Experimental Investigations of the NASA Common Research Model

Rivers, Melissa B.; Dittberner, Ashley

doi:10.2514/1.c032626

Cited by 81 publications

(47 citation statements)

References 22 publications

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“…The CRM was designed by Boeing as part of collaboration with NASA to represent a typical modern wide-body commercial transport, whose geometry, 22 computational 23,24,25,26,27,28 and experimental data 29,30 are publicly available. The CRM was designed for a cruise Mach number of 0.85 at a Reynolds number of 40 million.…”

Section: Reference Wingmentioning

confidence: 99%

3D Swept Hybrid Wing Design Method for Icing Wind Tunnel Tests

Fujiwara

Wiberg

Woodard

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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A 3D swept hybrid wing design method using hybrid airfoils is presented for the purpose of icing wind tunnel testing of large commercial aircraft. Hybrid airfoils are those that present the same leading-edge geometry of the full-scale aircraft wing with a redesigned truncated aft section, such that models can fit inside icing wind tunnels and still reproduce full-scale flowfield and ice accretion with reduced chord. The effects of tunnel sidewalls, model sweep angle, aspect ratio, and wind tunnel blockage are presented. Attachment line location is used as a first-order parameter for matching full-scale ice shapes, and methods for controlling its spanwise variation are assessed including the use of gap between model and tunnel wall, aerodynamic twist, and segmented flaps. Finally, model design tradeoffs are presented between competing performance parameters such as full-scale ice accretion agreement, wind tunnel load/speed limits, and model manufacturing/operational complexity. NomenclatureAR = Aspect ratio α = Airfoil angle of attack c fs = Full-scale chord c hyb = Hybrid airfoil chord C p = Pressure coefficient C l = Lift coefficient C m0 = Quarter-chord zero-angle of attack pitching moment coefficient CRM = Common research model CRM65 = 65% scaled common research model δ = Flap deflection, positive down h/c = Tunnel height over model chord η = Wing spanwise position LE = Leading edge RANS = Reynolds-averaged Navier-Stokes equations SF = Scale factor (full-scale chord divided by hybrid chord) s/c = Normalized surface length coordinate

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Section: Reference Wingmentioning

confidence: 99%

3D Swept Hybrid Wing Design Method for Icing Wind Tunnel Tests

Fujiwara

Wiberg

Woodard

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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“…The National Transonic Facility (NTF) at NASA Langley tested the CRM during Jan-Feb 2010, and then it was evaluated at the Ames 11-ft wind-tunnel during Mar-Apr 2010. Data from the NTF and Ames tests have been released to the public domain by Rivers and Dittberner [40][41][42] . Due to past observations of grid dependence on the solutions, a greater emphasis was placed on establishing meshing guidelines for the generation of baseline grid families.…”

Section: Introductionmentioning

confidence: 99%

Summary of Data from the Fifth AIAA CFD Drag Prediction Workshop

Levy¹,

Laflin²,

Tinoco

et al. 2013

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

104

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Results from the Fifth AIAA CFD Drag Prediction Workshop (DPW-V) are presented. As with past workshops, numerical calculations are performed using industry-relevant geometry, methodology, and test cases. This workshop focused on force/moment predictions for the NASA Common Research Model wing-body configuration, including a grid refinement study and an optional buffet study. The grid refinement study used a common grid sequence derived from a multiblock topology structured grid. Six levels of refinement were created resulting in grids ranging from 0.64x10 6 to 138x10 6 hexahedra -a much larger range than is typically seen. The grids were then transformed into structured overset and hexahedral, prismatic, tetrahedral, and hybrid unstructured formats all using the same basic cloud of points. This unique collection of grids was designed to isolate the effects of grid type and solution algorithm by using identical point distributions. This study showed reduced scatter and standard deviation from previous workshops. The second test case studied buffet onset at M=0.85 using the Medium grid (5.1x10 6 nodes) from the above described sequence. The prescribed alpha sweep used finely spaced intervals through the zone where wing separation was expected to begin. Some solutions exhibited a large side of body separation bubble that was not observed in the wind tunnel results. An optional third case used three sets of geometry, grids, and conditions from the Turbulence Model Resource website prepared by the Turbulence Model Benchmarking Working Group. These simple cases were intended to help identify potential differences in turbulence model implementation. Although a few outliers and issues affecting consistency were identified, the majority of participants produced consistent results.

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“…The aspect ratio is 9.0, the leading edge sweep angle is 35 deg. The original wind tunnel model used in the NTF test 13 was also used in the ETW test, while another copy fabricated by JAXA was used in the JTWT test. The wing reference area is 0.279 m 2 , the wing span is 1.587 m, and the mean aerodynamic chord is 0.189 m, for the original model.…”

Section: B Model Descriptionmentioning

confidence: 99%

CFD-Aided Model Deformation Corrections of NASA Research Model Wind Tunnel data

Yasue

Ueno

Koga

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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CFD-aided wind tunnel data corrections for static model deformation effect of NASA-Common Research Model (CRM) are performed for wind tunnel data obtained at the 2m×2m Transonic Wind Tunnel of JAXA (JTWT), the National Transonic Facility (NTF) and the European Transonic Wind tunnel (ETW). In this paper, the model deformation effects are estimated by difference between CFD results for a designed configuration and that for a deformed configuration. At first, the applied techniques for the model deformation correction are validated using two sets of wind tunnel data of the NTF at the Reynolds number of 20 million with different dynamic pressures. Then, the model deformation corrections are applied to the wind tunnel data obtained at the JTWT, the NTF and the ETW. It is shown that differences of the drag coefficients among the JTWT, the NTF and the ETW fall within about 10 drag counts by the model deformation corrections and the Reynolds number corrections for the JTWT data to align the Reynolds number at 5 million. Nomenclatureof attack Span-wise section location normalized by the half span length Sweep angle of the maximum thickness line Maximum gross sectional area of the body Span length Chord length Drag coefficient Skin friction coefficient Lift coefficient Section lift coefficient Pitching moment coefficient Pressure Coefficient Reference diameter of the body 4 !"# Wing twist caused by the model deformation Wing bending caused by the model deformationfactor Length of the body Mach number Total pressure Component interference factor Reynolds number Reference area Cross-section area of the wind tunnel test section Wetted area Thickness of the wing Total temperature X-component coordinate of body axis Chord-wise location Chord-wise location of the airfoil maximum thickness point Y-component coordinate of body axis Normalized wall distance Z-component coordinate of body axis 1 Researcher, Institute of Aeronautical Technology, yasue.kanako@jaxa.jp, Member AIAA. 2 Associate senior researcher, Institute of Aeronautical Technology, ueno.makoto@jaxa.jp, Senior Member AIAA. 3 Engineer, Institute of Aeronautical Technology, koga.seigo@jaxa.jp. 4 Researcher, Institute of Aeronautical Technology, kohzai.masataka@jaxa.jp. Downloaded by PURDUE UNIVERSITY on July 17, 2015 | http://arc.aiaa.org |

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Experimental Investigations of the NASA Common Research Model

Cited by 81 publications

References 22 publications

3D Swept Hybrid Wing Design Method for Icing Wind Tunnel Tests

3D Swept Hybrid Wing Design Method for Icing Wind Tunnel Tests

Summary of Data from the Fifth AIAA CFD Drag Prediction Workshop

CFD-Aided Model Deformation Corrections of NASA Research Model Wind Tunnel data

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