Dynamics stability derivatives of space shuttle orbiter obtained from wind-tunnel and approach and landing flight tests

A comparison was made between ground facility measurements, the aerodynamic design data book values, and the dynamic damping derivatives extracted from the space shuttle orbiter approach and landing flight tests. The comparison covers an angle of attack range from 2 deg to 10 deg at subsonic Mach numbers. The parameters of pitch, yaw, and roll damping, as well as the yawing moment due to rolling velocity and rolling moment due to yawing velocity are compared

Comparison of Space Shuttle Orbiter low-speed static stability and control derivatives obtained from wind-tunnel and approach and landing flight tests

Tests were conducted in the 8 foot transonic pressure tunnel to obtain wind tunnel data for comparison with static stability and control parameters measured on the space shuttle orbiter approach and landing flight tests. The longitudinal stability, elevon effectiveness, lateral directional stability, and aileron effectiveness derivatives were determined from the wind tunnel data and compared with the flight test results. The comparison covers a range of angles of attack from approximately 2 deg to 10 deg at subsonic Mach numbers of 0.41 to 0.56. In general the wind tunnel results agreed well with the flight test results, indicating the wind tunnel data is applicable to the design of entry vehicles for subsonic speeds over the angle of attack range studied

Dynamic stability characteristics of the combination space shuttle orbiter and ferry vehicle

Subsonic forced-oscillation tests of a 0.015 scale model of the space shuttle orbiter/747 ferry vehicle were conducted in the Langley high speed 7- by 10-foot tunnel at Mach numbers of 0.2, 0.4, and 0.5 for angles of attack up to 12 deg. Tests were made of the basic 747 airplane, of the modified 747 (tip fins and struts added), of the ferry configuration, (747 plus orbiter at an incidence angle of 3 deg), and of the approach and landing test configuration (747 plus orbiter at an incidence angle of 6 deg)

Applications Technology Satellite /ATS-1/ Suprathermal Ion Detector experiment /SID/ data reduction and analysis Final report, 6 Dec. 1966 - 30 Mar. 1970

Data analysis on ATS-1 Suprathermal Ion Detector /SID/ measurements of low energy plasma flow in magnetopause boundar

Investigation of the relation between solar variations and weather on earth as shown by study of simultaneous data from the sun, Mariner II, near-earth satellites and the atmosphere below the mesosphere

Relation of solar variations and wind to weather on earth shown by data from sun, Mariner II, ATMOSPHERE, and near-earth satellite

Wind tunnel investigation of an unpowered helicopter fuselage model with a V-type empennage

The applicability of a V-type empennage on an unpowered semiscale helicopter fuselage is considered as design criteria for improved directional control devices. Configuration changes included variations of V-tail dihedral angle, planform area, and incidence angle. Of the configurations tested, a V-tail with a dihedral angle of 55 deg, a total planform area of 0.244 sq cm, and an incidence angle of 5 deg most nearly match the trim and static stability of the baseline conventional empennage

Analysis of stability contributions of high dihedral V-tails

An investigation was undertaken to determine the effectiveness of four analytical methods (empirical, modified empirical, vortex-lattice, and an inviscid, three dimensional, potential flow, wing body program) to estimate the lateral and longitudinal static stability characteristics of an isolated V-tail wind tunnel model. The experimental tests were conducted in the V/STOL tunnel at a Mach number of 0.18. Angle-of-attack data were obtained from -12 deg to 8 deg at 0 deg sideslip. Sideslip sweeps from -5 deg to 10 deg were made at angles of attack of 4 deg, 0 deg and -4 deg. The V-tail dihedral angles were 45 deg, 50 deg, 55 deg, and 60 deg

Utilizing Multi-Grounded Theory in a Dissertation: Reflections and Insights

Recently developed and growing in popularity in Europe, Multi-Grounded Theory is seldom used in the United States today. In order to promote the research method, this article traces the academic origins of Multi-Grounded Theory and, via a personal reflection, provides an example of successful employment of this approach. Multi-Grounded Theory is recommended to strong, organized doctoral candidates and other researchers who are able to navigate the combination of qualitative and quantitative data encouraged by this approach

The Hidden Curriculum of Starting an Open-Access Online Journal: An Editor’s Perspective

Starting a new academic journal is a scholarly undertaking that is not taught in graduate school. However, higher education professors may well find it necessary to engage in journal work during their careers. As available literature gives little direction for prospective journal founders and editors, this article provides a Scholarly Personal Narrative (SPN) account of a Senior Editor-in-Chief’s journey through the process of establishing a new academic journal. Challenges inherent to the process are discussed, and recommendations are provided for prospective editors

Quiet Clean Short-haul Experimental Engine (QCSEE) Under-The-Wing (UTW) composite nacelle subsystem test report

The element and subcomponent testing conducted to verify the under the wing composite nacelle design is reported. This composite nacelle consists of an inlet, outer cowl doors, inner cowl doors, and a variable fan nozzle. The element tests provided the mechanical properties used in the nacelle design. The subcomponent tests verified that the critical panel and joint areas of the nacelle had adequate structural integrity