Turbulent boundary layer solution for two-dimensional compressible flow using mixing length and k-ε turbulence models

The continuity, momentum and energy equations for two-dimensional compressible turbulent boundary layers are solved using the k-ε turbulence model and the extended mixing length approach to calculate the shear stress terms. The finite difference equations are set up applying Keller's box scheme and the resulting tridiagonal matrix system is...

A Summary of Transonic Natural Laminar Flow Airfoil Development at NAE

This report contains an analysis of the experimental results obtained from four supercritical natural laminar flow (NLF) airfoils investigated in the NAE High Reynolds Number Test Facility. The airfoils have maximum thickness to chord ratios of 0.10, 0.13, 0.16 and 0.21 and were designed for a lift coefficient of CL = 0.6. Their design Mach...

New transonic test sections for the NAE 5FTx5FT trisonic wind tunnel

The NAE 5ftx5ft blowdown wind tunnel has undergone a major upgrade of its transonic testing capabilities. Two entirely new test sections, one for testing two-dimensional models (2D) and one for testing three-dimensional models and reflection plane models (3D), have been constructed. The two test sections are parts of the so-called Roll-in Roll...

Use of riblets to obtain drag reduction on airfoils at high reynolds number flows

An investigation was carried out to study the drag reduction capabilities of riblets (commercially available) when installed on a supercritical airfoil which was aerodynamically tested in the NAE's High Reynolds Number 2 D Test Facility. The flow conditions in this test ranged from M = 0.15 to M = 0.76, and Re/ft = 1.5 X 106 to Re/ft = 8 X 106 •...

The use of hot-film technique for boundary layer studies on a 21%thick airfoil

A heat transfer method of studying boundary layer flows over airfoils at transsonic test conditions has been investigated. The method employs very thin DISA hot-film gauges housing Constant Temperature Anemometer probes. Provided that the thickness dimension of the films remains less than the critical disturbances height for inducing transition...

An experimental investigation of skin friction on smooth surfaces supporting air bearing channels

A new method, to obtain skin friction reduction by installing airbearing channels on a smooth surface in uniform flow was investigated. The measurements were made by a servo-controlled skin friction balance. The parametric studies of the channel having step dimensions less than the laminar sublayer thicknesses and placed in flows of free stream...

Analysis of experimental data for a 21% thick natural laminar flow airfoil, NAE 68-060-21:1

NAE and de Havilland Aircraft of Canada have designed and tested in the NAE 5 ft X 5 ft wind tunnel a 21% thick supercritical airfoil capable of sustaining long runs of laminar flow on both surfaces. The measured drag levels are superior to those of any model previously tested in this facility and are comparabIe to classical NACA and modern NASA...