TY  - CHAP
A1  - Mertens, Josef
ED  - Sobieczky, H.
T1  - Aerodynamic multi point design challenge
T2  - New design concepts for high speed air transport.- (Courses and lectures / International Centre for Mechanical Sciences ; 366)
N2  - In the chapter “Son of Concorde, a Technology Challenge” one of the new challenges for a Supersonic Commercial Transport (SCT) is multi-point design for the four main design points:

- supersonic cruise
- transonic cruise
- take-off and landing
- transonic acceleration.
KW  - Drag Reduction
KW  - Pitching Moment
KW  - Leading Edge Vortex
KW  - Wave Drag
KW  - Variable Geometry
Y1  - 1997
SN  - 3-2118-2815-X
U6  - http://dx.doi.org/10.1007/978-3-7091-2658-5_4
SP  - 53
EP  - 67
PB  - Springer
CY  - Wien [u.a.]
ER  - 
TY  - JOUR
A1  - Gerhardt, Hans Joachim
A1  - Konrath, B.
A1  - Kramer, C.
A1  - Oliveira, L.-A.
T1  - Aerodynamische Abdichtung von Anlagen für die Bandbearbeitung
JF  - Blech, Rohre, Profile. 39 (1992), H. 1
Y1  - 1992
SN  - 0006-4688
SP  - 39
EP  - 1
ER  - 
TY  - RPRT
A1  - Bohn, Dieter
A1  - Funke, Harald
A1  - Wolff, M.
A1  - Sürken, N.
T1  - Aerodynamische Entlastung der Schaufelspalte durch Konturierung des Meridiankanals [Abschlussbericht]
N2  - Abschlussbericht über das Vorhaben Nr. 688 (FVV-Nr. 066880). Laufzeit 01.04.2000 bis 31.03.2001. Heft R 516 (2002). 24 S. Informationstagung Turbinen, Frühjahr 2002, Frankfurt-Möhrfelden
KW  - Strömungsmaschine
KW  - Turbine
KW  - Spaltentlastung
KW  - Turbine
Y1  - 2002
ER  - 
TY  - RPRT
A1  - Bohn, Dieter
A1  - Funke, Harald
A1  - Sürken, N.
T1  - Aerodynamische Entlastung der Schaufelspalte durch Konturierung des Meridiankanals [Zwischenbericht]
N2  - Zwischenbericht über das Vorhaben FVV-Nr. 0666880. Laufzeit 01.03.1998 bis 31.03.2000. Heft R 507 (2000) . 19 S. Informationstagung Turbinen, Frühjahr 2000, Frankfurt am Main
KW  - Strömungsmaschine
KW  - Turbine
KW  - Spaltentlastung
KW  - Turbine
Y1  - 2000
ER  - 
TY  - RPRT
A1  - Bohn, Dieter
A1  - Funke, Harald
A1  - M., Wolff.
A1  - Sürken, N.
T1  - Aerodynamische Entlastung der Schaufelspalte durch Konturierung des Meridiankanals [Zwischenbericht]
N2  - Zwischenbericht über das Vorhaben Nr. 688 (FVV-Nr. 066880). Laufzeit 01.04.2000 bis 31.03.2001. Heft R 514 (2001). 21 S. Informationstagung Turbinen, Herbst 2001, Dresden-Radebeul
KW  - Strömungsmaschine
KW  - Turbine
KW  - Spaltentlasung
KW  - Turbine
Y1  - 2001
ER  - 
TY  - RPRT
A1  - Reimer, Lars
A1  - Wellmer, Georg
A1  - Braun, Carsten
A1  - Ballmann, Josef
T1  - Aerodynamische Simulation und Optimierung in der Flugzeugentwicklung. Teilvorhabenbezeichnung: Aerodynamische Optimierung unter Berücksichtigung von Struktureigenschaften auf der Basis reduzierter Strukturmodelle, Verbundvorhaben MEGADESIGN. Schlussbericht. Berichtszeitraum: 01.06.2003-31.05.2007. BMBF-Forschungsbericht
Y1  - 2007
ER  - 
TY  - JOUR
A1  - Mertens, Josef
T1  - Aerodynamische Ziele des Adaptiven Flügels (ADIF).
JF  - DGLR-Jahrbuch 1998 Bd. 1
Y1  - 1998
N1  - DGLR-JT98-213
SP  - 47
EP  - 52
ER  - 
TY  - JOUR
A1  - Gerhardt, Hans Joachim
A1  - Kramer, C.
T1  - Aerodynamsiche RA-Optimierung
JF  - Zentralblatt fuer Industriebau. 31 (1985), H. 5
Y1  - 1985
SN  - 0044-4227
SP  - 358
EP  - 362
ER  - 
TY  - CHAP
A1  - Ballmann, Josef
A1  - Boucke, Alexander
A1  - Braun, Carsten
T1  - Aeroelastic sensitivity in the transonic regime
T2  - Symposium Transsonicum IV : proceedings of the IUTAM symposium held in Göttingen, Germany, 2 - 6 September 2002 / ed. by Helmut Sobieczky. Fluid mechanics and its applications.  Vol. 73
Y1  - 2003
SN  - 978-94-010-3998-7
SP  - 225
EP  - 236
PB  - Kluwer Academic
CY  - Dordrecht
ER  - 
TY  - JOUR
A1  - Götten, Falk
A1  - Havermann, Marc
A1  - Braun, Carsten
A1  - Marino, Matthew
A1  - Bil, Cees
T1  - Airfoil drag at low-to-medium reynolds numbers: A novel estimation method
JF  - AIAA Journal
N2  - This paper presents a novel method for airfoil drag estimation at Reynolds numbers between 4×10⁵ and 4×10⁶. The novel method is based on a systematic study of 40 airfoils applying over 600 numerical simulations and considering natural transition. The influence of the airfoil thickness-to-chord ratio, camber, and freestream Reynolds number on both friction and pressure drag is analyzed in detail. Natural transition significantly affects drag characteristics and leads to distinct drag minima for different Reynolds numbers and thickness-to-chord ratios. The results of the systematic study are used to develop empirical correlations that can accurately predict an airfoil drag at low-lift conditions. The new approach estimates a transition location based on airfoil thickness-to-chord ratio, camber, and Reynolds number. It uses the transition location in a mixed laminar–turbulent skin-friction calculation, and corrects the skin-friction coefficient for separation effects. Pressure drag is estimated separately based on correlations of thickness-to-chord ratio, camber, and Reynolds number. The novel method shows excellent accuracy when compared with wind-tunnel measurements of multiple airfoils. It is easily integrable into existing aircraft design environments and is highly beneficial in the conceptual design stage.
Y1  - 2020
U6  - http://dx.doi.org/10.2514/1.J058983
SN  - 1533-385X
VL  - 58
IS  - 7
SP  - 2791
EP  - 2805
PB  - AIAA
CY  - Reston, Va.
ER  -