DPW8 Test Cases

Verification Activity

Verification 1: ONERA OAT15A Airfoil (Required)
ONERA OAT15A Airfoil
Working Group Test Case
Sources of Scatter 1a & 1c
Wind Tunnel Environment 1a
Static Deformation (AePW) 1a
Buffet (AePW) 1a & 1b

Objectives and Description

  • Validation of steady CFD analysis grid convergence study and polar
  • Users are encouraged to employ best practices
  • Steady CFD (e.g., RANS)
  • Multiple turbulence models can be submitted
  • Grids
    • Six-member grid family; four are required, six are desirable
    • Use periodic boundary conditions for sidewall boundary conditions
    • Encourage use of committee-supplied grids
    • User-generated grids are acceptable (see guidelines)
  • Flow Conditions
    • Mach=0.73, Rec=3x106, TStatic=271.K (487.8 R)

Test Cases

V1a: Grid Convergence and Polar
  • Settings:
    • Flow Conditions: α = [1.36°, 1.50°, 2.50°, 3.00°, 3.10°]
    • Grid Levels: [1,2,3,4,5,6]
V1b: Extended Polar (Unsteady) [Buffet WG Test Case 1b]
  • Settings:
    • Unsteady analysis
    • Flow Conditions: α = [3.25°, 3.40°, 3.50°, 3.60°, 3.90°]
    • Grid Levels: [1,2,3,4,5,6]
V1c: Scatter Reduction Reprise [Scatter WG Test Case 1c]
  • Additional Instructions for the Source of Scatter Working Group:
    • Use updated grid families with common farfield (1000 chords away)
    • French Vanilla SA-(neg) (All-terms)
    • Sutherland's Law
    • Adiabatic Wall (not isothermal)
    • Converge residuals to machine precision (~1e-10)
  • Additional Flow Conditions for the Source of Scatter Working Group:
    • γ = 1.4, Pr = 0.72, PrT = 0.9
    • farfield Χ = ν/ν~ = 3

Verification 2: Joukowski Airfoil
Joukowski Airfoil
Working Group Test Case
Sources of Scatter 1b

Objectives and Description

  • Validation of steady CFD analysis grid convergence study
  • Build on work of the High-Fidelity CFD Verification Workshop RANS WG
  • Settings
    • Steady CFD (e.g., RANS)
    • French Vanilla SA-(neg) (All-terms)
    • Converge residuals to machine precision (~1e-10)
    • Adiabatic Wall (not isothermal)
    • Sutherland's Law
    • Grids
      • Use python script to generate grid family (recommend Classic family)
      • Six-member grid family; four are required, six are desirable
      • Use periodic boundary conditions for sidewall boundary conditions
      • Encourage use of committee-supplied grids
      • User-generated grids are acceptable (see guidelines)
    • Grids
      • Six-member grid family; four are required, six are desirable
      • Use periodic boundary conditions for sidewall boundary conditions
      • Encourage use of committee-supplied grids
      • User-generated grids are acceptable (see guidelines)

Test Cases

V2: Grid Convergence Study [Scatter WG Test Case 1b]
  • Settings:
    • Flow Conditions:
      • Mach=0.15, Rec=6x106, TStatic=520.0 R
      • γ = 1.4, Pr = 0.72, PrT = 0.9
      • farfield Χ = ν/ν~ = 3
      • α = 0.0°
    • Grid Levels: [1,2,3,4,5,6]

Verification 3: DPW-III Wing Increment: W1/W2
DPW3 Wing 1 & 2
Working Group Test Case
Sources of Scatter 1d & 1e

Objectives and Description

  • Validation of steady CFD analysis grid convergence study
  • Repeat of DPW III W1 & W2 (20 years later)
  • Users are encouraged to employ best practices
  • Settings:
  • Grids:
  • Reference Parameters:

Test Cases

V3a: Grid Convergence [Sources of Scatter WG Test Case: 1d]
  • Flow Conditions:
    • Mach=0.76, Rec=5x106, TStatic=580.0 R (322.22 K)
    • γ = 1.4, Pr = 0.72, PrT = 0.9
    • farfield Χ = ν/ν~ = 3
    • α = 0.5°
  • Grid Levels: [1,2,3,4,5,6]
V3b: Polar: [Sources of Scatter WG Test Case: 1e]
  • Flow Conditions:
    • Mach=0.76, Rec=5x106, TStatic=580.0 R (322.22 K)
    • γ = 1.4, Pr = 0.72, PrT = 0.9
    • farfield Χ = ν/ν~ = 3
    • α = [-1.0°, 0.0°, 0.5°, 1.0°, 1.5°, 2.0°, 2.5°, 3.0°]
  • Grid Level: 3 or 4

