Author: Patsy Darlene BrownPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 104
Book Description
Boundary 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
Transition of the Laminar Boundary Layer on a Delta Wing with 74 Degree Sweep in Free Flight at Mach Numbers from 2.8 to 5.3
Author: Gary T. ChapmanPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 46
Book Description
Masters Theses in the Pure and Applied Sciences
Author: Wade H. ShaferPublisher: Springer Science & Business Media
ISBN: 1461559693
Category : Science
Languages : en
Pages : 341
Book Description
Masters Theses in the Pure and Applied Sciences was first conceived, published, and disseminated by the Center for Information and Numerical Data Analysis and Synthesis (CINDAS)* at Purdue University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dis semination phases of the activity were transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this jOint undertaking we had concluded that it was in the interest of all concerned if the printing and distribution of the volumes were handled by an international publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Corporation of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 40 (thesis year 1995) a total of 10,746 thesis titles from 19 Canadian and 144 United States universities. We are sure that this broader base for these titles reported will greatly enhance the value of this impor tant annual reference work. While Volume 40 reports theses submitted in 1995, on occasion, certain uni versities do report theses submitted in previous years but not reported at the time.
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.
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 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.
Effects of Sweep Angle on the Boundary-layer Stability Characteristics of an Untapered Wing at Low Speeds
Author: Frederick W. BoltzPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 86
Book Description
Difficulties in Predicting Boundary-layer Transition on Swept Wings
Author: M. G. HallStatus 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
Analysis of Boundary-layer Transition on X-15-2 Research Airplane
Author: Albert L. BraslowPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 20
Book Description