Add to ORKGThe transition prediction capability of two different semi/empirical methods originating from fixed wing applications is studied for steady, rotary wing application. This includes the AHD method, used with approximated boundary layer data, as well as the Drela eN envelope method, based on integral boundary layer parameters. The methods have been implemented in the DLR's structured flow solver FLOWer. A two-dimensional test case (Somers airfoil) and three-dimensional rotor test case at hover (DLR Bo 105 flight test ) serve to validate the computed transition locations
A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition pre...
A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition pre...
We present a CFD analysis of a wind tunnel model of the new laminar turbo-prop aircraft designed in ...
The transition prediction capability of two different semi/empirical methods originating from fixed ...
The transition prediction capability of two semi/empirical methods originating from fixed wing appli...
The transition prediction capability of two semi-/empirical criteria originating from fixed wing app...
In order to numerically determine the laminar-turbulent transition on hovering rotors, the applicabi...
The modeling of laminar-turbulent transition in RANS flow solvers is an inevitable requirement for t...
The present paper deals with the laminar-turbulent transition prediction on helicopter rotors in hov...
A numerical procedure to improve the performances of a RANS code by including an accurate prediction...
Boundary-layer-transition computations are performed using the in-house finite-volume solvers elsA b...
A method is presented for predicting the laminar-turbulent transition on helicopter rotors. For a ro...
A methodology to predict the laminar-turbulent transition in RANS computations for general three-dim...
Laminar-turbulent transition remains a critical issue in a number of cases, among which drag reducti...
The simulation capabilities of the U/RANS solver TAU of DLR have been successfully extended in order...
A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition pre...
A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition pre...
We present a CFD analysis of a wind tunnel model of the new laminar turbo-prop aircraft designed in ...
The transition prediction capability of two different semi/empirical methods originating from fixed ...
The transition prediction capability of two semi/empirical methods originating from fixed wing appli...
The transition prediction capability of two semi-/empirical criteria originating from fixed wing app...
In order to numerically determine the laminar-turbulent transition on hovering rotors, the applicabi...
The modeling of laminar-turbulent transition in RANS flow solvers is an inevitable requirement for t...
The present paper deals with the laminar-turbulent transition prediction on helicopter rotors in hov...
A numerical procedure to improve the performances of a RANS code by including an accurate prediction...
Boundary-layer-transition computations are performed using the in-house finite-volume solvers elsA b...
A method is presented for predicting the laminar-turbulent transition on helicopter rotors. For a ro...
A methodology to predict the laminar-turbulent transition in RANS computations for general three-dim...
Laminar-turbulent transition remains a critical issue in a number of cases, among which drag reducti...
The simulation capabilities of the U/RANS solver TAU of DLR have been successfully extended in order...
A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition pre...
A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition pre...
We present a CFD analysis of a wind tunnel model of the new laminar turbo-prop aircraft designed in ...