Add to ORKGA potential-flow panel method was modified to calculate the effects of a rotor wake on the time-averaged surface pressure and velocity distributions on a helicopter fuselage. The rotor-induced velocities are calculated by using a vortex-tube wake model. The calculated pressure distributions are found to compare well with experimental data obtained from tests of a wind-tunnel model
Tests have been conducted on the Langley helicopter test tower to determine the vertical drag and pr...
The prediction capabilities of unstructured primitive-variable and vorticity-transport-based Navier-...
A thin-layer Navier-Stokes code and a panel method code are used to predict the flow over a generic ...
A method was developed which allows the fully coupled calculation of fuselage and rotor airloads for...
The problem of rotor-fuselage aerodynamic interaction has to be considered in industry applications ...
A benchmark test to aid the development of various rotor performance codes was conducted. Simultaneo...
A computational method was developed to treat unsteady aerodynamic interactions between a helicopter...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The theory for predicting helicopter inflow-wake velocities called flat wake theory was correlated w...
Recent advances in computing subsonic flow have been applied to helicopter configurations with vario...
A simple analytical model to account for fuselage-induced velocities at rotor blade elements and at ...
The prediction capabilities of unstructured primitive-variable and vorticity-transport-based Navier-...
Tests have been conducted on the Langley helicopter test tower to determine the vertical drag and pr...
The prediction capabilities of unstructured primitive-variable and vorticity-transport-based Navier-...
A thin-layer Navier-Stokes code and a panel method code are used to predict the flow over a generic ...
A method was developed which allows the fully coupled calculation of fuselage and rotor airloads for...
The problem of rotor-fuselage aerodynamic interaction has to be considered in industry applications ...
A benchmark test to aid the development of various rotor performance codes was conducted. Simultaneo...
A computational method was developed to treat unsteady aerodynamic interactions between a helicopter...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The unsteady loads experienced by a helicopter are known to be strongly influenced by aerodynamic in...
The theory for predicting helicopter inflow-wake velocities called flat wake theory was correlated w...
Recent advances in computing subsonic flow have been applied to helicopter configurations with vario...
A simple analytical model to account for fuselage-induced velocities at rotor blade elements and at ...
The prediction capabilities of unstructured primitive-variable and vorticity-transport-based Navier-...
Tests have been conducted on the Langley helicopter test tower to determine the vertical drag and pr...
The prediction capabilities of unstructured primitive-variable and vorticity-transport-based Navier-...
A thin-layer Navier-Stokes code and a panel method code are used to predict the flow over a generic ...