TY - GEN
T1 - Numerical and experimental investigation of a helicopter engine side intake
AU - Knoth, Florian
AU - Breitsamter, Christian
N1 - Publisher Copyright:
© Springer International Publishing AG 2018.
PY - 2018
Y1 - 2018
N2 - Aerodynamic characteristics of an engine side intake of a light helicopter are investigated experimentally and numerically with an emphasis on fast forward flight (Ma < 0.2). For this purpose, a novel full scale model of a helicopter fuselage section has been developed and tested. With a duct system, including a fan, engine mass flow rates are realized corresponding to real helicopter operating conditions. The wind tunnel data comprise aerodynamic interface plane (AIP) five-hole pressure probe and particle image velocimetry data which are compared to unsteady Reynolds-averaged Navier-Stokes simulations results. In order to assess the influence of the truncation of the fuselage, two numerical cases are compared. The first is a sectional fuselage case, incorporating all wind tunnel model components, and influential wind tunnel parts. The second is a full fuselage case. Only small differences between the sectional and full fuselage cases in flow direction upstream of the intake are present whereas the AIP total pressure distributions provide the same characteristics. The experimental data are also used to validate the numerical simulations while the complementary experimental and numerical data enables a detailed analysis of the flow distortion up to the AIP.
AB - Aerodynamic characteristics of an engine side intake of a light helicopter are investigated experimentally and numerically with an emphasis on fast forward flight (Ma < 0.2). For this purpose, a novel full scale model of a helicopter fuselage section has been developed and tested. With a duct system, including a fan, engine mass flow rates are realized corresponding to real helicopter operating conditions. The wind tunnel data comprise aerodynamic interface plane (AIP) five-hole pressure probe and particle image velocimetry data which are compared to unsteady Reynolds-averaged Navier-Stokes simulations results. In order to assess the influence of the truncation of the fuselage, two numerical cases are compared. The first is a sectional fuselage case, incorporating all wind tunnel model components, and influential wind tunnel parts. The second is a full fuselage case. Only small differences between the sectional and full fuselage cases in flow direction upstream of the intake are present whereas the AIP total pressure distributions provide the same characteristics. The experimental data are also used to validate the numerical simulations while the complementary experimental and numerical data enables a detailed analysis of the flow distortion up to the AIP.
UR - http://www.scopus.com/inward/record.url?scp=85033503037&partnerID=8YFLogxK
U2 - 10.1007/978-3-319-64519-3_3
DO - 10.1007/978-3-319-64519-3_3
M3 - Conference contribution
AN - SCOPUS:85033503037
SN - 9783319645186
T3 - Notes on Numerical Fluid Mechanics and Multidisciplinary Design
SP - 27
EP - 37
BT - New Results in Numerical and Experimental Fluid Mechanics XI - Contributions to the 20th STAB/DGLR Symposium
A2 - Dillmann, Andreas
A2 - Wagner, Claus
A2 - Heller, Gerd
A2 - Kramer, Ewald
A2 - Bansmer, Stephan
A2 - Radespiel, Rolf
A2 - Semaan, Richard
PB - Springer Verlag
T2 - 20th STAB/DGLR Symposium on New Results in Numerical and Experimental Fluid Mechanics, 2016
Y2 - 8 November 2016 through 9 November 2016
ER -