Wind Tunnel Investigation At Supersonic Speeds Of The Lift Drag Static Stability And Control Characteristics Of A 003 Scale Model Of An Interim Development Version Of The B 70 Airplane PDF Download

Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Wind Tunnel Investigation At Supersonic Speeds Of The Lift Drag Static Stability And Control Characteristics Of A 003 Scale Model Of An Interim Development Version Of The B 70 Airplane PDF full book. Access full book title Wind Tunnel Investigation At Supersonic Speeds Of The Lift Drag Static Stability And Control Characteristics Of A 003 Scale Model Of An Interim Development Version Of The B 70 Airplane.

Wind Tunnel Investigation at Supersonic Speeds of the Lift, Drag, Static-Stability and Control Characteristics of a 0.03-Scale Model of an Interim Development Version of the B-70 Airplane

Wind Tunnel Investigation at Supersonic Speeds of the Lift, Drag, Static-Stability and Control Characteristics of a 0.03-Scale Model of an Interim Development Version of the B-70 Airplane
Author: James C. Daugherty
Publisher:
Total Pages: 310
Release: 1961
Genre:
ISBN:
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Wind-tunnel Investigation of the Static Longitudinal and Lateral Stability of a 1/62-scale Model of the X-1E at Supersonic Speeds

Wind-tunnel Investigation of the Static Longitudinal and Lateral Stability of a 1/62-scale Model of the X-1E at Supersonic Speeds
Author: Arthur Henderson
Publisher:
Total Pages: 94
Release: 1956
Genre: Aerodynamics, Supersonic
ISBN:
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Download Wind-tunnel Investigation of the Static Longitudinal and Lateral Stability of a 1/62-scale Model of the X-1E at Supersonic Speeds Book in PDF, ePub and Kindle

An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the X-1E has been conducted in the Langley 9-inch supersonic tunnel. Tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete model configurations. Detailed analysis of the test results has not been made.

Wind-tunnel/flight Correlation Study of Aerodynamic Characteristics of a Large Flexible Supersonic Cruise Airplane (XB-70-1). 3: A Comparison Between Characteristics Predicted from Wind-tunnel Measurements and Those Measured in Flight

Wind-tunnel/flight Correlation Study of Aerodynamic Characteristics of a Large Flexible Supersonic Cruise Airplane (XB-70-1). 3: A Comparison Between Characteristics Predicted from Wind-tunnel Measurements and Those Measured in Flight
Author:
Publisher:
Total Pages: 64
Release: 1980
Genre:
ISBN:
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Wind-tunnel/flight Correlation Study of Aerodynamic Characteristics of a Large Flexible Supersonic Cruise Airplane CXB-70-1). 1: Wind-tunnel Tests of a 0.03-scale Model at Mach Numbers from 0.6 to 2.53

Wind-tunnel/flight Correlation Study of Aerodynamic Characteristics of a Large Flexible Supersonic Cruise Airplane CXB-70-1). 1: Wind-tunnel Tests of a 0.03-scale Model at Mach Numbers from 0.6 to 2.53
Author:
Publisher:
Total Pages: 232
Release: 1979
Genre:
ISBN:
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Wind-tunnel/flight Correlation Study of Aerodynamic Characteristics of a Large Flexible Supersonic Cruise Airplane (XB-70-1).: A comparison between characteristics predicted from wind-tunnel measurements and those measured in flight

Wind-tunnel/flight Correlation Study of Aerodynamic Characteristics of a Large Flexible Supersonic Cruise Airplane (XB-70-1).: A comparison between characteristics predicted from wind-tunnel measurements and those measured in flight
Author:
Publisher:
Total Pages: 64
Release: 1980
Genre: Aerodynamics, Supersonic
ISBN:
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Analysis of Post-support and Wind-tunnel Wall Interference on Flow Field about Subsonic High-lift High-speed Research Configuration

Analysis of Post-support and Wind-tunnel Wall Interference on Flow Field about Subsonic High-lift High-speed Research Configuration
Author: Wendy B. Lessard
Publisher:
Total Pages: 48
Release: 2000
Genre: Aerodynamics, Supersonic
ISBN:
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The present study was performed to determine how significant the interference effects of the wind-tunnel model support system and tunnel walls can be for a high-speed configuration during takeoff and landing conditions. A 5-percent scale model of the Technology Concept Airplane was recently tested in the Langley 14- by 22-Foot Subsonic Tunnel. The model was numerically modeled with and without the support and tunnel walls and compared with experimental data. Detailed analysis of the flow provided additional insight concerning what effects the postsupport and tunnel walls had on the flow field. This study revealed that although the overall forces and moments could be experimentally accounted for, the detailed flow features, such as the surface pressure distributions, could not be accurately simulated without including the post in the computations.