Verification 4: CRM FEM Validation
NASA CRM Finite Element Model
Working Group Test Case
Static Deformation (AePW) 1b

Objectives and Description

  • Validation of provided NASA CRM Finite Element Model

Test Cases

V4: CRM FEM Validation [Static Deformation WG Test Case 1b]
  • Settings:

Study Configurations

Configuration A: JAXA CRM Wing/Body/Tail
JAXA CRM in Tunnel
Working Group Test Case
Buffet (AePW) 2 & 3

Objectives and Description

  • Validation of unsteady CFD analysis of CRM Wing/Body/Tail(0)
  • Users are encouraged to employ best practices
  • Settings:
    • Unsteady CFD
    • Simulations executed at JAXA wind tunnel scale
    • Multiple turbulence models can be submitted
  • Flow Conditions:
    • Mach=0.85
  • Reference Units:
      • Full Scale (inches) Model Scale (meters) Tunnel Coordinates (meters)
      SREF (semispan) 297360.00 sq.in 0.179014 sq.m 0.179014 sq.m
      CREF 275.80 in 0.15131 m 0.15131 m
      Semispan 1156.75 in 1.26927 m 1.26927 m
      Moment Center (1325.9,0.0,177.95) (0.72741,0.0,0.097627) m

Test Cases

Test Case 2: Unsteady CFD / Rigid Geometry
Test Case 3: Unsteady CFD and Fluid/Structure Interaction
  • Validation of unsteady CFD analysis of CRM Wing/Body/Tail(0) with dynamic wing fluid/structural interaction
  • Geometry/Grids:
  • Goals:
    • Resolve wing structural dynamics
    • Capture as much of the spectra as reasonably possible
  • Grid Levels: [1,2,3,4,5,6]
  • Flow Conditions:
    • Mach=0.85, Rec=2.27x106, TStatic=127.4 F (326.15 K)
    • PTotal = 12.0 kPa (5.51 psi)
    • α = [3.05°, 3.61°, 4.70°]
  • Experimental Data:
    • Forces and moments, buffet coefficient intensity based on wing-root strain gauge, time-averaged/rms/PSD Cp sectional cuts from unsteady pressure sensors (Kulite), time-averaged/rms/PSD unsteady Pressure Sensitive Paint
      • https://cfdws.chofu.jaxa.jp/apc/dpw/upsp.html

Configuration B: NASA CRM Wing/Body
NASA CRM Shaded Surface
Working Group Test Case
Sources of Scatter 2a & 2b
Wind Tunnel Environment 2a & 2b & 2b(S)
Static Deformation (AePW) 2a(E) & 2b(E)

Objectives and Description

  • Validation of steady CFD analysis grid convergence study
  • Users are encouraged to employ best practices
  • Settings:
    • Steady CFD (e.g., RANS)
    • Multiple turbulence models can be submitted
  • Geometry:
  • Grids:
  • Flow Conditions:
    • Mach=0.85, Rec=5x106, TStatic=100 F (559.67 R, 310.928 K)
  • Reference Units:
      • Full Scale (inches) Model Scale Tunnel Coordinates
      SREF (semispan) 297360.00 sq.in 216.77544 sq.in 216.77544 sq.in
      CREF 275.80 in 7.51950 in 7.51950 in
      Semispan 1156.75 in 31.23225 in 31.23225 in
      Moment Center (1325.9,0.0,177.95) (35.7993,0.0,4.80465) (156.0,0.0,0.0)
  • Additional Instructions for the Source of Scatter Working Group
    • French Vanilla SA-(neg) (All-terms)
    • Converge residuals to machine precision (~1e-10)
    • Adiabatic Wall (not isothermal)
    • Sutherland's Law
    • γ = 1.4, Pr = 0.72, PrT = 0.9
    • farfield Χ = ν/ν~ = 3

