Author: Gary T. Chapman
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 46
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. Chapman
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 46
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. CHAPMAN
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
The test were conducted at Mach numbers from 2.8 to 5.3, with model surface temperatures small compared to boundary-layer recovery temperature. The effects of Mach number, unit Reynolds number, leading-edge diameter, temperature ratio, AND ANGLE OF ATTACK WERE INVESTIGATED IN AN EXPLORATORY FASHION. The results were compared to results of wind-tunnel tests of swept wings and to results f free-flight tests for unswept leading edges. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
The test were conducted at Mach numbers from 2.8 to 5.3, with model surface temperatures small compared to boundary-layer recovery temperature. The effects of Mach number, unit Reynolds number, leading-edge diameter, temperature ratio, AND ANGLE OF ATTACK WERE INVESTIGATED IN AN EXPLORATORY FASHION. The results were compared to results of wind-tunnel tests of swept wings and to results f free-flight tests for unswept leading edges. (Author).
Transition of the Laminar Boundary Layer on a Delta Wing with 74° Sweep in Free Flight at Mach Numbers from 2.8 to 5.3
Scientific and Technical Aerospace Reports
Technical Publications Announcements
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
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.
Analysis of Boundary-layer Transition on X-15-2 Research Airplane
Author: Albert L. Braslow
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 20
Book Description
A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0
Author: Robert S. Osborne
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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
Summary of Laminar Flow Control Techniques for Aircraft
Author: Philip P. Antonatos
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 44
Book Description