Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 436
Book Description
Wind Tunnel Investigation of Nacelle-Airframe Interference at Mach Numbers of 0.9 to 1.4-pressure Data, Volume 2
Author: Wind Tunnel Investigation of Nacelle-airframe Interference at Mach Numbers of 0.9 to 1.4 - Pressure Data, Volume 1
Author: Wind Tunnel Investigation of Nacelle-Airframe Interference at Mach Numbers of 0.9 to 1.4-force Data
Author: Scientific and Technical Aerospace Reports
Author: Experimental Evaluation of Nacelle-airframe Interference Forces and Pressures at Mach Numbers of 0.9 to 1.4
Author: Daniel P. BenczePublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 188
Book Description
NASA Technical Memorandum
Author: Applied Mechanics Reviews
Author: Aerodynamics of Power Plant Installation
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and DevelopmentPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 542
Book Description
An Investigation of Three-dimensional Wall Interference in a Variable Porosity Transonice Wind Tunnel
Author: Travis W. Binion (Jr.)Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 88
Book Description
Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from 0. 7 To 1. 4
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722942373
Category :
Languages : en
Pages : 38
Book Description
Flush pressure orifices installed on the nose section of a 1/7-scale model of the F-14 airplane were evaluated for use as a flush airdata system (FADS). Wing-tunnel tests were conducted in the 11- by 11-ft Unitary Wind Tunnel at NASA Ames Research Center. A full-scale FADS of the same configuration was previously tested using an F-14 aircraft at the Dryden Flight Research Facility of NASA Ames Research Center (Ames-Dryden). These tests, which were published, are part of a NASA program to assess accuracies of FADS for use on aircraft. The test program also provides data to validate algorithms for the shuttle entry airdata system developed at the NASA Langley Research Center. The wind-tunnel test Mach numbers were 0.73, 0.90, 1.05, 1.20, and 1.39. Angles of attack were varied in 2 deg increments from -4 deg to 20 deg. Sideslip angles were varied in 4 deg increments from -8 deg to 8 deg. Airdata parameters were evaluated for determination of free-stream values of stagnation pressure, static pressure, angle of attack, angle of sideslip, and Mach number. These parameters are, in most cases, the same as the parameters investigated in the flight test program. The basic FADS wind-tunnel data are presented in tabular form. A discussion of the more accurate parameters is included. Larson, Terry J. and Moes, Timothy R. and Siemers, Paul M., III Ames Research Center; Armstrong Flight Research Center; Langley Research Center RTOP 505-60-21...