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Shock Control Bump and Cruise Flap for a NLF Aerofoil

Schojda, Lukas (2014) Shock Control Bump and Cruise Flap for a NLF Aerofoil. DLR-Interner Bericht. DLR-IB 224-2012 A 73. 39 S.

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Within the Smart Fixed Wing Aircraft – ITD of the Clean Sky Project a new transonic laminar aerofoil was investigated numerically respective to a possible drag reduction. These aerofoils show a strong drag rise for Off-Design Mach numbers due to increased wave drag. One possible method to reduce wave drag is the use of a shock control bump. Variations of bump position, bump height and crest positon are presented. Succesful reductions of wave drag are presented under Off-Design conditions. For those regions affected adversely by the bump a cruise flap is applied to control shock position and thus the effectiveness of the shock control bump.

Item URL in elib:https://elib.dlr.de/89150/
Document Type:Monograph (DLR-Interner Bericht)
Title:Shock Control Bump and Cruise Flap for a NLF Aerofoil
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Schojda, Lukaslukas.schojda (at) dlr.deUNSPECIFIED
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Number of Pages:39
Keywords:Shock Control, Laminar Flow, Variable Camber
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Micknaus, Ilka
Deposited On:10 Jun 2014 16:50
Last Modified:10 Jun 2014 16:50

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