate-il1,000,000963.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ultimate-il1,000,000567 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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