Investigations of propulsion integration interference effects on a transport aircraft configuration

Rossow, Cord-Christian; Godard, Jean-Luc; Hoheisel, H.; Schmitt, V.

doi:10.2514/3.46605

Cited by 56 publications

(24 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The second drag prediction workshop (DPW-II) 5,6 , held in June of 2003, added the challenge of determining the increment of a large component, in this case a pylon/nacelle. The DLR-F6 configuration 5,7 was used for this study. Once again, experimental data were available for comparison.…”

Section: Introductionmentioning

confidence: 99%

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Rivers

Hunter

Campbell

2012

30th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

An experimental investigation of the NASA Common Research Model was conducted in the NASA Langley National Transonic Facility and NASA Ames 11-foot Transonic Wind Tunnel Facility for use in the Drag Prediction Workshop. As data from the experimental investigations was collected, a large difference in moment values was seen between the experiment and computational data from the 4 th Drag Prediction Workshop. This difference led to a computational assessment to investigate model support system interference effects on the Common Research Model. The results from this investigation showed that the addition of the support system to the computational cases did increase the pitching moment so that it more closely matched the experimental results, but there was still a large discrepancy in pitching moment. This large discrepancy led to an investigation into the shape of the as-built model, which in turn led to a change in the computational grids and re-running of all the previous support system cases. The results of these cases are the focus of this paper. Nomenclature b= wing span, in. c = wing mean aerodynamic chord, in. = CRM wing/body/tail=0° configuration WBT0ss = CRM wing/body/tail=0° with support system configuration WBT0ssa = CRM wing/body/tail=0° with support system and arc sector configuration x/c = longitudinal distance from wing leading edge nondimensionalized by local wing chord α = angle-of-attack, degrees δ = change in per unit area values η = fraction of wing semi-span φ = radial station, degrees Δ = change in total values

show abstract

Section: Introductionmentioning

confidence: 99%

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Rivers

Hunter

Campbell

2012

30th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

show abstract

“…The second drag prediction workshop 5,6 (DPW-II), held in June of 2003, added the challenge of determining the increment due to adding a large component, in this case a pylon/nacelle. The DLR-F6 configuration 5,7 was used for this study. Once again, experimental data were available for comparison.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited)

Rivers

Dittberner

Sverdrup³

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

117

View full text Add to dashboard Cite

Experimental aerodynamic investigations of the NASA Common ResearchModel have been conducted in the NASA Langley National Transonic Facility and the NASA Ames 11-ft wind tunnel. Data have been obtained at chord Reynolds numbers of 5 million for five different configurations at both wind tunnels. Force and moment, surface pressure and surface flow visualization data were obtained in both facilities but only the force and moment data are presented herein. Nacelle/pylon, tail effects and tunnel to tunnel variations have been assessed. The data from both wind tunnels show that an addition of a nacelle/pylon gave an increase in drag, decrease in lift and a less nose down pitching moment around the design lift condition of 0.5 and that the tail effects also follow the expected trends. Also, all of the data shown fall within the 2-sigma limits for repeatability. The tunnel to tunnel differences are negligible for lift and pitching moment, while the drag shows a difference of less than ten counts for all of the configurations. These differences in drag may be due to the variation in the sting mounting systems at the two tunnels.

show abstract

“…Aerodynamic optimization of the engine location is considered to be one of the key factors that influence the overall flight performance. Consequently, the understanding of flow interactions for aerodynamic optimization has been the subject of a large number of experimental (Godard et al, 1991, 1996, Rossow et al, 1994 and numerical studies (Chaput et al , 1996, Rudnik et al , 1996. To reduce development cost and to obtain detailed data, feasibility tests in an existing small wind tunnel were carried out.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of sonic jet flows for wing/nacelle integration

Kwon

Leblanc

Garem

2001

KSME International Journal

View full text Add to dashboard Cite

An experimental study of compressible jet flows has been undertaken in a small transonic wind tunnel. The aim of this investigation was to realize a jet simulator in the framework of wing/nacelle integration research and to characterize the jet flow behavior. First, free jet configuration, and subsequently jet flow in co-flowing air stream configuration were analyzed. Flow conditions were those encountered in a typical flight condition of a generic transport aircraft. i.e, fully expanded sonic jet flows interacting with a compressible external flowfield. Conventional experimental techniques were used to investigate the jet flows-Schlieren visualization and two-component Laser Doppler Velocimetry (LDV). The mean and fluctuating properties were measured along the jet centerline and in the symmetric plane at various downstream locations. The results of two configurations show remarkable differences in the mean and fluctuating components and agree well with the trend observed by other investigators. Moreover, these experiments enrich the database for such flow conditions and verify the feasibility of its application in future aerodynamic research of wing/nacelle interactions.

show abstract

Investigations of propulsion integration interference effects on a transport aircraft configuration

Cited by 56 publications

References 1 publication

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited)

Experimental investigation of sonic jet flows for wing/nacelle integration

Contact Info

Product

Resources

About