document

Flight evaluation of curved path MLS precision approaches in a Falcon 20 aircraft

Croll, J.B. (author)

A Falcon 20 aircraft belonging to the National Research Council (NRC) was used for the demonstration and evaluation of curved, segmented approaches using the Microwave Landing System (MLS) as a position sensor. A total of over 80 approaches flown by pilots from Transport Canada, the Department of National Defence and NRC confirmed that curved...

report 1995

document

Torque and thrust from five-hole pressure probe measurements in the near slipstream of a propeller in compressible flow

Öhman, L.H. (author)

A momentum analysis has been performed of the flow through a propeller in compressible flow, leading to integral expressions for torque and thrust in terms of local flow quantities such as flow angles, total pressure and Mach number, that can be derived from live-hole pressure probe measurements in the near slipstream. Such data, obtained for...

report 1995

document

Support interference assessment in rotary experiments using the orbital platform concept

Penna, P.J. (author), Beyers, M.E. (author)

A flow visualization study was undertaken to investigate the unobstructed vortical flows generated by a cone-cylinder model in steady coning motion at high angle of attack. Using an orbital platform apparatus in a water tunnel, spatial measurements of vortex breakdown could be made with and without a rotary support sector downstream of the model...

report 1994

document

Influence of the transonic doublet in the farfield of a lifting airfoil

Mokry, M. (author)

A method is described for calculation of the transonic doublet and its inclusion in the farfield boundary condition of a finite-volume, time-stepping solver of the Euler equations. Also discussed is the assessment of the wall interference on a lifting, supercritical airfoil, which takes into account the doublet effect at wind tunnel walls.

report 1993

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The effects of tailwinds and control cross coupling on rotorcraft handling qualities for steep, decelerating instrument approaches and missed approaches

Baillie, S.W. (author), Kereliuk, S. (author), Morgan, J.M. (author)

The expansion of the rotorcraft instrument flight envelope to allow steep, decelerating approaches to low speeds and altitudes will profoundly improve the utility of these vehicles. As a supplement to previously published investigations by the National Research Council of Canada in the Bell 205 Airborne Simulator, a research program was...

report 1993

document

Measurements of wing and fin buffering on the standard dynamics model

Zan, S.J. (author)

This report is concerned with a wind tunnel investigation of wing and fin buffeting measured on the Standard Dynamics Model, a generic fighter aircraft configuration. Buffering was investigated for three modes - the fin bending mode and the wing symmetrie and anti-symmetrie bending modes. Testing was conducted in the IAR 2m x 3m low-speed wind...

report 1993

document

Flow-field interference produced by an asymmetrical support strut

Beyers, M.E. (author), Cai, H.J. (author), Penna, P.J. (author)

The interference flow field associated with an asymmetrical strut-mounted aircraft model was studied visually and through floor pressure measurements in a low-speed wind tunnel. The work was undertaken to shed light on the unsteady interference phenomena which are expected to prevail in oscillatory tests. The conditions under which direct...

report 1993

document

Trajectories and stability of trailing vortices very near the ground

Drummond, A.M. (author), Onno, R. (author), Panneton, B. (author)

The behaviour of the trailing vortices of a Harvard aircraft used as the spraying vehicle during a set of experiments in aerial spraying over flat terrain for agricultural applications is discussed. The aircraft flew at a nominal attitude of 3 m (10 ft.) above ground at a speed of 56.7 m/s (110 knots). The stability and trajectory of a chosen...

report 1991

document

Flight evaluation of curved MLS precision approaches in a Twin Otter Aircraft. Phase II

Croll, J.B. (author)

Phase II flight testing of curved, segmented approaches using a Microwave Landing System (MLS) was conducted on a Twin Otter aircraft belonging to the Canadian National Research Council's Institute for Aerospace Research (IAR). Precision guidance algorithms were developed for approaches with track angle changes exceeding 180°. Software...

report 1991

document

A Kalman filter integrated navigation design for the IAR Twin Otter Atmospheric Research Aircraft

Leach, B.W. (author)

The IAR Twin Otter Atmospheric Research Aircraft has a continuing requirement for more accurate, inertially-based navigation data for both track recovery and the calculation of wind gust components. This navigational accuracy is necessary, not just during post-flight analysis, but also for realtime, in-flight guidance and wind computation....

report 1991

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Tracking performance requirements for rotorcraft instrument approaches to reduced minima. Phase 1: Preliminary study

Baillie, S.W. (author), Kereliuk, S. (author), Srinivassan, R. (author), Hoh, R. (author)

The ability to track approach guidance (position and speed) to a low decision height (50 feet) when performing a steep instrument approach (6 to 9 degrees) in a rotoreraft clearly has a profound effect on the success of the approach. This report describes a preliminary attempl to define approach tracking standards for such approaches and...

report 1991

document

A system for the digital image analysis of spray samples

Panneton, B. (author), Drummond, A.M. (author)

A system for analyzing spray samples based on an electronic digitizing camera is described. The implementation and development of both the hardware and the software are discussed as well as the system performance. The system is capable of digitizing a sample into 1504 by 3008 pixels using 256 gray levels. The resolution is 10 μm at the image...

report 1990

document

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

Khalid, M. (author)

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...

report 1990

document

The IAR high Reynolds number two-dimensional test facility: A description of equipment and procedures common to most 2-D airfoil tests

Galway, R.D. (author)

This report describes features and operational procedures which are common to the great majority of wind tunnel test projects conducted in the Two-Dimensional (2-D) Test Facility of the Institute for Aerospace Research 1.5m Trisonic Blowdown Wind Tunnel in Ottawa, Canada. lt is intended to be used as a reference document describing the 'facility...

report 1990

document

A Summary of Transonic Natural Laminar Flow Airfoil Development at NAE

Khalid, M. (author), Jones, D.J. (author)

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...

report 1990

document

A review of crashworthiness of composite aircraft structures

Poon, C. (author)

A review of major research activities in North America with respect to the crashworthiness of composite aircraft structures was performed with the goal of identifying potential Canadian contribution to R&D areas where effort would be required to complement the on-going programs in the United States. The areas reviewed included the...

report 1990

document

A review of research and development in crashworthiness of general aviation aircraft: seats, restraints and floor structures

Huculak, P. (author)

A literature search has been conducted to determine the status of knowledge of the crashworthiness aspects of general aviation aircraft. Research and development work relating to seats, restraints, and floor structures of general aviation aircraft has been selected for review. The primary goal of crashworthiness studies has been the reduction of...

report 1990

document

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

Ohman, L.H. (author), Brown, D. (author), Chan, Y.Y. (author), Galway, R.D. (author), Hashim, S.M. (author), Khalid, M. (author), Malek, A. (author), Mokry, M. (author), Tang, N. (author), Thain, J. (author)

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...

report 1990

document

An improved airborne wind measurement technique for the NAE twin otter

Leach, B.W. (author), MacPherson, J.I. (author)

Airborne wind measurement techniques currently being used onboard the NAE Twin Otter Atmospheric Research Aircraft are described and their fundamentallimitations are discussed. In particular, a recently acquired L TN-90-1 00 strapdown inertial reference system (IRS) demonstrates significant low frequency Schuier oscillations in its velocity...

report 1989

document

An accurate numerical technique for determining flight test rate gyroscope biases prior to takeoff

Beauchamp, G.M. (author)

Rate gyroscope biases play an important role in flight tests requiring flight path reconstruction, a method of ten used in aircraft parameter estimation. The biases can drift wi th time, be affected by system power up and, ideally, should be calibrated before each flight to maintain optimum performance. This report details a numerical method to...

report 1989