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23 results on '"Laberge, J. G"'

3. Measurement of dynamic cross-derivatives due to pitching and yawing

Author

Orlik-Rueckemann, K. J, Laberge, J. G, and Hanff, E. S

Subjects
Facilities, Research, And Support
Abstract

A novel wind-tunnel apparatus is described with which all the 12 static and dynamic moment derivatives due to pitching and yawing can be obtained at angles of attack up to 40 deg and in the presence of some sideslip. The experimental technique and the data reduction procedure are discussed, and preliminary data on dynamic derivatives for an aircraft-like configuration at M ? 0.70 are presented. It is shown that in the range of angle of attack investigated, some rather large variations occur in both the two direct damping derivatives and some of the dynamic cross-derivatives; the latter, however, remain small as compared to the corresponding direct damping derivatives (in general less than 10%).

Published
1974

4. Experiments on the dynamic stability of the space shuttle

Author

Orlik-Rueckermann, K. J, Laberge, J. G, and Hanff, E. S

Subjects
Space Vehicles
Abstract

Some dynamic stability experiments on the space shuttle using a half-model oscillatory technique are discussed. Resulting information from the experiments is presented and includes: (1) dynamic pitching characteristics of both the orbiter and the booster alone as well as of the two models mated into a single launch configuration; (2) the static and dynamic interference effects during an abort separation maneuver; and (3) the dynamic plume interference effect.

Published
1972

5. Static and dynamic pitching moment measurements on a family of elliptic cones at Mach number 11 in helium

Author

Orlik-Rueckermann, K. J and Laberge, J. G

Subjects
Fluid Mechanics
Abstract

Static and dynamic pitching moment measurements were made on a family of constant volume elliptic cones about two fixed axes of oscillation in the NAE helium hypersonic wind tunnel at a Mach number of 11 and at Reynolds numbers based on model length of up to 14 million. Viscous effects on the stability derivatives were investigated by varying the Reynolds number for certain models by a factor as large as 10. The models investigated comprised a 7.75 deg circular cone, elliptic cones of axis ratios 3 and 6, and an elliptic cone with conical protuberances.

Published
1970

6. Supersonic Experiments on Dynamic Cross-Derivatives Due to Pitching and Yawing of Aircraft-Like Vehicles

Author

Orlik-Ruckemann, K. J, Laberge, J. G, and Hanff, E. S

Subjects
Aircraft
Abstract

A wind tunnel apparatus has been developed and constructed for the determination of moment cross-derivatives due to pitching and yawing on models at moderate angles of attack and sideslip. The apparatus can also be used to determine the direct moment derivatives in pitch and yaw. Experimental results were obtained at Mach 2 on a cone-wing-fin configuration at angles of attack and sideslip up to 15. Although at small values of these angles the cross-derivatives were always negligibly small, measureable effects were sometimes observed, at all angles of attack included in this investigation (i.e. up to 15 deg), when the angle of sideslip was 10 deg or 15 deg.

Published
1973

7. Supersonic tunnel tests on effects of engine-off operation on lateral characteristics of the C-105 aircraft

Author

LaBerge, J. G. and Boyer, D. W.

Subjects
intercepteur supersonique à ailes delta, Canada supersonic jet, avion à réaction supersonique du Canada, Avro Canada CF-105 Arrow, Avro Canada, Avro Arrow, A.V. Roe Canada, CF-105, delta-winged supersonic interceptor
Abstract

The effect of blocking completely or partially one engine intake on the side force and yawing moment of the C-105 aircraft was investigated at supersonic speeds. A 1/80 scale model was tested in the 10 inch tunnel, the force and moment measurements being taken at a Mach number of 2.04. Schlieren photographs are presented for Mach numbers of 1.64 and 2.04. Over the whole range of yaw angles explored complete blockage of one intake resulted in a yawing moment (ΔCₙ =0.001) tending to put the blocked intake on the windward side of the fuselage.

Published
1955

8. Six-component supersonic wind tunnel tests of a 1/80 scale model of the C-105 aircraft

Author

LaBerge, J. G.

