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  • 1
    ISSN: 0002-2667
    Source: Emerald Fulltext Archive Database 1994-2005
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: The use of computer simulation helped to significantly reduce the estimated costs of building the International Space Station's (ISS) X-38 emergency crew return vehicle. Lockheed Martin engineers wanted to determine the actual flow conditions within the X-38 cabin, but ruled out physical testing as they lacked a physical prototype of the X-38 and because such testing could prove very difficult. Computational Fluid Dynamics (CFD) simulation offered an alternative way to evaluate airflow within the vehicle by making it possible to visualize the flow field. Engineers built a computer model of the X-38 and its contents, and used CFD to simulate the airflow and heat transfer throughout the vehicle's cabin, thus eliminating the costs of building and testing a physical prototype.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2011-08-24
    Description: A method for analyzing the mutual aerodynamic interaction between a rotor and an airframe model has been developed. This technique models the rotor implicitly through the source terms of the momentum equations. A three-dimensional, incompressible, laminar, Navier-Stokes solver in cylindrical coordinates was developed for analyzing the rotor/airframe problem. The calculations are performed on a simplified model at an advance ratio of 0.1. The airframe surface pressure predictions are found to be in good agreement with wind tunnel test data. Results are presented for velocity and pressure field distributions in the wake of the rotor.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 489-512.
    Format: text
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  • 3
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted in the Langley 14- by 22-Foot Subsonic Tunnel to quantify the rotor wake behind a scale model helicopter rotor in forward level flight at one thrust level. The rotor system in this test consisted of a four-bladed fully articulated hub with blades of rectangular planform and an NACA 0012 airfoil section. A laser light sheet, seeded with propylene glycol smoke, was used to visualize the vortex geometry in the flow in planes parallel and perpendicular to the free-stream flow. Quantitative measurements of wake geometric proper- ties, such as vortex location, vertical skew angle, and vortex particle void radius, were obtained as well as convective velocities for blade tip vortices. Comparisons were made between experimental data and four computational method predictions of experimental tip vortex locations, vortex vertical skew angles, and wake geometries. The results of these comparisons highlight difficulties of accurate wake geometry predictions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TP-3584 , L-17449 , NAS 1.60:3584 , ATCOM-TR-96-A-007
    Format: application/pdf
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  • 4
    Publication Date: 2019-07-13
    Description: A method for analyzing the mutual aerodynamic interaction between a rotor and an airframe model has been developed. This technique models the rotor implicitly through the source terms of the momentum equations. A three-dimensional, incompressible, laminar, Navier-Stokes solver in cylindrical coordinates was developed for analyzing the rotor-airframe problem. The calculations are performed on a simplified rotor-airframe model at an advance ratio of 0.1. The airframe surface pressure predictions are found to be in good agreement with wind tunnel test data. Results are also presented for velocity and pressure field distributions in the wake of the rotor.
    Keywords: AERODYNAMICS
    Type: American Helicopter Society, Journal (ISSN 0002-8711); 40; 2; p. 57-67
    Format: text
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