Abe Silverstein 10- by 10-Foot Supersonic Wind Tunnel Validated for Low-Speed (Subsonic) Operation

· NASA (NTRS) · 2001

Public domain · NASA (NTRS)Technical Reports

Overview

The NASA Glenn Research Center and Lockheed Martin Corporation tested an aircraft model in two wind tunnels to compare low-speed (subsonic) flow characteristics. Objectives of the test were to determine and document the similarities and uniqueness of the tunnels and to validate that Glenn's 10- by…

Publisher: NASA (NTRS)
Document
Year: 2001
Pages: 2

Key points

The 10×10 Supersonic Wind Tunnel (SWT) at NASA Glenn has been validated as a viable low-speed test facility.
The test compared low-speed flow characteristics of the 10×10 SWT with the 836 SWT using a Lockheed Martin Joint Strike Fighter model.
Data collected showed that the 10×10 SWT can operate effectively at flight speeds ranging from 0 to 250 knots.
Most data comparisons between the 8×6 and 10×10 SWT's were within a 0.5-percent range, with some variations up to 1 percent.
The test objectives included verifying the 10×10 SWT's viability and comparing model data at various low-speed conditions.

Frequently asked questions

What was the purpose of the tests conducted in the 10×10 SWT?

The tests aimed to determine and document the similarities and uniqueness of the wind tunnels and to validate the 10×10 SWT as a viable low-speed test facility.

What aircraft model was used for the testing?

The Lockheed Martin Joint Strike Fighter concept demonstration aircraft model was used during the tests.

What were the results of the comparison between the 10×10 SWT and the 836 SWT?

The results showed that the data from the 10×10 SWT and the 836 SWT compared very favorably, indicating that the 10×10 SWT is a viable low-speed wind tunnel.

What is the range of flight speeds that the 10×10 SWT can accommodate?

The 10×10 SWT allows for flight speeds to be varied from 0 to 250 knots.

Who can be contacted for more information regarding the 10×10 SWT?

For more information, Albert L. Johns and Thomas R. Hoffman can be contacted at NASA Glenn.

Document

Abe Silverstein 10- by 10-Foot Supersonic

Wind Tunnel Validated for Low-Speed

(Subsonic) Operation

Lockheed Martin Joint Strike Fighter concept demonstration aircraft model installed at Glenn's 10- by 10-Foot Supersonic Wind Tunnel.

The NASA Glenn Research Center and Lockheed Martin Corporation tested an aircraft model in two wind tunnels to compare low-speed (subsonic) flow characteristics.

Objectives of the test were to determine and document the similarities and uniqueness of the tunnels and to validate that Glenn's 10- by 10-Foot Supersonic Wind Tunnel (10×10 SWT) is a viable low-speed test facility. Results from two of Glenn's wind tunnels compare very favorably and show that the 10×10 SWT is a viable low-speed wind tunnel.

The Subsonic Comparison Test was a joint effort by NASA and Lockheed Martin using the Lockheed Martin's Joint Strike Fighter Concept Demonstration Aircraft model.

Although Glenn's 10310 and 836 SWT's have many similarities, they also have unique characteristics. Therefore, test data were collected for multiple model configurations at various vertical locations in the test section, starting at the test section centerline and extending into the ceiling and floor boundary layers.

The stated test objectives are as follows: Verify that the 10×10 SWT is a viable subsonic test facility. • Compare and validate model data of the 10×10 SWT versus the 836 SWT at • multiple low-speed conditions and model positions.

In conclusion, The 10×10 SWT is a viable low-speed test facility (from the standpoint of data 1.

quality), allowing flight speed to be varied from 0 to 250 knots.

The maneuver range is similar to that for the 8×6 SWT because of existing 2.

boundary layers in the 10×10 SWT test section.

A comparison of data from the 8×6 and 10×10 SWT's shows that the data are 3.

within an acceptable range. Most data are within a 0.5-percent range, with some data in a range up to 1 percent that may have resulted from adding unmatched parameters, such as angle of attack, angle of slip, and exhaust flow.

Glenn contacts: Albert L. Johns, 216-433-3972, Albert.L.Johns@grc.nasa.gov; and Thomas R. Hoffman, 216-433-5637, Thomas.R.Hoffman@grc.nasa.gov Author: Thomas R. Hoffman Headquarters program office: OAT Programs/Projects: Propulsion Systems R&T