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Aeroelasticity
Aeroservoelasticity
Flutter
Flight Loads



ZEUS Validation Test Cases

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Steady Subsonic, Transonic, & Supersonic Aerodynamics

Validation of Cp on the L51F07 Configuration

ZEUS subsonic and supersonic steady pressure results (invicsid and viscous) for the L51F07 Wing-Body Configuration are compared to wind tunnel results.

          



Comparison of Wing Cp, M=0.9, AoA=2°



Comparison of Body Cp, M=0.9, AoA=2°



Comparison of Wing Cp, M=1.2, AoA=2°


Comparison of Body Cp, M=1.2, AoA=2°

Lift, Moment and Drag on L56A18 Wing-Body-Tail Configuration

The L56A18 configuration and ZEUS mesh are shown below. The results that follow demonstrate ZEUS' good aerodynamic results as compared to wind tunnel (WT) and other available data.


Comparison of Normal Force Coefficient M = 0.80, 0.90, 0.94, 1.03

Comparison of Coefficient of Moment M = 0.80,0.90,0.94,1.03

Comparison of Coefficient of Drag M = 0.80,0.90,0.94,1.03

Steady Hypersonic Aerodynamics

Bent-Nose Compact Kinetic Energy Missile (CKEM) with Wrap-around Fins

  • Nine blocks of overset meshes to model the missile body and eight wrap-around fins
  • Block 1: Missile Body
  • Blocks 2-9: Eight wrap-around fins
  • CPU time for each angle of attack case is approximately 10 minutes with one CPU

Mesh on Y-Z Plane


3D View of Mesh


Lift and Moment at Mach 0.6



Unsteady Transonic Aerodynamics

Steady and Unsteady Cp on LANN Wing

  • M=0.822, α=0.6°
  • Aspect Ratio: 7.92
  • Taper Ratio: 0.4
  • Swept Angle: 25°
  • Twist from root to tip: 2.6° ~ -2.0°
  • Supercritical Airfoil with max t/c = 12%
  • Pitch mode at reduced frequency = 0.102

Steady Cp at Four Span Stations


Unsteady Cp (Real Part)


Unsteady Cp (Imaginary Part)


Flexible Aerodynamics Stability Derivatives

S4T Wind Tunnel Flutter Model

5 Blocks

  • Block 1: Aircraft, 133x78x69
  • Block 2: Trail, 55x26x50
  • Block 3: Canard, 75x21x61
  • Block 4: Inbord Engine, 73x24x36
  • Block 5: Outboard Engine, 69x23x41


Angle-of-Attack


Trailing Edge Flap


Horizontal Tail


Trim Analysis


Joined-Wing at M=0.8 and Load Factor = 2.0g


F-16 with Under-Wing Stores at M=0.95 and Load Factors = 5.0g


Flutter and LCO Analysis

Flutter Analysis of Goland Wing


LCO Analysis of Goland Wing


Flutter and LCO Analysis of the F-16 with Stores


24 Mesh Blocks Used to Model the Whole Aircraft with Under-wing Stores


Splined Structural Modes on the Aerodynamic Mesh


F-16 Tip Launcher Acceleration at AoA = 2.2° and Re=4.6x106


Flutter of the Twin Engine Transporter





Two Blocks of Overset Mesh are used: