Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 468
Book Description
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-pressure Data, Volume 2
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: Wind Tunnel and Analytical Investigation of Over-the-wing Propulsion/air Frame Interferences for a Short-haul Aircraft at Mach Numbers from 0.6 to 0.78
Author: Wind Tunnel and Analytical Investigation of Over-the-wing Propulsion/air Frame Interferences for a Short-haul Aircraft at Mach Numbers from 0.6 to 0.78
Author: O. D. WellsPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 252
Book Description
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
A Study of the Simulation of Flow with Free-stream Mach Number 1 in a Choked Wind Tunnel
Author: John R. SpreiterPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Summary: The degree to which experimental results obtained under choking conditions in a wind tunnel with solid walls simulate those associated with an unbounded flow with free-stream Mach number 1 is investigated for the cases of two-dimensional and axisymmetric flows. It is found that a close resemblance does indeed exist in the vicinity of the body, and that the results obtained in this way are generally at least as accurate as those obtained in a transonic wind tunnel with partly open test section. Some of the results indicate, however, that substantial interference effects, particularly those of the wave reflection type, may be encountered under certain conditions, both in choked wind tunnels and in transonic wind tunnels, and that the reduction of these interference effects to acceptable limits may require the use of models of unusually small size.
NASA Technical Memorandum
Author: 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...