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National Aeronautical Establishment (Canada)

Works: 843 works in 1,384 publications in 2 languages and 2,843 library holdings
Genres: Periodicals  Bibliography  Catalogs 
Roles: Other, Editor
Classifications: TL523, 620
Publication Timeline
Publications about National Aeronautical Establishment (Canada)
Publications by National Aeronautical Establishment (Canada)
Most widely held works by National Aeronautical Establishment (Canada)
Quarterly bulletin of the Division of Mechanical Engineering and the National Aeronautical Establishment by National Research Council of Canada( serial )
in English and held by 65 libraries worldwide
Aeronautical note by National Research Council of Canada( serial )
in English and held by 38 libraries worldwide
Laboratory technical report. Rapport technique de laboratoire by National Aeronautical Establishment (Canada)( serial )
in English and held by 32 libraries worldwide
A new method of estimating wind tunnel wall interference in the unsteady two-dimensional flow by H Sawada( Book )
8 editions published in 1983 in English and held by 27 libraries worldwide
A new method of estimating wall interference in unsteady flow is presented. This method is valid for subcritical flow within the accuracy of the linearized small disturbance theory. The main feature of the method is the use of measured pressure along lines in the flow direction near the tunnel walls. This method is particularly effective in a tunnel with ventilated walls because it does not require the representation of wall characteristics with unreliable mathematical expressions. Results of some numerical examples indicate that the new method produces satisfactory results except for cases when the reduced frequencies are close to the tunnel resonance frequencies. For the case of an airfoil in pitching motion, the method has been used to correct the amplitude of the angle attack and the time lag in the motion. (Author)
A review of crashworthiness of composite aircraft structures = étude sur la résistance à l'écrasement des structures d'aéronef en matériaux composites by C Poon( Book )
6 editions published in 1990 in English and held by 25 libraries worldwide
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. Recommendations include a study on the effect of aircraft size on crashworthiness design requirements; the implementation of the KRASH code in Canada to establish commonality in analytical methods with major U.S. and European users; an investigation on the energy absorption capabilities of the design features for small aircraft containing composite and/or composite/hybrid structures; and a parametric study on the crashworthiness design of composite-to-composite and composite-to-metal joints
An accurate numerical technique for determining flight test rate gyroscope biases prior to takeoff = Technique numérique précise pour determiner les erreurs systématiques des gyromètres d'essai en vol avant le décollage by National Aeronautical Establishment (Canada)( Book )
5 editions published in 1989 in English and held by 24 libraries worldwide
Rate gyroscope biases play an important role in flight tests requiring flight path reconstruction a method often used in aircraft parameter estimation. The biases can drift with 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 determine the biases of high quality flight test rate gyroscopes immediately prior to a flight. The accuracy of the method is such that the earth rate is clearly sensed and accounted for, a variable rarely considered in flight testing. The method requires minimal time and no calibration hardware. (JES)
Use of riblets to obtain drag reduction on airfoils at high Reynolds number flows = Utilisation de petites nervures pour obtenir une diminution de la traînée sur des plans porteurs soumis à des vitesses correspondant à des nombres de Reynolds élevés by M Khalid( Book )
7 editions published in 1988 in English and held by 23 libraries worldwide
This paper reports some results from an investigation concerning the application of riblets on airfoil surfaces at a range of Mach Numbers from M=0.15 to 0.76 and up to a Reynolds Number of 8 million per foot. The measurements were made in NAE's 15" X 60", 2 D High Reynolds Number Trisonic Facility. Two sizes of riblet sheets having groove measurements of 0.0013 and 0.0030 inches were mounted on a 13% thick airfoil. The effective drag on the airfoil, with and without the riblets was measured by a sidewall-mounted traversing rake supporting four pivot probes. This report provides a short background to the work, with a brief discussion of the facility and the experiment, followed by an analysis of the results
Comparison of boundary layer trips of disks and grit types on airfoil performance at transonic speeds / Comparaison de l'effet des déclencheurs de transition de couche limite des types à disques et à grains sur les caractéristiques des profils aérodynamiques aux vitesses transsoniques / par Y.Y. Chan by Y. Y Chan( Book )
7 editions published in 1988 in English and held by 23 libraries worldwide
Investigation of the effects on aerodynamic performance of a supercritical airfoil applying disk or grit tripping for boundary layer transition at transonic speeds. The investigation was performed on a two-dimensional airfoil section with both forward and rear tripping. A single row disk strip was employed for all tests with chord Reynolds numbers ranged from 4-15 million. The results are then compared with data from an earlier investigation with grit strips at the same conditions
An improved airborne wind measurement technique for the NAE Twin Otter by National Aeronautical Establishment (Canada)( Book )
5 editions published in 1989 in English and held by 23 libraries worldwide
Processing of advanced ceramics which have potential for use in gas turbine aero engines = mise en oeuvre de céramiques de pointe à usage potentiel pour composants de moteurs d'avion by T.M Maccagno( Book )
4 editions published in 1989 in English and held by 23 libraries worldwide
Si3N4 and SiC based advanced ceramics that have been produced by hot isostatic pressing (HIPing) 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 been used to produce both monolithic ceramics and SiC whisker reinforced composite ceramics. This is followed by a comprehensive survey of past efforts to produce Si3N4 and SiC based ceramics by HIPing. It is apparent that many of these efforts have involved HIPing of material that has already been densified by sintering, but such an approach does not really allow the full benefits of HIP processing to be realized. On the other hand, HIPing of Si3N4 based composite produced by reaction bonding may result in ceramic material of superior quality. (jes)
The use of hot-film technique for boundary layer studies on a 21% thick airfoil / Utilisation de la technique du film chaud pour des études de couche limite autour d'un profil d'aile d'une épaisseur relative de 21% / par M. Khalid by M Khalid( Book )
