Experimental Investigations of the NASA Common Research Model (Invited)

Rivers, Melissa B.; Dittberner, Ashley

doi:10.2514/6.2010-4218

Cited by 77 publications

(29 citation statements)

References 3 publications

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“…The experimental data 10,11 was reported at a non-uniform set of incidences up to a maximum of 10 . To enable the effect of the nacelle installation to be quantified, and to facilitate the comparison between the experimental and computational data sets, it was necessary to perform comparisons at constant lift so as to exclude the effect of lift induced drag.…”

Section: Drag Extraction Methodsmentioning

confidence: 99%

“…It was decided to base the work on the NASA Common Research Model (CRM), 9 which is a civil transport configuration which is comparable with a typical twin-engined wide-body 250-300 seater airframe. The aerodynamics for the CRM with through-flow nacelles (TFN) has been experimentally investigated 10,11,14,15 using a 1/37th sub-scale model at a Reynolds number of 5 Â 10 6 . The CRM has a representative modern wing design with a design point 9 at M 1 ¼ 0:85 and C L ¼ 0.5.…”

Section: Test Case Configurationsmentioning

confidence: 99%

“…8 The success of the initial workshop triggered the design of the more modern aircraft geometry of the NASA Common Research Model. 9 The publication of substantial experimental datasets with and without through-flow nacelles (TFNs) 10,11 makes the Common Research Model a benchmark validation activity for the assessment of installation effect.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamics of aero-engine installation

Stańkowski

MacManus

Sheaf

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper describes current progress in the development of methods to assess aero-engine airframe installation effects. The aerodynamic characteristics of isolated intakes, a typical transonic transport aircraft as well as a combination of a through-flow nacelle and aircraft configuration have been evaluated. The validation task for an isolated engine nacelle is carried out with concern for the accuracy in the assessment of intake performance descriptors such as mass flow capture ratio and drag rise Mach number. The necessary mesh and modelling requirements to simulate the nacelle aerodynamics are determined. Furthermore, the validation of the numerical model for the aircraft is performed as an extension of work that has been carried out under previous drag prediction research programmes. The validation of the aircraft model has been extended to include the geometry with through flow nacelles. Finally, the assessment of the mutual impact of the through flow nacelle and aircraft aerodynamics was performed. The drag and lift coefficient breakdown has been presented in order to identify the component sources of the drag associated with the engine installation. The paper concludes with an assessment of installation drag for through-flow nacelles and the determination of aerodynamic interference between the nacelle and the aircraft. KeywordsEngine-airframe integration, through-flow nacelle, aerodynamic interference, computational fluid dynamics, NASA Common Research Model

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Section: Drag Extraction Methodsmentioning

confidence: 99%

Section: Test Case Configurationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamics of aero-engine installation

Stańkowski

MacManus

Sheaf

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…A body of literature for the CRM is available in the public domain including the model geometry, 2 computational results, 3,4,5,6,7 and experimental data. 8,9 Figure 1 shows the full configuration of the CRM including the wing, body, horizontal tail, and nacelle-pylon group.…”

mentioning

confidence: 99%

Large-Scale Swept-Wing Icing Simulations in the NASA Glenn Icing Research Tunnel Using LEWICE3D

Wiberg

Fujiwara

Woodard

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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Computational icing simulations of a hybrid, swept-wing model in the NASA IRT are presented. The results of these simulations are compared to those for the same icing conditions conducted on the full-scale reference wing. The effects of tunnel sidewalls, attachment line position, and altitude are considered. A discussion of icing scaling and the results of one scaling approach are given. The variation of impingement and ice shape with span in the tunnel for different angles of attack and flap deflection are presented.

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“…Experimental data were collected in the NASA Langley National Transonic Facility in JanuaryFebruary 2010 and in the NASA Ames 11-ft wind tunnel during March-April 2010. [16][17] A summary of the results from DPW-IV is provided in Ref. 7.…”

mentioning

confidence: 99%

Statistical Analysis of CFD Solutions from the Fifth AIAA Drag Prediction Workshop

Morrison

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Experimental Investigations of the NASA Common Research Model (Invited)

Cited by 77 publications

References 3 publications

Aerodynamics of aero-engine installation

Aerodynamics of aero-engine installation

Large-Scale Swept-Wing Icing Simulations in the NASA Glenn Icing Research Tunnel Using LEWICE3D

Statistical Analysis of CFD Solutions from the Fifth AIAA Drag Prediction Workshop

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