Subjects
intercepteur supersonique à ailes delta, Canada supersonic jet, avion à réaction supersonique du Canada, Avro Canada CF-105 Arrow, Avro Canada, Avro Arrow, A.V. Roe Canada, CF-105, delta-winged supersonic interceptor
Abstract

Six-component supersonic wind tunnel tests were carried out on a 1/80 scale model of the C-105 aircraft at four Mach numbers. In all, 27 model configurations were investigated over a period of three months requiring a total of 1991 tunnel runs. This memorandum contains the results of these tests in the form of basic plots, cross plots and final aerodynamic derivatives. In order to expedite the publication of the data, the results are presented without detailed analysis.

Published
1956

9. Minimum drag tests on the C-105 1/80 scale model

Author

Laberge, J. G.

Subjects
intercepteur supersonique à ailes delta, Canada supersonic jet, avion à réaction supersonique du Canada, Avro Canada CF-105 Arrow, Avro Canada, Avro Arrow, A.V. Roe Canada, CF-105, delta-winged supersonic interceptor
Abstract

Zero lift drag measurements of a 1/80 scale model of the C-105 aircraft were made in the 30-inch tunnel at subsonic and supersonic speeds. The Mach number range extended from 0.53 to 1.57 corresponding to a Reynolds number range of 1.2 to 1.7 x 10⁶ based on wing mean aerodynamic chord, see Fig. 1.

Published
1955

11. Some zero-lift characteristics of a 1/80 scale model of the CF-105 aircraft at test Mach Number of 1.57

Author

LaBerge, J. G.

Subjects
intercepteur supersonique à ailes delta, Canada supersonic jet, avion à réaction supersonique du Canada, Avro Canada CF-105 Arrow, Avro Canada, Avro Arrow, A.V. Roe Canada, CF-105, delta-winged supersonic interceptor
Abstract

At supersonic speeds the values of C ₘₒ predicted and measured by the N.A.E. were found to disagree with the values measured by the N.A.C.A. In an attempt to discover a possible explanation for this discrepancy a detailed investigation was made in the area of interest and at a Mach number of 1.57. The effect of tunnel flow angularity was assessed by testing the model in both the inverted and upright positons while the effect of flow through the rather long and narrow intake ducts of the model was determined by testing the model with and without fairings over the intakes. In addition the effect of duct flow on the drag was determined at zero lift.

Published
1957

12. Dynamic Stability Testing of Unconventional Configurations

Author

NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), Orlik-Ruckemann,K. J., Adams,P. A., LaBerge,J. G., NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), Orlik-Ruckemann,K. J., Adams,P. A., and LaBerge,J. G.

Abstract

Situations frequently occur when standard wind-tunnel test equipment, based on the concept of an all-containing rear-sting support is impractical or even impossible to use. In the paper, two alternative test arrangements are indicated and descriptions are given of the experimental equipment and procedures. Full and half-model techniques are discussed and the experimental procedures include free and forced-oscillation methods. Examples contain cases such as flat elliptic cones, cones at incidence and combinations of two models in close proximity (space shuttle), at supersonic and hypersonic speeds., Presented at the AIAA Aerodynamic Testing Conference (6th), Albuquerque, N. Mex., 10-12 Mar 71. Revision of report dated 21 Jul 71.

Published
1971

13. Supersonic Dynamic Stability Experiments on the Space Shuttle

Author

NATIONAL RESEARCH COUNCIL OF CANADA OTTAWA (ONTARIO), Orlik-Ruckemann,K. J., LaBerge,J. G., Hanff,E. S., NATIONAL RESEARCH COUNCIL OF CANADA OTTAWA (ONTARIO), Orlik-Ruckemann,K. J., LaBerge,J. G., and Hanff,E. S.

Abstract

A wind-tunnel study was performed of the longitudinal dynamic stability of the shuttle spacecraft at supersonic speeds. In particular, the study included the determination of the damping-in-pitch characteristics of the orbiter and of the booster, both separately and in a mated launch configuration, and the investigation of the effect of a simulated rocket exhaust plume and of the static and dynamic interference during abort separation. Static interference is defined here as caused by the proximity of the second vehicle when that vehicle is stationary, whereas dynamic interference denotes the same effect but with the other vehicle performing an oscillatory motion. (Author), Presented at the AIAA Aerospace Sciences Meeting (10th), San Diego, Calif., 17-19 Jan 72 (AIAA Paper No. 72-135).

Published
1972

14. Effect of Flow Discontinuities on Oscillatory Pressures Measured in Supersonic Wind Tunnels

Author

NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), Orlik-Rueckemann,K. J., LaBerge,J. G., NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), Orlik-Rueckemann,K. J., and LaBerge,J. G.

