Wake Vortex Advisory System (WakeVAS) Concept of Operations
Author:
Publisher: DIANE Publishing
Published: 2003
Total Pages: 27
ISBN-13: 1428995315
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Author:
Publisher: DIANE Publishing
Published: 2003
Total Pages: 27
ISBN-13: 1428995315
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-06-12
Total Pages: 28
ISBN-13: 9781721038695
DOWNLOAD EBOOKNASA Langley Research Center has a long history of aircraft wake vortex research, with the most recent accomplishment of demonstrating the Aircraft VOrtex Spacing System (AVOSS) at Dallas/Forth Worth International Airport in July 2000. The AVOSS was a concept for an integration of technologies applied to providing dynamic wake-safe reduced spacing for single runway arrivals, as compared to current separation standards applied during instrument approaches. AVOSS included state-of-the-art weather sensors, wake sensors, and a wake behavior prediction algorithm. Using real-time data AVOSS averaged a 6% potential throughput increase over current standards. This report describes a Concept of Operations for applying the technologies demonstrated in the AVOSS to a variety of terminal operations to mitigate wake vortex capacity constraints. A discussion of the technological issues and open research questions that must be addressed to design a Wake Vortex Advisory System (WakeVAS) is included.Rutishauser, David and Lohr, Gary and Hamilton, David and Powers, Robert and McKissick, Burnell and Adams, Catherine and Norris, EdwardLangley Research CenterAIRCRAFT WAKES; VORTEX ADVISORY SYSTEM; VORTICES; NASA PROGRAMS; AIRCRAFT APPROACH SPACING; AIR TRAFFIC CONTROL; ARRIVALS
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-05-29
Total Pages: 56
ISBN-13: 9781720384601
DOWNLOAD EBOOKThe FAA and NASA are currently engaged in a Wake Turbulence Research Program to revise wake turbulence separation standards, procedures, and criteria to increase airport capacity while maintaining or increasing safety. The research program is divided into three phases: Phase I near term procedural enhancements; Phase II wind dependent Wake Vortex Advisory System (WakeVAS) Concepts of Operations (ConOps); and Phase III farther term ConOps based on wake prediction and sensing. This report contains an analysis that evaluates the benefits of a closely spaced parallel runway (CSPR) Phase I ConOps, a single runway and CSPR Phase II ConOps and a single runway Phase III ConOps. A series of simulation runs were performed using the Airspace Concepts Evaluation System (ACES) Build 3.21 air traffic simulator to provide an initial assessment of the reduction in delay and cost savings obtained by the use of a WakeVAS at selected U.S. airports. The ACES simulator is being developed by NASA Ames Research Center as part of the Virtual Airspace Modelling and Simulation (VAMS) program.Smith, Jeremy C.Langley Research CenterAIRSPACE; COST REDUCTION; VORTEX ADVISORY SYSTEM; WAKES; VORTEX ALLEVIATION; AIR TRAFFIC; AIRPORTS; AUGMENTATION; RUNWAYS; SAFETY; TURBULENCE
Author:
Publisher:
Published: 1979
Total Pages: 236
ISBN-13:
DOWNLOAD EBOOKAuthor: George C. Ashby
Publisher:
Published: 1965
Total Pages: 82
ISBN-13:
DOWNLOAD EBOOKAuthor: Robert J. Pegg
Publisher:
Published: 1962
Total Pages: 48
ISBN-13:
DOWNLOAD EBOOKAuthor: Herman L. Bohon
Publisher:
Published: 1963
Total Pages: 48
ISBN-13:
DOWNLOAD EBOOKAuthor: George E. Weeks
Publisher:
Published: 1967
Total Pages: 28
ISBN-13:
DOWNLOAD EBOOKAuthor: James M. Cubbage
Publisher:
Published: 1971
Total Pages: 76
ISBN-13:
DOWNLOAD EBOOKResults from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.
Author: Manuel Stein
Publisher:
Published: 1961
Total Pages: 36
ISBN-13:
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