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NDARC NASA Design and Analysis of Rotorcraft. Appendix 5; Theory
NTRS Full-Text: Click to View  [PDF Size: 1.7 MB]
Author and Affiliation:
Johnson, Wayne(NASA Ames Research Center, Moffett Field, CA, United States)
Abstract: The NASA Design and Analysis of Rotorcraft (NDARC) software is an aircraft system analysis tool that supports both conceptual design efforts and technology impact assessments. The principal tasks are to design (or size) a rotorcraft to meet specified requirements, including vertical takeoff and landing (VTOL) operation, and then analyze the performance of the aircraft for a set of conditions. For broad and lasting utility, it is important that the code have the capability to model general rotorcraft configurations, and estimate the performance and weights of advanced rotor concepts. The architecture of the NDARC code accommodates configuration flexibility, a hierarchy of models, and ultimately multidisciplinary design, analysis, and optimization. Initially the software is implemented with low-fidelity models, typically appropriate for the conceptual design environment. An NDARC job consists of one or more cases, each case optionally performing design and analysis tasks. The design task involves sizing the rotorcraft to satisfy specified design conditions and missions. The analysis tasks can include off-design mission performance calculation, flight performance calculation for point operating conditions, and generation of subsystem or component performance maps. For analysis tasks, the aircraft description can come from the sizing task, from a previous case or a previous NDARC job, or be independently generated (typically the description of an existing aircraft). The aircraft consists of a set of components, including fuselage, rotors, wings, tails, and propulsion. For each component, attributes such as performance, drag, and weight can be calculated; and the aircraft attributes are obtained from the sum of the component attributes. Description and analysis of conventional rotorcraft configurations is facilitated, while retaining the capability to model novel and advanced concepts. Specific rotorcraft configurations considered are single-main-rotor and tail-rotor helicopter, tandem helicopter, coaxial helicopter, and tiltrotor. The architecture of the code accommodates addition of new or higher-fidelity attribute models for a component, as well as addition of new components.
Publication Date: Aug 01, 2017
Document ID:
20170011656
(Acquired Dec 19, 2017)
Subject Category: AIRCRAFT DESIGN, TESTING AND PERFORMANCE; COMPUTER PROGRAMMING AND SOFTWARE
Report/Patent Number: NASA/TP-2015-218751, ARC-E-DAA-TN46522
Document Type: Technical Report
Publication Information: SEE 20150021267
Financial Sponsor: NASA Ames Research Center; Moffett Field, CA, United States
Organization Source: NASA Ames Research Center; Moffett Field, CA, United States
Description: 298p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright; Work of the U.S. Government - Public use permitted
NASA Terms: DESIGN ANALYSIS; ROTARY WING AIRCRAFT; COMPUTER PROGRAMS; SYSTEMS ANALYSIS; AIRCRAFT CONFIGURATIONS; MATHEMATICAL MODELS; VERTICAL TAKEOFF AIRCRAFT; VERTICAL LANDING; AIRCRAFT PERFORMANCE; FUSELAGES; TECHNOLOGY ASSESSMENT; FLIGHT CONDITIONS; AIRCRAFT CONTROL; LOADS (FORCES); MULTIDISCIPLINARY DESIGN OPTIMIZATION
Other Descriptors: DESIGN AND ANALYSIS; APPENDIX; THEORY; NDAR
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