Author: Louis S. StiversPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
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. StiversPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
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: 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. StiversThe Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0
Author: W. F. LindseyPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
Book Description
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Experimental and Analytical Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5
Author: Samuel Ralph PateEffects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate
Author: Don W. JilliePublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6
Author: Mitchel H. BertramPreliminary In-Flight Boundary Layer Transition Measurements on a 45 Deg Swept Wing at Mach Numbers Between 0. 9 And 1. 8
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722499976
Category :
Languages : en
Pages : 48
Book Description
A preliminary flight experiment was flown to generate a full-scale supersonic data base to aid the assessment of computational codes, to improve instrumentation for measuring boundary layer transition at supersonic speeds, and to provide preliminary information for the definition of follow-on programs. The experiment was conducted using an F-15 aircraft modified with a small cleanup test section on the right wing. Results are presented for Mach (M) numbers from 0.9 to 1.8 at altitudes from 25,000 to 55,000 ft. At M greater than or = 1.2, transition occurred near or at the leading edge for the clean configuration. The furthest aft that transition was measured was 20 percent chord at M = 0.9 and M = 0.97. No change in transition location was observed after the addition of a notch-bump on the leading edge of the inboard side of the test section which was intended to minimize attachment line transition problems. Some flow visualization was attempted during the flight experiment with both subliming chemicals and liquid crystals. However, difficulties arose from the limited time the test aircraft was able to hold test conditions and the difficulty of positioning the photo chase aircraft during supersonic test points. Therefore, no supersonic transition results were obtained. Johnson, J. Blair Armstrong Flight Research Center RTOP 533-02-21...
Author: L. N. Cattafesta
Author: K. R. Czarnecki