CEAS Aeronautical Journal

, Volume 9, Issue 2, pp 307–317 | Cite as

Comparison of the NASA Common Research Model European Transonic Wind Tunnel test data to NASA National Transonic Facility test data

  • Melissa RiversEmail author
  • Jürgen Quest
  • Ralf Rudnik
Original Paper


Experimental aerodynamic investigations of the NASA Common Research Model have been conducted in the NASA Langley National Transonic Facility and the European Transonic Wind Tunnel. Data have been obtained at chord Reynolds numbers of 5, 19.8 and 30 million for the wing/body/tail = 0° incidence configuration in the National Transonic Facility and in the European Transonic Wind Tunnel. Force and moment, surface pressure, wing bending and twist, and surface flow visualization data were obtained in both facilities but only the force and moment, and surface pressure data are presented herein.


Transonic Reynolds number Wind tunnel Comparison 

List of symbols


Wing span


Wing mean aerodynamic chord


Drag coefficient


Lift coefficient


Pitching moment coefficient referenced to 0.25 of the wing mean aerodynamic chord


Pressure coefficient


Common Research Model


Drag prediction workshop


Modulus of elasticity


European Strategic Wind Tunnels Improved Research Potential


Freestream Mach number


National Transonic Facility


Total pressure


Dynamic pressure


Reynolds number based on mean aerodynamic chord


Model reference area


Total temperature


Wing/body/tail = 0°


Longitudinal distance from wing leading edge nondimensionalized by local wing chord


Angle of attack, degree


Fraction of wing semi-span


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Copyright information

© US Government (outside the USA)  2017

Authors and Affiliations

  1. 1.NASA Langley Research CenterHamptonUSA
  2. 2.ETW, European Transonic Wind TunnelKölnGermany
  3. 3.DLR, German Aerospace CenterKölnGermany

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