TY - GEN
T1 - Two-dimensional inflow above disk for an actuator strip in axial flow
AU - Rojas, Pilar
AU - Peters, David A.
AU - Karunamoorthy, Swami
PY - 2002
Y1 - 2002
N2 - The modeling of unsteady airflow around a rotor has always been a challenge in the design and analysis of a helicopter. While the flow is three-dimensional in nature, a twodimensional analysis provides a good basis in understanding the physics of the problem. An existing finite-state wake model that is based on an acceleration potential theory ignores some of the inflow modes. A new model derived from first principles by a Galerkin method with velocity potentials provides a unique and complete theory to compute the flow parameters on-disk as well as off-disk. While the results for the flow field on-disk are available in the literature, an emphasis is given in this paper to compute the flow field off-disk, above the rotor. The results for both components of induced velocity for the case of axial flow are included in this paper. Also, these results from Galerkin Method have been compared with an exact solution obtained by a convolution integral.
AB - The modeling of unsteady airflow around a rotor has always been a challenge in the design and analysis of a helicopter. While the flow is three-dimensional in nature, a twodimensional analysis provides a good basis in understanding the physics of the problem. An existing finite-state wake model that is based on an acceleration potential theory ignores some of the inflow modes. A new model derived from first principles by a Galerkin method with velocity potentials provides a unique and complete theory to compute the flow parameters on-disk as well as off-disk. While the results for the flow field on-disk are available in the literature, an emphasis is given in this paper to compute the flow field off-disk, above the rotor. The results for both components of induced velocity for the case of axial flow are included in this paper. Also, these results from Galerkin Method have been compared with an exact solution obtained by a convolution integral.
UR - https://www.scopus.com/pages/publications/85067317100
U2 - 10.2514/6.2002-2814
DO - 10.2514/6.2002-2814
M3 - Conference contribution
AN - SCOPUS:85067317100
SN - 9781624101106
T3 - 20th AIAA Applied Aerodynamics Conference
BT - 20th AIAA Applied Aerodynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 20th AIAA Applied Aerodynamics Conference 2002
Y2 - 24 June 2002 through 26 June 2002
ER -