Author: Bianca Trujillo Anderson
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 0
Book Description
Effects of Wing Sweep on Boundary-layer Transition for a Smooth F-14A Wing at Mach Numbers from 0.700 to 0.825
Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40
Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5
Author: S. R. Pate
Publisher:
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.
Publisher:
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.
Effects of Sweep and Angle of Attack on Boundary-layer Transition on Wings at Mach Number 4.04
Author: Robert W. Dunning
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 692
Book Description
The data showed that transition always occurred along a front parallel to the wing leading edge, and that increasing the leading-edge sweep angle or increasing the angle of attack between the undisturbed stream and model surface caused the transition line to move closer to the wing leading edge and, in general, decreased the transition Reynolds number.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 692
Book Description
The data showed that transition always occurred along a front parallel to the wing leading edge, and that increasing the leading-edge sweep angle or increasing the angle of attack between the undisturbed stream and model surface caused the transition line to move closer to the wing leading edge and, in general, decreased the transition Reynolds number.
Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40
Author: Louis S. Stivers
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
Effects of Wing Sweep on In-flight Boundary-layer Transition for a Laminar Flow Wing at Mach Numbers from 0.60 to 0.79
Author: Bianca Trujillo Anderson
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 0
Book Description
Effects of Sweep Angle on the Boundary-layer Stability Characteristics of an Untapered Wing at Low Speeds
Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate
Author: Don W. Jillie
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description