The work cumulated in a series of laminar-turbulent transition flight-test experiments on a swept wing with the goal of validating the spanwise-periodic distributed roughness elements (DRE) technology in a Reynolds number range applicable to SensorCraft technology. Phase I of the program measured freestream turbulence levels that were nominally 0.05 % to 0.06 % of the freestream speed and thus established the suitability of the flight environment for the laminarization flights. Phase II of the program did the baseline transition measurements on the airfoil i.e. with and without DRE technology. The region of laminar flow was extended from 30 % to 60 % chord at a chord Reynolds number of Rec = 8.1 x106 and sweep angle, Λ = 37°. 1
Simulations were carried out to model the receptivity and growth of stationary crossflow vortices fr...
This paper discusses and evaluates the test measurement techniques used to determine the laminar-to-...
Surface roughness elements are often used to force laminar to turbulent transition during aerodynami...
Micron-sized, spanwise-periodic, discrete roughness elements (DREs) were applied to and tested on a ...
Micron-sized, spanwise-periodic, discrete roughness elements (DREs) were applied to and tested on a ...
Micron-sized, spanwise-periodic, discrete roughness elements (DREs) were applied to and tested on a ...
Swept wings and control surfaces are common elements of modern aircraft, and it has been shown both ...
In the context of the ongoing research regarding boundary layer transition, this project aims to stu...
On-going efforts to reduce aircraft drag through transition delay focus on understanding the process...
AbstractA series of experiments were conducted to study the effect of leading-edge roughness on the ...
A series of experiments were conducted to study the effect of leading-edge roughness on the state of...
AbstractThis paper is devoted to a detailed experimental investigation of scenarios of the laminar-t...
Direct numerical simulations (DNS) are performed to study potential stabilizing effect of spanwise p...
One of the last remaining challenges preventing the laminarization of sweptwings is the control of u...
An experimental study of the effects of large distributed roughness located near the leading-edge of...
Simulations were carried out to model the receptivity and growth of stationary crossflow vortices fr...
This paper discusses and evaluates the test measurement techniques used to determine the laminar-to-...
Surface roughness elements are often used to force laminar to turbulent transition during aerodynami...
Micron-sized, spanwise-periodic, discrete roughness elements (DREs) were applied to and tested on a ...
Micron-sized, spanwise-periodic, discrete roughness elements (DREs) were applied to and tested on a ...
Micron-sized, spanwise-periodic, discrete roughness elements (DREs) were applied to and tested on a ...
Swept wings and control surfaces are common elements of modern aircraft, and it has been shown both ...
In the context of the ongoing research regarding boundary layer transition, this project aims to stu...
On-going efforts to reduce aircraft drag through transition delay focus on understanding the process...
AbstractA series of experiments were conducted to study the effect of leading-edge roughness on the ...
A series of experiments were conducted to study the effect of leading-edge roughness on the state of...
AbstractThis paper is devoted to a detailed experimental investigation of scenarios of the laminar-t...
Direct numerical simulations (DNS) are performed to study potential stabilizing effect of spanwise p...
One of the last remaining challenges preventing the laminarization of sweptwings is the control of u...
An experimental study of the effects of large distributed roughness located near the leading-edge of...
Simulations were carried out to model the receptivity and growth of stationary crossflow vortices fr...
This paper discusses and evaluates the test measurement techniques used to determine the laminar-to-...
Surface roughness elements are often used to force laminar to turbulent transition during aerodynami...