TY  - JOUR
A1  - Havermann, Marc
A1  - Haertig, J.
A1  - Rey, C.
A1  - George, F.
T1  - PIV measurements in Mach 3.5 and 4.5 shock tunnel flow / Haertig, J. ; Havermann, M. ; Rey, C. ; George, F.
Y1  - 2001
N1  - AIAA-2001-699 
Aerospace Sciences Meeting and Exhibit, 39th, Reno, NV, Jan. 8-11, 2001
PB  - -
ER  - 
TY  - JOUR
A1  - Havermann, Marc
A1  - Haertig, J.
A1  - Rey, C.
A1  - George, A.
T1  - Particle image velocimetry in mach 3.5 and 4.5 shock-tunnel flows / Haertig, J. ; Havermann, M. ; Rey, C. ; George, A.
JF  - AIAA journal. 40 (2002), H. 6
Y1  - 2002
SN  - 0001-1452
N1  - Printausgabe in der Bereichsbibliothek Eupener Str. Signatur: 23 Z 701
SP  - 1056
EP  - 1060
PB  - -
ER  - 
TY  - JOUR
A1  - Havermann, Marc
A1  - Haertig, J.
A1  - Rey, C.
A1  - George, A.
T1  - PIV Measurements in Shock Tunnels and Shock Tubes / Havermann, M. ; Haertig, J. ; Rey, C. ; George, A.
JF  - Particle Image Velocimetry : New Developments and Recent Applications
Y1  - 2008
SN  - 978-3-540-73528-1
N1  - Topics in applied physics. Vol 112.
SP  - 429
EP  - 442
PB  - Springer
CY  - Berlin
ER  - 
TY  - JOUR
A1  - Havermann, Marc
A1  - Ende, H.
A1  - Seiler, F.
A1  - Schwenzer, M.
T1  - Shock tunnel measurement of the interaction amplification factor for a hot gas side jet in a supersonic cross flow / Havermann, M. ; Ende, H. ; Seiler, F. ; Schwenzer, M.
JF  - Shock Waves : Proceedings of the 24th International Symposium on Shock Waves Beijing, China July 11-16, 2004 / edited by Z. Jiang
Y1  - 2005
SN  - 978-3-540-22497-6
SP  - 113
EP  - 118
PB  - Springer
CY  - Berlin
ER  - 
TY  - JOUR
A1  - Havermann, Marc
A1  - Beylich, A. E.
T1  - Performance and Limitations of the Laser-Induced Fluorescence Measurement Technique and the Established Experimental Methods for the Study of Supersonic Mixing / Havermann, M. ; Beylich, A. E.
JF  - International Journal of heat and technology. 15 (1997), H. 2
Y1  - 1997
SP  - 3
EP  - 10
PB  - -
ER  - 
TY  - JOUR
A1  - Havermann, Marc
A1  - Beylich, A. E.
T1  - Combined Measurement of Velocity, Temperature and Pressure in Compressible Gas Flows Using Laser-Induced Iodine Fluorescence / Havermann, M. ; Beylich, A. E.
Y1  - 1998
N1  - 9th International Symposium on Applications of Laser Techniques to Fluid Mechanics, Lisbon (Portugal), 1998
PB  - -
ER  - 
TY  - JOUR
A1  - Havermann, Marc
T1  - Effects of the shock tube open-end shape on vortex loops released from it / Kainuma, M. ; Havermann, M. ; Sun, M. ; Takayama, K.
JF  - Shock Waves : Proceedings of the 24th International Symposium on Shock Waves Beijing, China July 11-16, 2004 / edited by Z. Jiang
Y1  - 2005
SN  - 978-3-540-22497-6
SP  - 505
EP  - 510
PB  - Springer
CY  - Berlin
ER  - 
TY  - JOUR
A1  - Havermann, Marc
T1  - Systematic Shock Tube Experiments on Vortex Ring Generation and Propagation / Havermann, M. ; Kainuma, M. ; Takayama, K.
JF  - Shock waves : proceedings of the 25th International Symposium on Shock Waves-ISSW25, July 17 - 22, 2005, Bangalore, India / ed.: G. Jagadeesh
Y1  - 2006
SN  - 978-81-7371571-6
N1  - International Symposium on Shock Waves ; 25 (Bangalore) : 2005.07.17-22
ISSW ; 25 (Bangalore) : 2005.07.17-22
PB  - Universities Pr.
CY  - Hyderabad
ER  - 
TY  - JOUR
A1  - Harder, Jörn
T1  - A crystallographic model for the study of local deformation processes in polycrystals
JF  - International journal of plasticity. 15 (1999), H. 6
Y1  - 1999
SN  - 0749-6419
N1  - Online: http://opus.tu-bs.de/opus/volltexte/1999/10/pdf/10_1.pdf
SP  - 605
EP  - 624
ER  - 
TY  - JOUR
A1  - Hammer, Thorben
A1  - Quitter, Julius
A1  - Mayntz, Joscha
A1  - Bauschat, J.-Michael
A1  - Dahmann, Peter
A1  - Götten, Falk
A1  - Hille, S.
A1  - Stumpf, E.
T1  - Free fall drag estimation of small-scale multirotor unmanned aircraft systems using computational fluid dynamics and wind tunnel experiments
JF  - CEAS Aeronautical Journal
N2  - New European Union (EU) regulations for UAS operations require an operational risk analysis, which includes an estimation of the potential danger of the UAS crashing. A key parameter for the potential ground risk is the kinetic impact energy of the UAS. The kinetic energy depends on the impact velocity of the UAS and, therefore, on the aerodynamic drag and the weight during free fall. Hence, estimating the impact energy of a UAS requires an accurate drag estimation of the UAS in that state. The paper at hand presents the aerodynamic drag estimation of small-scale multirotor UAS. Multirotor UAS of various sizes and configurations were analysed with a fully unsteady Reynolds-averaged Navier–Stokes approach. These simulations included different velocities and various fuselage pitch angles of the UAS. The results were compared against force measurements performed in a subsonic wind tunnel and provided good consistency. Furthermore, the influence of the UAS`s fuselage pitch angle as well as the influence of fixed and free spinning propellers on the aerodynamic drag was analysed. Free spinning propellers may increase the drag by up to 110%, depending on the fuselage pitch angle. Increasing the fuselage pitch angle of the UAS lowers the drag by 40% up to 85%, depending on the UAS. The data presented in this paper allow for increased accuracy of ground risk assessments.
KW  - Multirotor UAS
KW  - Drag estimation
KW  - CFD
KW  - Wind tunnel experiments
KW  - Wind milling
Y1  - 2023
U6  - http://dx.doi.org/10.1007/s13272-023-00702-w
SN  - 1869-5590 (Online)
SN  - 1869-5582 (Print)
N1  - Corresponding author: Thorben Hammer
PB  - Springer
CY  - Wien
ER  -