**Nominal Configuration (inboard/outboard flap angles on 40/37 deg):**- HLPW-4_CRM-HL_40-37_Nominal_v2_IGES.zip (zipped, 21.2 MB) <- new as of 10/13/2020
- HLPW-4_CRM-HL_40-37_Nominal_v2_STEP.zip (zipped, 19.7 MB) <- new as of 10/13/2020

**Inboard/outboard flap angles of 37/34 deg:**- HLPW-4_CRM-HL_37-34_v2_IGES.zip (zipped, 19.4 MB) <- new as of 10/13/2020
- HLPW-4_CRM-HL_37-34_v2_STEP.zip (zipped, 19.8 MB) <- new as of 10/13/2020

**Inboard/outboard flap angles of 43/40 deg:**- HLPW-4_CRM-HL_43-40_v2_IGES.zip (zipped, 19.5 MB) <- new as of 10/13/2020
- HLPW-4_CRM-HL_43-40_v2_STEP.zip (zipped, 19.8 MB) <- new as of 10/13/2020

- Model Boundary Layer Trip Guide - NASA 10% semi-span model tested in QinetiQ 5 Metre WT (pdf file, version 1)
- tripcurves.igs (IGES file with curves defining the locations where trip dots were placed on the WT model; needs to be read in along with the CRM-HL geometry)

- Mean aerodynamic chord (MAC) = 275.8 in, located at y=468.75 in
- Use the MAC as the x-direction length to nondimensionalize pitching moment about the moment reference center (see Q12/A12 on the FAQs page)
- Reference area of the semi-span model = Sref/2 = 297,360.0 in
^{2} - Moment reference center (MRC): x=1325.90 in, y=0.0 in, z=177.95 in
- Wing semi-span (b/2) = 1156.75 in
- Aspect Ratio (AR) = b
^{2}/Sref = 9.0 - In the wind tunnel, the standoff did not contribute to forces or moment

- Q5m_Tunnel_Modeling_V01.pdf (informational pdf file)
- q5m_forHLPW4.igs (IGES file of tunnel geometry)
- standoff_simple.igs (IGES file of standoff geometry)

- TempProbe 1: (-6467.3414, 2121.9242, 1096.6220)
- TempProbe 2: (-6467.3414, 2121.9242, -700.6220)
- TempProbe 3: (-6467.3414, -543.4989, 1096.6220)
- TempProbe 4: (-6467.3414, -543.4989, -700.6220)
- PTprobeTip: (-6388.1923, -965.9338, 1847.6063)
- S3Static (Max): (-4873.4423, -1043.0073, -1737.6408)
- S1Static (Noz): (-2102.6710, 1636.0441, 198.000)
- BL Rake: On floor at (X,Y,Z) = (54.2717, -35.000, -152.2203), with Y range from -35.00 to 35.8662 inches

- Use inviscid thermodynamic relations with the desired reference Mach number (Mach=0.2) to obtain total pressure (Pt) and total temperature (Tt) (relative to the reference static pressure and reference static temperature, respectively) at the tunnel inlet. Apply an appropriate inlet BC that fixes these total values; this inlet BC remains unchanged throughout the iterative procedure.
- Set static pressure BC at tunnel outflow boundary. (A typical starting value might be slightly lower than that
required for an empty tunnel; see
AIAA-2017-4126 for an example in a different wind tunnel.
In the QinetiQ tunnel geometry, the area ratio between the test section and downstream boundary
is approximately A
_{min}/A_{exit}= 0.474.#### An estimated starting back pressure for the provided QinetiQ tunnel configuration is P

_{exit}/P_{ref}≈ 1.02. - Run CFD solver.
- Use temperature (average of 4 probe locations), pressures, and total pressure computed by CFD at the tunnel probe locations, along with the tunnel calibrations (described in above Q5m_Tunnel_Modeling_V01.pdf file) to calculate q/Pt and Mach in the CFD run. Note, in an empty tunnel, the computed Mach should also be achieved (seen) at the tunnel's calibration reference location ((X,Y,Z)=(1227.5, 791.7717, 198.00) in the provided scale). However, when a test article is present in the tunnel, the computed Mach value is based on the calibration only.
- Iterate steps 2-5 until the computed Mach is within a desired tolerance (preferably within 0.195 - 0.205); i.e., if the computed Mach number comes out too high, then raise the back pressure, if too low then lower the back pressure. You may need to experiment to determine the effect, and use linear interpolation to determine the next back pressure to try (for example, if p_back1 yields M1 and p_back2 yields M2 (and neither M1 nor M2 is close enough to the goal of M=0.2), then try p_back = p_back1 + [(0.2 - M1)*(p_back2 - p_back1)/(M2 - M1)]). Note that this iterative procedure can take time. Once converged, other conditions, particularly Re, should also be checked using inviscid thermodynamic relations.
- Note that the required back pressure may be different for every case (it could be affected by the grid and the angle of incidence of the model in the tunnel).

- 2-D Multielement Airfoil based on CRM-HL
- NASA Juncture Flow Model F6-based wing and body
__with__horn/leading edge extension (Tests 640 and 653)) - NASA Wall Mounted Hump Model

Link to: Grids Page

Link to: Test Cases Page

Return to: High Lift Prediction Workshop Home Page

Recent significant updates:

02/18/2021 - Added estimated starting back pressure setting for in-tunnel iterative procedure

01/25/2021 - Added Tunnel Probe Locations and typical CFD procedure for running in tunnel

12/18/2020 - Added QinetiQ Wind Tunnel geometry files and information

12/17/2020 - Added clarification regarding use of MAC as the length to nondimensionalize the pitching moment

11/18/2020 - Added link to NASA wall-mounted hump website

10/20/2020 - Added additional suggestions in red regarding problems/issues

10/13/2020 - Posted V2 geometry files and farfield/symmetry plane definition

09/25/2020 - Added tripping information from QinetiQ test

09/24/2020 - Added links to other geometry files

09/09/2020 - Updated note regarding STEP file details

**Responsible NASA Official:**
Christopher Rumsey

**Page Curator:**
Christopher Rumsey

**Last Updated:** 02/20/2021