National Aeronautical Establishment (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 24 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

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 24 libraries worldwide

Static pressure position error calibration of the NAE T-33 C-FSKH = Étalonnage de la pression statique du T-33 C-FSKH de l'éan pour déterminer l'erreur de position by J. F Aitken( Book )
4 editions published in 1987 in English and held by 24 libraries worldwide

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 24 libraries worldwide

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 24 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 24 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

Development of the microsas longitudinal flight control system for the augmentor wing aircraft by S Kereliuk( Book )
7 editions published in 1983 in English and held by 23 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

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 23 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)

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 )
5 editions published in 1987 in English and French and held by 23 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

Hygrothermal effects in continuous fibre reinforced composites = Effets hygrothermiques dans les composites à renfort de fibre continu by J. P Komorowski( Book )
5 editions published in 1983 in English and held by 22 libraries worldwide