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National Aeronautical Establishment (Canada)

Overview
Works: 772 works in 1,366 publications in 3 languages and 2,773 library holdings
Genres: Periodicals  Bibliography  Catalogs 
Roles: Other, Editor
Classifications: TL523, 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 of Canada( serial )
in English and held by 66 libraries worldwide
Aeronautical note by National Research Council of Canada( serial )
in English and held by 37 libraries worldwide
Laboratory technical report. Rapport technique de laboratoire by National Aeronautical Establishment (Canada)( serial )
in 3 languages and held by 36 libraries worldwide
A new method of estimating wind tunnel wall interference in the unsteady two-dimensional flow by H Sawada( Book )
7 editions published in 1983 in English and held by 26 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)
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 )
5 editions published in 1984 in English and held by 24 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
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)
An improved airborne wind measurement technique for the NAE Twin Otter by National Aeronautical Establishment (Canada)( Book )
6 editions published in 1989 in English and held by 24 libraries worldwide
Airborne wind measurement techniques currently being used onboard the NAE Twin Otter Atmospheric Research Aircraft are described and their fundamental limitations are discussed. In particular, a recently acquired LTN-90-100 strapdown inertial reference system (IRS) demonstrates significant low frequency Schuler oscillations in its velocity components (attaining peak errors of 2 to 3 mps), actually degrading wind computation accuracy compared with older techniques. A new wind measurement technique, based on Kalman filter integration navigation approach, is described which solves this problem and provides wind computation accuracy superior to previous methods. Preliminary results, based on applying the Kalman filter to Twin Otter flight test data, indicate that inertial velocity accuracies of 0.3 mps RMS (per channel) are attainable, with a corresponding improvement in the accuracy of earth-referenced wind components. Keywords: Canada; French language
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 )
8 editions published in 1987 in 3 languages and held by 24 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
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 )
8 editions published in 1988 in English and held by 24 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
Wing [i.e. Wind] tunnel investigation of dynamic stall of an NACA 0018 airfoil ocsillating [sic] in pitch = Etude en soufflerie du décrochage aérodynamique d'un profil NACA 0018 oscillant en tangage by R. H Wickens( Book )
8 editions published in 1985 in English and held by 23 libraries worldwide
This report presents aerodynamic data on an NACA 0018 airfoiloscillating in pitch in the NAE 2m x 3m Low Speed Tunnel. Thepurpose of the test was to simulate the dynamic aerodynamicbehaviour of a Vertical Axis Wind Turbine blade section at theequatorial plane under the dynamic stall conditions which mayoccur at low ratios of tip speed to wind speed. Measurementswere made of wing surface pressure time histories at variouschordwise locations, during a complete cycle of oscillation. Thedynamic effects on nose suction pressures were seen to increasetheir magnitude and to delay flow breakdown to a higher angle ofattack. Integration of wing pressures furnished normal andchordwise forces during the angle of attack cycle. The behaviourof these parameters showed that dynamic stall for wing angles ofattack up to 30 degrees, occurred about 5 degrees later than forthe equivalent steady flow case. This phenomenon resulted in anincrease in normal force of about 20% and an increase inchordwise force of about 40% when the wing is pitching to 30degrees
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 23 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
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)
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 S Kereliuk( Book )
3 editions published in 1987 in English and held by 23 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)
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
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
Evaluation of the effects of lateral and longitudinal aperiodic modes on helicopter instrument flight handling qualities = Évaluation des effets des modes apériodiques latéraux et longitudinaux sur les qualités de pilotage aux instruments des hélicoptères by S. R. M Sinclair( Book )
3 editions published in 1983 in English and held by 21 libraries worldwide
This report describes a part of a larger program funded jointly by the US Federal Aviation Administration and the National Aeronautical Establishment to provide background information on instrument flight handling qualities of helicopter. This latest series of tests was aimed at addressing the acceptability of pitch and roll aperiodic characteristics when performing general handling and mission-oriented tasks in the NAE Airborne Simulator. In general, the results of these tests are consistent with proposed requirements for helicopter IFR handling qualities. Two significant factors were highlighted in these tests: aircraft characteristics which were not specifically under study may have affected pilot opinions; and changes in pilot opinion occurred depending on whether the task was one of general handling or was specifically mission-oriented. (Author)
 
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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
National Aeronautical Establishment
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
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