Author: M. G. HallPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Difficulties in Predicting Boundary-layer Transition on Swept Wings
Author: M. G. HallBoundary Layer Transition Prediction on a Twenty Degree Swept Wing at Transonic Flight Onset Conditions
Author: Patsy Darlene BrownPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 104
Book Description
Comments on Hypersonic Boundary-layer Transition
Author: Kenneth F. StetsonPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 116
Book Description
This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5
Author: S. R. PatePublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 58
Book Description
Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.
Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds
Author: Gary T. ChapmanPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38
Book Description
Experimental and Analytical Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5
Author: Samuel Ralph PateStatus of Linear Boundary-layer Stability Theory and the en Method, with Emphasis on Swept-wing Applications
Author: Jerry N. HefnerPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Book Description
Boundary Layer Transition
Author: D. ArnalPublisher:
ISBN:
Category :
Languages : en
Pages : 59
Book Description
This paper describes the practical calculation methods which are currently available to predict the transition location in two- and three-dimensional flows. Emphasis is given to the problem of skin friction drag reduction on swept wings at subsonic and transonic speeds. The so-called en method, which is deduced from the linear stability theory is widely used in the case of natural transition, but simpler techniques (empirical criteria) are useful in more complex situations such as boundary layer tripping or leading edge contamination. The simulation of flight in wind tunnels is also discussed. Wind tunnel/flight correlation includes comparisons between the free stream disturbance environment, the transition Reynolds number and the n factor at transition onset.
Boundary Layer Transition in the Leading Edge Region of a Swept Cylinder in High Speed Flow
Author: Colin Phillip ColemanPublisher:
ISBN:
Category :
Languages : en
Pages : 212
Book Description
Boundary Layer Effects
Author: Anthony W. FiorePublisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 962
Book Description
In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.