Status Report

NASA LaRC Solicitation: Crew Launch Vehicle Wind Tunnel Test in Polysonic Test Facility

By SpaceRef Editor
August 30, 2006
Filed under , ,
NASA LaRC Solicitation: Crew Launch Vehicle Wind Tunnel Test in Polysonic Test Facility
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Synopsis – Aug 30, 2006
General Information
Solicitation Number: NNL06173318Q
Posted Date: Aug 30, 2006
FedBizOpps Posted Date: Aug 30, 2006
Original Response Date: Sep 11, 2006
Current Response Date: Sep 11, 2006
Classification Code: R — Professional, administrative, and mgmt support services
NAICS Code: 488190 – Other Support Activities for Air Transportation

Contracting Office Address

NASA/Langley Research Center, Mail Stop 144, Industry Assistance Office, Hampton, VA 23681-0001

Description

NASA/LaRC has a requirement to conduct a wind tunnel test in a Polysonic Wind Tunnel. The Crew Launch Vehicle project is preparing an aerodynamic database that characterizes the vehicle throughout the speed regime of ascent flight where aerodynamic effects are important. This speed regime begins at liftoff and continues through first-stage separation or about Mach 6. The aerodynamic database will be used to determine the CLV performance, stability & control effectiveness and structural stability. Verification of the loads database produced using Computational Fluid Dynamics (CFD) is needed through comparison with wind tunnel data from a pressure instrumental model.

NASA/LaRC intends to purchase the services from Boeing, Inc. who is the only known responsible source. To support the assessment of the CLV configuration, the data to develop the aerodynamic database is required over the ascent Mach range. A 0.01-scale ( ~ 38″ long) wind tunnel model has been built to test at NASA LaRC’s Unitary Plan Wind Tunnel, for the Mach range 1.5-4.6. Data is required at the lower speeds for the initial phase of ascent. The Boeing Polysonic wind tunnel test covers the Mach range 0.4-1.6 providing data for the early ascent phase for CLV flight. This facility allows the use of the existing model and sting hardware. There are no NASA facilities available with this Mach range and size. The Boeing Polysonic tunnel is the only known blow-down facility with the specific Mach number range, Reynolds number, and size to satisfy the wind tunnel testing requirement. Also, to eliminate tunnel to tunnel differences, both the force and moment model and the pressure model should be tested in the same facilities. The force and moment model was tested in the Boeing Polysonic facility due to CLVs specific test requirements, so for the complimentary pressure model, the Boeing Polysonic facility is also required. The authority for this action is the test program for commercial items (section 4202 of the Clinger-Cohen Act of 1996), and 10 USC 2304(c)(1). The Government intends to acquire a commercial item using FAR Part 12 and Part 13.5, Test Program for Certain Commercial Items.

Interested organizations may submit their capabilities and qualifications to perform the effort in writing to the identified point of contact not later than 4:30 p.m. local time on September 11, 2006. Such capabilities/qualifications will be evaluated solely for the purpose of determining whether or not to conduct this procurement on a competitive basis. A determination by the Government not to compete this proposed effort on a full and open competition basis, based upon responses to this notice, is solely within the discretion of the government.

Oral communications are not acceptable in response to this notice. All responsible sources may submit an offer which shall be considered by the agency. An Ombudsman has been appointed. See NASA Specific Note “B”. Any referenced notes may be viewed at the following URLs linked below.

Point of Contact

Name: Panice H. Clark
Title: Contracting Officer
Phone: (757) 864-2522
Fax: (757) 864-8541
Email: Panice.H.Clark@nasa.gov

SpaceRef staff editor.