Abstract

The effect of wind-tunnel flow discontinuities, which previously was considered to be a serious obstacle in measuring oscillatory surface pressures at supersonic speeds, was investigated. Results are reported for a particular nozzle in one tunnel., Revision of report dated 6 Aug 69.

Published
1969

15. On Dynamic Stability Testing of Unconventional Configurations

Author

NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), Orlik-Ruckemann,K. J., Adams,P. A., LaBerge,J. G., NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), Orlik-Ruckemann,K. J., Adams,P. A., and LaBerge,J. G.

Abstract

Situations frequently occur when standard wind-tunnel test equipment, based on the concept of an all-containing rear-sting support is impractical or even impossible to use. In this paper some possible alternative test arrangements are indicated and descriptions are given of the actual experimental equipment and procedures. Full- and half-model techniques are discussed and the experimental procedures include free- and forced-oscillation methods. Examples contain cases such as cones at incidence and combinations of two models in close proximity (space shuttle), at supersonic and hypersonic speeds. Comparisons of results obtained with different methods and techniques are included. (Author), Pub. in Proceedings of the AIAA Aerodynamic Testing Conference (6th) Albuquerque, New Mexico, 10-12 Mar 71, AIAA Paper No. 71-276.

Published
1971

16. LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF BLACK BRANT V AT MACH NUMBER 7 IN HELIUM

Author

NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), LaBerge,J. G., NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), and LaBerge,J. G.

Abstract

Two slightly different configurations of the Black Brant V rocket were tested at Mach number 7 in the NAE helium hypersonic wind tunnel. Static longitudinal characteristics were measured at two Reynolds numbers differing by a factor of 8, over a nominal incidence range of plus or minus 5 degrees. The helium results were converted to equivalent air results and compared with those of the NAE 5-foot air wind tunnel, in which the maximum Mach number reached was 4.25. The results from both tunnels were compared with calculated values. (Author)

Published
1967

23. New hormonal therapy in prostatic carcinoma: combined treatment with an LHRH agonist and an antiandrogen.

Author

Labrie F, Dupont A, Belanger A, Cusan L, Lacourciere Y, Monfette G, Laberge JG, Emond JP, Fazekas AT, Raynaud JP, and Husson JM

Subjects
Adenocarcinoma diagnosis, Adenocarcinoma pathology, Androgen Antagonists therapeutic use, Animals, Bone Neoplasms secondary, Buserelin, Drug Therapy, Combination, Gonadotropin-Releasing Hormone therapeutic use, Humans, Male, Prostatic Neoplasms diagnosis, Prostatic Neoplasms pathology, Rats, Adenocarcinoma drug therapy, Gonadotropin-Releasing Hormone analogs & derivatives, Imidazoles therapeutic use, Imidazolidines, Prostatic Neoplasms drug therapy
Abstract

In order to block the influence of androgens from all sources on the growth of prostatic cancer, we have used a new hormonal therapy based on medical castration achieved with the potent LHRH agonist [D-Ser(TBU)6, des-Gly-NH2(10)]LHRH ethylamide (HOE-766) combined with the administration of a pure antiandrogen that neutralizes the action of adrenal androgens as well as those still secreted in low amounts by the testis during LHRH agonist treatment. This study was performed in ten patients with advanced prostatic carcinoma (9 at stage D2 and one at stage C). Bone pain, prostatism and general well-being were 60 to 90% improved within one month after starting treatment in all patients. After 2 months of treatment, minimal bone pain remained only in one patient who was originally bedridden. Bone scanning showed a 70 to 90% decrease in uptake after 3 to 5 months of treatment in the patients studied. Acid phosphatase levels were 60 to 90% reduced after 2 months of treatment in 3 out of the 4 patients who had elevated levels before therapy. Marked objective and subjective improvement was thus rapidly observed in 9 out of 10 patients treated with the combined therapy, while, in the other patient at stage C, subjective improvement could be documented. Although preliminary, this study indicates that a combined hormonal therapy which neutralizes all androgenic influences on peripheral tissues is of potential benefit in prostatic cancer. Moreover, the ease of application as well as the lack of secondary effects of the present approach should make possible its use early in the disease and should thus minimize the development of metastases and androgen-resistant cell clones. Randomized prospective studies on this potentially beneficial therapy are warranted.

Published
1982

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