AIAA CFD Drag Prediction Workshop

June 2006, San Francisco, CA

Test Cases

Either Configuration 1 or Configuration 2 or both may be presented

Configuration 1 - DLR-F6 Wing-Body with and without FX2B fairing

For all cases, Reynolds No. = 5x10⁶ (Based on c_ref = 141.2 mm), free-stream Temperature 580R ( 322.22 Kelvin)

1. DLR-F6 Wing-Body with FX2B Fairing
   - Grid convergence study at Mach=0.75, C_L=0.500 (±0.001)

2. DLR-F6 Wing-Body without fairing
   - Medium grid at Mach=0.75, C_L=0.500 (±0.001)
   or
   - Grid convergence study at Mach=0.75, C_L=0.500 (±0.001)

3. DLR-F6 Wing-Body with and without FX2B fairing (medium grid)
   - Drag Polar at Mach=0.75, alpha=-3, -2, -1, -0.5, 0, 0.5, 1, 1.5
   
   
   

• Reference Geometry:
  S_ref = 0.1454 m² (full model), c_ref = 141.2 mm, b/2=585.647 mm
  Nose Location (in CAD coordinates): x = -347.0 mm, z = 17.5 mm
  Moment Reference Center (from fuselage nose): delta(x) = 504.9 mm, delta(z) = -51.42 mm (aft and below nose)
  Moment Reference Center (in CAD coordinates): x = 157.9 mm, z = -33.92 mm

Configuration 2 - Wing Alone Comparison
  DPW-W1 - baseline
  DPW-W2 - simple optimization

For all cases, Reynolds No. = 5x10⁶ (Based on c_ref = 197.556 mm), free-stream Temperature 580R ( 322.22 Kelvin)

1. Grid convergence study at Mach=0.76, alpha=0.5

2. Drag polar at Mach=0.76, alpha=-1, 0, 0.5, 1, 1.5, 2, 2.5, 3 (medium grid)
   
   
   

• Reference Geometry:
  Sref = 290322 mm2 = 450 in2
  cref = 197.556 mm = 7.778 in
  b = 1524 mm = 60 in
  Moment Reference Center
  
  

Notes:

• Simulations are to be “free air”; no wind tunnel walls or model support systems are to be included.

• Boundary layer is to be fully turbulent.

• For the optional cases, interpolated forces and moments are acceptable (as is typically done for wind tunnel data reduction).

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