Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721267156
Category :
Languages : en
Pages : 34
Book Description
This report describes the NASA Langley 16-Ft. Transonic Tunnel Pressure Sensitive Paint (PSP) System and presents results of a test conducted June 22-23, 2000 in the tunnel to validate the PSP system. The PSP system provides global surface pressure measurements on wind tunnel models. The system was developed and installed by PSP Team personnel of the Instrumentation Systems Development Branch and the Advanced Measurement and Diagnostics Branch. A discussion of the results of the validation test follows a description of the system and a description of the test. Sprinkle, Danny R. and Obara, Clifford J. and Amer, Tahani R. and Leighty, Bradley D. and Carmine, Michael T. and Sealey, Bradley S. and Burkett, Cecil G. Langley Research Center NASA/TM-2001-211017, NAS 1.15:211017, L-18048
Langley 16- Ft. Transonic Tunnel Pressure Sensitive Paint System
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721267156
Category :
Languages : en
Pages : 34
Book Description
This report describes the NASA Langley 16-Ft. Transonic Tunnel Pressure Sensitive Paint (PSP) System and presents results of a test conducted June 22-23, 2000 in the tunnel to validate the PSP system. The PSP system provides global surface pressure measurements on wind tunnel models. The system was developed and installed by PSP Team personnel of the Instrumentation Systems Development Branch and the Advanced Measurement and Diagnostics Branch. A discussion of the results of the validation test follows a description of the system and a description of the test. Sprinkle, Danny R. and Obara, Clifford J. and Amer, Tahani R. and Leighty, Bradley D. and Carmine, Michael T. and Sealey, Bradley S. and Burkett, Cecil G. Langley Research Center NASA/TM-2001-211017, NAS 1.15:211017, L-18048
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721267156
Category :
Languages : en
Pages : 34
Book Description
This report describes the NASA Langley 16-Ft. Transonic Tunnel Pressure Sensitive Paint (PSP) System and presents results of a test conducted June 22-23, 2000 in the tunnel to validate the PSP system. The PSP system provides global surface pressure measurements on wind tunnel models. The system was developed and installed by PSP Team personnel of the Instrumentation Systems Development Branch and the Advanced Measurement and Diagnostics Branch. A discussion of the results of the validation test follows a description of the system and a description of the test. Sprinkle, Danny R. and Obara, Clifford J. and Amer, Tahani R. and Leighty, Bradley D. and Carmine, Michael T. and Sealey, Bradley S. and Burkett, Cecil G. Langley Research Center NASA/TM-2001-211017, NAS 1.15:211017, L-18048
Langley 16-ft. Transonic Tunnel Pressure Sensitive Paint System
Author: Danny R. Sprinkle
Publisher:
ISBN:
Category : Fluid dynamic measurements
Languages : en
Pages : 22
Book Description
This report describes the NASA Langley 16-Ft. Transonic Tunnel Pressure Sensitive Paint (PSP) system and presents results of a test conducted June 22-23, 2000 in the tunnel to validate the PSP system. The PSP system provides global surface pressure measurements on wind tunnel models. The system was developed and installed by PSP Team personnel of the Instrumentation Systems Development Branch and the Advanced Measurement and Diagnostics Branch. A discussion of the results of the validation test follows a description of the system and a description of the test.
Publisher:
ISBN:
Category : Fluid dynamic measurements
Languages : en
Pages : 22
Book Description
This report describes the NASA Langley 16-Ft. Transonic Tunnel Pressure Sensitive Paint (PSP) system and presents results of a test conducted June 22-23, 2000 in the tunnel to validate the PSP system. The PSP system provides global surface pressure measurements on wind tunnel models. The system was developed and installed by PSP Team personnel of the Instrumentation Systems Development Branch and the Advanced Measurement and Diagnostics Branch. A discussion of the results of the validation test follows a description of the system and a description of the test.
The NASA Langley 16-foot Transonic Tunnel: Historical Overview, Facility Description, Calibration, Flow Characteristics, and Test Capabilities
Author: Francis J. Capone
Publisher:
ISBN:
Category : Transonic wind tunnels
Languages : en
Pages : 208
Book Description
Publisher:
ISBN:
Category : Transonic wind tunnels
Languages : en
Pages : 208
Book Description
Flow-visualization Techniques Used at High Speed by Configuration Aerodynamics Wind-tunnel-test Team
Author: John E. Lamar
Publisher:
ISBN:
Category : High-speed aeronautics
Languages : en
Pages : 36
Book Description
This paper summarizes a variety of optically based flow-visualization techniques used for high-speed research by the Configuration Aerodynamics Wind-Tunnel-Test Team of the High-Speed Research Program during its tenure. The work of other national experts is included for completeness. Details of each technique with applications and status in various national wind tunnels are given.
Publisher:
ISBN:
Category : High-speed aeronautics
Languages : en
Pages : 36
Book Description
This paper summarizes a variety of optically based flow-visualization techniques used for high-speed research by the Configuration Aerodynamics Wind-Tunnel-Test Team of the High-Speed Research Program during its tenure. The work of other national experts is included for completeness. Details of each technique with applications and status in various national wind tunnels are given.
Monthly Catalog of United States Government Publications
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 882
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 882
Book Description
NASA Langley Scientific and Technical Information Output-2001
NASA Technical Memorandum
Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (F-16XL-1) at Subsonic and Transonic Speeds
Author: John E. Lamar
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 170
Book Description
Geometrical, flight, computational fluid dynamics (CFD), and wind-tunnel studies for the F-16XL-1 airplane are summarized over a wide range of test conditions. Details are as follows: (1) For geometry, the upper surface of the airplane and the numerical surface description compare reasonably well. (2) For flight, CFD, and wind-tunnel surface pressures, the comparisons are generally good at low angles of attack at both subsonic and transonic speeds; however, local differences are present. In addition, the shock location at transonic speeds from wind-tunnel presure contours is near the aileron hinge line and generally is in correlative agreement with flight results.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 170
Book Description
Geometrical, flight, computational fluid dynamics (CFD), and wind-tunnel studies for the F-16XL-1 airplane are summarized over a wide range of test conditions. Details are as follows: (1) For geometry, the upper surface of the airplane and the numerical surface description compare reasonably well. (2) For flight, CFD, and wind-tunnel surface pressures, the comparisons are generally good at low angles of attack at both subsonic and transonic speeds; however, local differences are present. In addition, the shock location at transonic speeds from wind-tunnel presure contours is near the aileron hinge line and generally is in correlative agreement with flight results.