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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

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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

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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

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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

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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

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Distance measures for speech recognition

Hunt, M.J. (author), Lefèbvre, . (author)

This report is concerned with the application of aspects of statistical pattern classification to speech recognition. It presents an extension of linear discriminant analysis to the case where the classes are unknown. This extension provides solutions to the interrelated problems of the design of acoustic representations and spectral distance...

report 1989

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Processing of advanced ceramics which have potential for use in gas turbine aero engines

Maccagno, T.M. (author)

SiaN4 and SiC based advanced ceramics that have been produced by hot isostatic pressing (HIP'ing) have good potential to be used as hot section components in gas turbine aero engines. This report provides background for an NAE-SML investigation of this potential. The report begins with a general overview of the many fabrication methods that have...

report 1989

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Analysis of experimental data for cast 10-2/DOA 2 supercritical airfoil at low Reynolds numbers and application to high Reynolds number flow

Chan, Y.Y. (author)

The experimental investigation of CAST 10-2/DOA 2 supercritical airfoil previously conducted in the NAE Two-Dimensional Test Facility has been extended to low Reynolds number range at the design Mach number 0.765. The results indicate that with forward transition fixing, the data trend at low Reynolds number is different from that at high...

report 1989

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Comparison of boundary layer trips of disk and grit types on airfoil performance at transonic speeds

Chan, Y.Y. (author)

The effects on aerodynamic performance of a supercritical airfoil applying disk or grit tripping for boundary layer transition has been investigated for a typical supercritical airfoil at transonic speeds. It is observed that by allowing the laminar flow passing through the space between the disks, transition takes place a short distance...

report 1988

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An investigation of lateral tracking techniques, flight directors and automatic control coupling on decelerating IFR approaches for rotorcraft

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

An in flight simulation experiment was performed to investigate the impact on handling qualities and certification of various issues associated with low minima decelerating flight directed IFR approaches for rotorcraft. These issues were the use of crab versus sideslip techniques to maintain lateral tracking under crosswind conditions, the...

report 1988

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

Khalid, M. (author)

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 •...

report 1988

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An experimental study of transonic buffet of a supercritical airfoil with trailing edge flap

Lee, B.B.K. (author), Tang, F.C. (author)

A supercritical airfoil with a trailing edge flap has been the subject of aerodynamic investigation in the National Aeronautical Establishment's High Reynolds Number 2-D Test Facility. The effects of flap deflection on buffet intensities and delay of buffet onset at transonic speeds were studied. Buffet boundaries for various flap angles were...

report 1988

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The orbital-platform concept for nonplanar dynamic testing

Huang, X.Z. (author), Beyers, M.E. (author)

A new concept is introduced for large-amplitude nonplanar testing at high incidence. The dynamic test apparatus is characterized by an annular, orbital platform on which the model support and secondary drive mechanisms are mounted. The device can be used as a rotary apparatus, while arbitrary epicyclic motions (including fixed-plane, orbital...

report 1988

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Field procedure for measurement of flightline offset in forestry spraying

Crabbe, R.S. (author), McCooeye, M. (author)

Some general remarks are presented on the design of a definitive field experiment on windborne droplet drift and deposition in aerial forestry spray applications. The role of the uncontrollable parameters, i.e. forest properties and, in particular, meteorology, is emphasized. Then, the variables in one aspect of the problem, the flightline...

report 1988

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An overview of technology for spoken interaction with machines

Hunt, M.J. (author)

This report provides a non-mathematical introduction to speech input and output technology. It is divided into three parts. The first presents necessary background information on speech: on its nature, its production and perception, and on methods of analysis and coding used in speech 1/0. A central message is that our subjective impression of...

report 1988

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Analysis of experimental data for cast 10-2/DOA2 supercritical airfoil at high Reynolds numbers

Chan, Y.Y. (author)

Experimental data obtained in the NAE Two-Dimensional Test Facility for CAST 10-2jDOA2 supercritical airfoil have been analyzed for the effects of Reynolds number, transition fixing and Mach number. The data were obtained for Reynolds numbers from 6 to 30 million and Mach numbers from 0.3 to 0.8 with fixed and free transitions. The analysis...

report 1988

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Access to microgravity: A technical description of the NAE T-33 microgravity facility

Aitken, J.F. (author)

The National Aeronautical Establishment operates a T-33 aircraft as a facility for short duration microgravity experiments. Details covering sensors available, experiment electrical and mechanical requirements, package size constraints, power available, and requirements for interfacing experiments with the aircraft instrumentation system are...

report 1987

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The application of linear maximum likelihood estimation of aerodynamic derivatives for the BELL-205 and BELL-206

DeLeeuw, J.H. (author), Hui, K. (author)

Parameter identification from flight test data of fixed-wing aircraft is currently a common procedure for application to aircraft development work, validation of simulation, flight simulator verification, flight control systems synthesis, aircraft handling qualities, flight envelope expansion and airplane certification. Similar work on the...

report 1987

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Static pressure position error calibration of the NAE T-33 C-FSKH

Aitken, J.F. (author), Baillie, S.W. (author)

The static pressure position error calibration of the NAE T-33 C-FSKH is presented. This calibration, necessary for the high altitudes and Mach Numbers flown in the United States FAA Vertical Separation Study , is an expansion of earlier low altitude low speed calibrations. Data collected cover a wide range of altitudes and dynamic pressure -...

report 1987