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Calculation cases

Cases:

Four cases of CFD computation are designed in this workshop. The purpose of Case 1 and Case 2 is to analyze the effect of model wing deformation and sting interference to the detailed flow and performance at design point, and to be compared with test data.

The purpose of Case 3 and Case 4 is to analyze the effect of deformation and sting interference to the forces and moment through different angle of attack at design Mach number, and compare the CFD results with the test data (uncorrected and corrected).

Definition of model configurations:

  • CAE-AVM: free flying model with undeformed design wings (configuration: Yellow only)
  • CAE-AVM-DZ: model on Z-sting with deformed wings at test status of M=0.85 / Re=4.7 million / CL=0.515 (Yellow fuselage + Red wing + Blue sting system)

Free flying model

Symbol Notation

AOA
BL
CL
CD
Cm
Cp
M
MAC
Re
T0
: Angle of attack 
: Buttock line
: Lift coefficient defined in wind system
: Drag coefficient defined in wind system
: Pitch moment coefficient defined in body system
: Pressure distribution
: Mach number for free flow
: Mean aerodynamic chord
: Reynolds number based on MAC
: Total temperature
   



Case 1

CAE-AVM at design condition (non-deformed geometry, no support)
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Case 2

CAE-AVM-DZ at design condition (deformed geometry, with support)
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Case 3

CAE-AVM, angle of attack sweep (non-deformed geometry, no support)
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Case 4

CAE-AVM-DZ, angle of attack sweep (deformed geometry, with support)
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test