Skip Navigation
SBIR/STTR

Hypersonic Free-Flight Measurement of Aeroshell Forces and Flowfields, Phase I

Completed Technology Project

Project Introduction

Hypersonic Free-Flight Measurement of Aeroshell Forces and Flowfields, Phase I
A Hypersonic Gun Tunnel and laser based high speed imaging systems will be used to generate a unique, free flight, aerodynamic data base of potential Mars aeroshell configurations. These experiments will provide reliable bench mark data for CFD code validation and help aerocapture modeling and optimize aeroshell payload and design. The experiments will be conducted at hypersonic Mach numbers in air and in simulated Martian atmospheric test gases and will cover the hypersonic continuum flow regime. The innovative test results will help improve aerocapture analysis and prediction techniques that will lead to reduced deceleration propellant launch weight, increased payload, and improved delivery accuracy. These improved measurement capabilities will greatly enhance U.S. commercial and military competitiveness in aerospace vehicle design and production, and help regain and stimulate a viable customer-testing base, which will help preserve and improve our national wind tunnel testing infrastructure. These new capabilities will provide significant test data improvements, which will greatly enhance our ability to understand the physical flow phenomena associated complex flows over advanced aerospace vehicles. More »

Anticipated Benefits

Primary U.S. Work Locations and Key Partners

Project Library

Share this Project

Organizational Responsibility

Project Management

Project Duration

This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.

A final report document may be available for this project. If you would like to request it, please contact us.

^