This Solicitation opportunity from Government of Canada was posted on March 5, 2026. The submission period has ended. Browse the details below for market research, or find similar active opportunities.

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Tomographic PIV System

Closed

25-58142-ACanada

Submission Closed04/07/2026, 07:00:00 PM UTC

Contract Overview

Solicitation details, issuing organization, response deadlines, documents, and interested companies for this government contract opportunity.

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NAICS: 541715

New

Federal

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Marshall Space Flight Center

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Armstrong Flight Research Center

POSTED

in 7 months

DEADLINE

N/A

General Info

Agency

Government of Canada → National Research Council of Canada

NAICS

541715 - Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) View NAICS

Place of Performance

CAN

Set-Aside

NONE

Documents

(4)

RFP 25-58142-A Tomographic PIV System

PDF•50 pages•rfp

RFP 25-58142-A Tomographic PIV System Q&A

PDF•q-and-a

Notice of Proposed Procurement for Tomographic PIV System 25 58142 A

PDF•4 pages•presolicitation

RFP 25-58142-A PIV System Tomographic

PDF•53 pages•rfp

AI Contract Breakdown

Uniform Contract Format

Timeline

PhaseClosed

PostedMar 5

Solicitation

Response DeadlineApr 7

Deadline has passed

Submission Closed

04/07/2026, 07:00:00 PM UTC

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Organization & Contact Information

AgencyGovernment of Canada → National Research Council of Canada

Contacts1 person available

OfficeN/A

Organization / Agency

Government of Canada → National Research Council of Canada

Office AddressN/A

Contacts

Mike CoxContracting Authority

contact@example.gov

+1 (555) 000-0000

Full Description

The objective is to acquire a compact, multi-camera system for conducting high-resolution volumetric flow measurements using Tomographic PTV and Tomographic PIV techniques. The system will be deployed in a wind tunnel setup to investigate jet-in-crossflow (JICF) configurations relevant to effusion and transpiration cooling strategies. These measurements will provide critical insight into boundary layer behavior, jet penetration, mixing efficiency, turbulence intensity, and unsteady flow structures within the cooling film. The resulting data will support the fundamental understanding and optimization of gas turbine engine liner cooling systems. By improving the effectiveness of these cooling techniques, the research contributes to enhancing engine thermal efficiency and enabling the adoption of advanced combustion technologies. The system enables the acquisition of full three-dimensional velocity fields data that would otherwise only be accessible through numerical simulations.