Turbulence Models: Data from Other Experiments: Shock Wave / Turbulent Boundary Layer Flows at High Mach Numbers

Shock Wave / Turbulent Boundary Layer Flows at High Mach Numbers. This web page provides data from experiments that may be useful for the validation of turbulence models. This resource is expected to grow gradually over time. All data herein arepublicly available.

Data and Resources

This dataset has no data

Field Value
accessLevel public
accrualPeriodicity irregular
bureauCode {026:00}
catalog_@context https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld
catalog_conformsTo https://project-open-data.cio.gov/v1.1/schema
catalog_describedBy https://project-open-data.cio.gov/v1.1/schema/catalog.json
identifier NASA-850__1
issued 2018-06-25
landingPage https://turbmodels.larc.nasa.gov/Other_exp_Data/cfdval2004_exp.html
modified 2025-07-17
programCode {026:023}
publisher National Aeronautics and Space Administration
references {http://turbmodels.larc.nasa.gov/index.html}
resource-type Dataset
source_datajson_identifier true
source_hash c6d7d4aef9932f42a872adcade43db56e47e1abcc95b1de4591e5238bfedf044
source_schema_version 1.1
theme {Aerospace}
Groups
  • AmeriGEOSS
  • National Provider
  • North America
Tags
  • AmeriGEO
  • AmeriGEOSS
  • CKAN
  • GEO
  • GEOSS
  • National
  • North America
  • United States
  • boundary
  • experiment
  • layer
  • mach
  • models
  • shockwave
  • turbulence
  • validation
isopen False
license_id notspecified
license_title License not specified
maintainer Christopher Rumsey
maintainer_email c.l.rumsey@nasa.gov
metadata_created 2025-09-23T22:44:15.968634
metadata_modified 2025-09-23T22:44:15.968641
notes Shock Wave / Turbulent Boundary Layer Flows at High Mach Numbers. This web page provides data from experiments that may be useful for the validation of turbulence models. This resource is expected to grow gradually over time. All data herein arepublicly available.
num_resources 0
num_tags 16
title Turbulence Models: Data from Other Experiments: Shock Wave / Turbulent Boundary Layer Flows at High Mach Numbers