6 editions published in 1987 in 3 languages and held by 22 libraries worldwide
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 of the laminar boundary layer, the heat transfer response from the films, positioned carefully on the model surface, can be studied to determine the boundary layer characteristics. Results from an application study on a 21% thick laminar flow airfoil model are presented and discussed
Flight tests of instrumentation for airborne carbon dioxide flux measurement = Essais en vol de l'appareillage de mesure en vol du flux de dioxyde de carbone by J.I Macpherson( Book )
3 editions published in 1983 in English and held by 22 libraries worldwide
At the request of Agriculture Canada, the Flight Research Laboratory of the National Aeronautical Establishment (NAE) has operated the Twin Otter atmohspheric research aircraft fitted with a CO2 analyzer in order to assess the feasibility of making airborne carbon dioxide flux measurements. This report will summarize progress to date and present an analysis of the data collected during a series of nine test flights in August and September, 1982. The experimental results show that it is possible to make realistic measurements of the heat and CO2 fluxes from an aircraft instrumented to measure vertical gusts. Special tests and analysis procedures were conducted to investigate the accuracy of the carbon dioxide measurements. Recommendations for improvements in the design of future test programs are made. (Author)
Theoretical and measured airflow about the Twin Otter wing = Écoulement aérodynamique théorique et mesuré sur l'aile du Twin Otter by A. M Drummond( Book )
7 editions published between 1983 and 1984 in English and held by 22 libraries worldwide
The NAE Twin Otter atmospheric research aircraft carries instruments mounted under the wings to count and image cloud and precipitation particles for cloud physics studies. As part of an investigation on the influence of the aircraft presence on these measurements, airflow velocities about the wing have been calculated. These theoretical results have been compared with in-flight measurements taken by pressure probes mounted in a cannister suspended from a long and a short pylon below the wing at two spanwise locations. The Twin Otter wing has been represented by a Joukowski aerofoil of the same maximum thickness but with a cusped trailing edge. The wing camber has been neglected but aspect ratio and planform effects have been included. The effect of the cannister was included in the comparison of theory with experiment. Use of theory aft of the quarter chord will require experimental verification. Both experimental and theoretical results for the local flow velocity ratio are linear functions of aircraft lift coefficient (CL) in the range of Cl between 0.35 to 1.06. The worst discrepancy between theory and experiment in the CL range of 0.4 to 0.6 is -2.8% to +1.1%. The results for the inboard/long pylon and outboard/short pylon have considerably less deviation. The theory has been experimentally verified to the above accuracy and can be used to describe the spatial variation of the flow velocity ahead of the wing. Applications of the theory to the study of aircraft flow effects on cloud physics measurements can proceed with a quantifiable level of confidence. (Author)
The influence of turbulence and deck section geometry on the aeroelastic behaviour of a cable-stayed bridge model = Les effects de la turbulence et de la géométrie de sections de tablier sur le comportement aéroélastique d'une maquette de pont à haubans by S. J Zan( Book )
9 editions published between 1985 and 1986 in English and French and held by 22 libraries worldwide
The reports contains the results of a full aeroelastic model test of acable-stayed bridge at a geometric scale of 1:75. Nine deck section configurations were tested in three different flows; two of which wereproperly scaled atmospheric turbulence, and the third being smooth flow. The experiments were performed in the NAE 9 m * 9 m wind tunnel
An experimental investigation of skin friction on smooth surfaces supporting air bearing channels = Étude expérimentale du frottement pelliculaire sur fes surfaces lisses porteuses de canux anti-frottement by M Khalid( Book )
4 editions published in 1986 in English and French and held by 21 libraries worldwide
A new method, to obtain skin friction reduction by installing air-bearing 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 velocity up to 90 ft/s have shown that an average skin friction reduction of 25% in the air bearing cavity is well within reach. It was also confirmed that riblet type surface grooves can produce up to 10% skin friction drag reduction
A review of research and development in crashworthiness of general aviation aircraft : seats, restraints and floor structures = revue de la recherche et du développement en matière de résistance à l'écrasement des aéronefs d'aviation générale : sont examinés les sièges, les attaches et les planchers by P Huculak( Book )
5 editions published in 1990 in English and held by 21 libraries worldwide
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 fatal and serious accidents. Study of the work on seats, restraints and floor structures has revealed that more attention to several research topics could ameliorate high accident rates in general aviation
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Alternative Names

controlled identity Institute for Aerospace Research (Canada)

Aeronautical Establishment
Aeronautical Establishment Ottawa
Canada Establissement aéronautique national
Canada Etablissement aéronautique national
Canada Institut de recherche aérospatiale
Canada Institute for Aerospace Research
Canada National Aeronautical Establishment
Canada. National Aeronautical Research Committee. National Aeronautical Establishment
Conseil national de recherches Canada Etablissement aéronautique national
Conseil national de recherches Canada Institut de recherche aérospatiale
Conseil national de recherches du Canada Etablissement aéronautique national
Establissement aéronautique national (Canada)
Etablissement Aéronautique National
Etablissement aéronautique national (Canada)
Etablissement Aéronautique National Ottawa
Institute of Aerospace Research (Canada)
National Aeronautical Establishment (Canada)
National Research Council Canada Establissement aéronautique national
National Research Council Canada Etablissement áeronautique national
National Research Council Canada Institute for Aerospace Research
National Research Council Canada National Aeronautical Establishment
National Research Council of Canada Establissement aéronautique national
National Research Council of Canada Etablissement áeronautique national
National Research Council of Canada National Aeronautical Establishment
English (112)
French (3)
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