Test Cases

Test Case 2a: Grid Convergence Study
  • Grid Levels: [1,2,3,4,5,6]
  • Flow Conditions:
    • α = 2.50°
Test Case 2b: Angle-of-Attack Alpha Sweep
  • Grid Level: 3 or 4
  • Flow Conditions:
    • α = [-1.50°, 2.50°, 2.75°, 3.00°, 3.25°, 3.50°, 3.75°, 4.00°, 4.25°]
    • CL = 0.50 +/- 0.0001
Test Case 2a(E) (Elastic): Grid Convergence Study
Test Case 2b(E) (Elastic): Alpha Sweep
  • Fluid/Structure Interaction (FSI) of wind tunnel model aeroelastic deformation:
  • Grid Level: 3 or 4
  • Flow Conditions:
    • α = [-1.50°, 2.50°, 2.75°, 3.00°, 3.25°, 3.50°, 3.75°, 4.00°, 4.25°]
Test Case 2b(S) (with Upper Swept Strut): Alpha Sweep

Configuration C: NASA CRM Wing/Body/Tail
CRM + Tail in Tunnel
Working Group Test Case
Wind Tunnel Environment 3b & 3b(S)

Objectives and Description

  • Validation of steady CFD analysis of CRM Wing/Body/Tail(0) with and without the Wind Tunnel Upper Swept Strut/Sting Mounting System
  • Users are encouraged to employ best practices
  • Settings:
    • Steady CFD (e.g., RANS)
    • Multiple turbulence models can be submitted
  • Geometry:
  • Grids:
    • Encourage use of committee-supplied grids
    • Encourage use of solution-adaptive grids
    • User-generated grids are acceptable (see guidelines)
  • Flow Conditions:
    • Mach=0.85, Rec=5x106, TStatic=100 F (559.67 R, 310.928 K)
  • Reference Units:
      • Full Scale (inches) Model Scale Tunnel Coordinates
      SREF (semispan) 297360.00 sq.in 216.77544 sq.in 216.77544 sq.in
      CREF 275.80 in 7.51950 in 7.51950 in
      Semispan 1156.75 in 31.23225 in 31.23225 in
      Moment Center (1325.9,0.0,177.95) (35.7993,0.0,4.80465) (156.0,0.0,0.0)

Test Cases

Test Case 3b: Angle-of-Attack Alpha Sweep
  • Flow Conditions:
    • α = [-1.50°, 2.50°, 2.75°, 3.00°, 3.25°, 3.50°, 3.75°, 4.00°, 4.25°]
    • CL = 0.50 +/- 0.0001
Test Case 3b(S) (with Upper Swept Strut): Alpha Sweep

Configuration D: NASA CRM Wing/Body/Nacelle/Pylon
CRM + Nacelle/Pylon in Tunnel
Working Group Test Case
Static Deformation (AePW) 3a (E) & 3b (E)

Objectives and Description

  • Validation of steady CFD analysis grid convergence study
  • Users are encouraged to employ best practices
  • Settings:
    • Steady CFD (e.g., RANS)
    • Multiple turbulence models can be submitted
  • Geometry:
  • Grids:
    • Encourage use of committee-supplied grids
    • Encourage use of solution-adaptive grids
    • User-generated grids are acceptable (see guidelines)
  • Flow Conditions:
    • Mach=0.85, Rec=5x106, TStatic=100 F (559.67 R, 310.928 K)
  • Reference Units:
      • Full Scale (inches) Model Scale Tunnel Coordinates
      SREF (semispan) 297360.00 sq.in 216.77544 sq.in 216.77544 sq.in
      CREF 275.80 in 7.51950 in 7.51950 in
      Semispan 1156.75 in 31.23225 in 31.23225 in
      Moment Center (1325.9,0.0,177.95) (35.7993,0.0,4.80465) (156.0,0.0,0.0)

Test Cases

Test Case 4a(E) (Elastic): Grid Convergence Study
Test Case 4b(E) (Elastic): Alpha Sweep
  • Fluid/Structure Interaction (FSI) of wind tunnel model aeroelastic deformation:
  • Grid Level: 3 or 4
  • Flow Conditions:
    • α = [-1.50°, 2.50°, 2.75°, 3.00°, 3.25°, 3.50°, 3.75°, 4.00°, 4.25°]
    • Q∞ = 1384 lb/sq.ft