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National Aeronautical Establishment (Canada)

Overview
Works: 651 works in 1,096 publications in 2 languages and 2,484 library holdings
Genres: Periodicals 
Roles: Editor
Classifications: TL501, 620
Publication Timeline
Key
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 Canada( serial )
in English and held by 65 libraries worldwide
Aeronautical note ( serial )
in English and held by 37 libraries worldwide
Laboratory technical report. Rapport technique de laboratoire by National Aeronautical Establishment (Canada)( serial )
in English and held by 30 libraries worldwide
Advances in high temperature structural materials and protective coatings ( Book )
2 editions published between 1993 and 1994 in English and held by 27 libraries worldwide
A new method of estimating wind tunnel wall interference in the unsteady two-dimensional flow by H Sawada( Book )
5 editions published in 1983 in English and held by 25 libraries worldwide
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 National Aeronautical Establishment (Canada)( Book )
6 editions published in 1988 in English and held by 25 libraries worldwide
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 million to Re/ft =8 million. The airfoil with riblets exhibited less drag than a completely turbulent air foil (without riblets) for Mach Number M <or = 0.5 and Reynolds Numbers Re/ft <or = 5 million. It was found that the thinner riblets material (0.0013) gave more attractive drag results than the thicker riblets (0.0030). However, at higher Mach numbers Reynolds number no drag reduction was observed. Canada. (edc)
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 23 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)
Tensile fracture of notched composite laminates = Rupture par traction de matériaux composites stratiés by C Poon( Book )
7 editions published in 1991 in English and held by 22 libraries worldwide
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 National Aeronautical Establishment (Canada)( Book )
7 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
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 22 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)
An improved airborne wind measurement technique for the NAE Twin Otter by B. W Leach( Book )
5 editions published in 1989 in English and held by 21 libraries worldwide
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 )
5 editions published in 1990 in English and held by 21 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
Determination of handling qualities and display requirements for helicopter instrument flight during decelerating approaches to slow speeds = Détermination des exigences en matière de qualités de manoeuvrabilité et d'affichage pour le vol aux instruments des hélicoptères pendant les approches en décélération à de faibles vitesses by National Aeronautical Establishment (Canada)( Book )
3 editions published in 1987 in English and held by 21 libraries worldwide
This paper discusses the most recent phase of a series of experiments performed jointly by the National Aeronautical Establishment and the United States Federal Aviation Administration. The experiment was aimed at determining the helicopter instrument flight handling qualities requirements when performing steep approaches to low decision heights to a landing area colocated with a Microwave Landing System. A total of 118 approaches were evaluated by three helicopter certification test pilots and one operational/training helicopter pilot. Results indicate that with simple rate damping augmentation in pitch, roll and yaw, and flight director guidance, a Bell 205A-1 exhibited borderline Level 1 (certifiable) handling qualities when performing decelerating approaches to 20 knots to decision heights representative of Category IIIA weather limits. Keywords: Helicopter handling; Instrument flight; (Canada)
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 National Aeronautical Establishment (Canada)( Book )
2 editions published in 1983 in English and held by 20 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)
High temperature protective coatings for aero engine gas turbine components = revêtements protecteurs hautes températures pour composants de turbines à gaz aéronautique by Prakash Chandra Patnaik( Book )
5 editions published in 1986 in English and held by 20 libraries worldwide
Aluminide coatings have been widely used in the aircraft industries for the protection of gas turbine engine hot section components against oxidation and/or hot corrosion. This paper considers modes of coating degradation under conditions of cyclic oxidation, hot corrosion and corrosion-erosion interactions during service as well as the effects of interdiffusion between coating and substrate alloys either during service or coating application. It also discusses means of improving existing coatings as well as advanced coating systems currently under development. In assessing coating performance, consideration must be given to the influence coatings may have on substrate properties such as mechanical strength, resistance to creep and resistance to mechanical and thermal fatigue. Finally it is stressed that proven performance for a given coating/substrate combination is no guarantee that no deleterious reaction will occur, when the same coating is used with a different substrate alloy. Therefore, coating substitution requires requalification. Keywords: Aircraft engines; Protective coatings
Development of the microsas longitudinal flight control system for the augmentor wing aircraft by National Aeronautical Establishment (Canada)( Book )
6 editions published in 1983 in English and held by 20 libraries worldwide
A digital longitudinal stability augmentation system was designed and installed in the Augmentor Wing Research Aircraft by the Flight Research Laboratory of the National Aeronautical Establishment. This system partially replaced the computer-controlled control and display system called STOLAND owned by NASA Ames Research Center that was removed from the aircraft prior to its return to Canada. The computer system is described and the software flow charts are illustrated. Brief comments on the performance of the system during the flight test program are included
Skin friction measurements for two relatively thick airfoil sections at high reynolds number = Mesures du frottement sur deux profils aérodynamiques assez épais à nombres de reynolds élevés by G. M Elfstrom( Book )
3 editions published in 1984 in English and held by 19 libraries worldwide
This Canadian report describes an experimental investigation of turbulent skin friction for two airfoil sections under conditions of high Reynolds number. Data are presented for an NACA 0020 section at a Mach number of 0.30 and chord Reynolds numbers between 5 and 20 million, and for a 16% thick supercritical section at a Mach number of 0.74 and chord Reynolds numbers between 15 and 25 million. Together with estimates of boundary layer transition location, these data are integrated to determine the skin friction component of total drag. The results are then discussed in terms of observed variation of total drag with Reynolds number
 
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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)
NAE
NAE Abkuerzung
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
Languages
English (94)
French (1)
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