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A simple mechanical analogue for studying the dynamic stability of aircraft having nonlinear moment characteristics

Description: "The analogy between a ball rolling over a contoured surface and a pitching and yawing aircraft is developed. Test results from a model representing a missile with linear moment characteristics are presented to verify the analogy. Several examples of the behavior of nonlinear systems are also given" (p. 1).
Date: February 1954
Creator: Canning, Thomas N.
Partner: UNT Libraries Government Documents Department

Drag and rolling-moment effectiveness of trailing-edge spoilers at Mach numbers 2.2 and 5.0

Description: Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.
Date: October 3, 1955
Creator: Canning, Thomas N. & DeRose, Charles E.
Partner: UNT Libraries Government Documents Department

Investigation in the Ames Supersonic Free-Flight Wind Tunnel of the Static Longitudinal Stability of the Hermes A-3B Missile at a Mach Number of 5.0

Description: Models of the Hermes A-3B missile were tested in the Ames supersonic free-flight wind tunnel to determine the static-longitudinal-stability characteristics at a Mach number of 5.0 and a Reynolds number based on body length of 10 million. The results indicated that the model center of pressure was 45.3 percent of the body length aft of the nose and the lift-curve slope based on body frontal area was 0.064 per degree. Estimates indicated that the effect on these characteristics of aeroelastic twisting of the model fins was small but important if a precise location of center of pressure is required. A comparison of the test results with predictions based on available theory showed that the theory was useful only for rough estimates, The drag coefficient at zero lift, based on body frontal area, was found to be 0.155.
Date: March 10, 1952
Creator: Canning, Thomas N. & Denardo, Billy Pat
Partner: UNT Libraries Government Documents Department

Investigation of lift and center of pressure of low-aspect-ratio, cruciform, triangular, and rectangular wings in combination with a slender fuselage at high supersonic speeds

Description: Report presenting tests to evaluate the usefulness of available theory for the calculation of lift-curve slope and center of pressure of low-aspect-ratio, triangular, and rectangular cruciform wings in combination with a long slender body. Tests were made over a range of Mach and Reynolds numbers based on model length.
Date: June 26, 1952
Creator: Canning, Thomas N. & Denardo, Billy Pat
Partner: UNT Libraries Government Documents Department

Investigation of downwash and wake characteristics at a Mach number of 1.53 2: triangular wing

Description: Report presenting the results of an experimental investigation of the downwash and wake characteristics behind a triangular plan-form wing in a supersonic stream. Measurements were made of the variation of downwash angle with angle of attack at several positions within the induced flow field. Results regarding the spanwise variation of the induced stream angle, rate of change of downwash at zero lift, variation of downwash with angle of attack, and wake are provided.
Date: June 6, 1949
Creator: Perkins, Edward W. & Canning, Thomas N.
Partner: UNT Libraries Government Documents Department

Investigation of downwash and wake characteristics at a Mach number of 1.53 1: rectangular wing

Description: The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made.
Date: March 1, 1949
Creator: Perkins, Edward W. & Canning, Thomas N.
Partner: UNT Libraries Government Documents Department

Investigation of downwash and wake characteristics at a Mach number of 1.53 3: swept wings

Description: Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.
Date: February 23, 1950
Creator: Perkins, Edward W. & Canning, Thomas N.
Partner: UNT Libraries Government Documents Department

Some experiments at high supersonic speeds on the aerodynamic and boundary-layer transition characteristics of high-drag bodies of revolution

Description: Report presenting measurements made at Mach numbers of 4.0 and 8.3 of the drag, static stability, damping in pitch, and boundary-layer transition characteristics of several high-drag bodies of revolution that might be used for high-speed entry into the earth's atmosphere. The static stability was found to be high with centers of pressure as far aft as 91 percent of the length from the nose. Results regarding the force and moment data, boundary-layer transition, a comparison of roughness height to boundary-layer thickness, other causes of boundary-layer instability, and Reynolds numbers for high-speed entry into the Earth's atmosphere are provided.
Date: January 14, 1957
Creator: Seiff, Alvin; Sommer, Simon C. & Canning, Thomas N.
Partner: UNT Libraries Government Documents Department

Investigation of boundary-layer transition on flat-faced bodies of revolution at high supersonic speeds

Description: An experimental investigation was carried out to determine the boundary-layer transition characteristics of bodies of revolution with flat and nearly flat faces. Shadowgraphs indicated that the boundary layer remained laminar on the front faces and was turbulent only on the sides. The tests also yielded information on the total drag coefficients and static longitudinal stability of the models.
Date: June 7, 1957
Creator: Canning, Thomas N. & Sommer, Simon C.
Partner: UNT Libraries Government Documents Department

The Ames supersonic free-flight wind tunnel

Description: From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Partner: UNT Libraries Government Documents Department

The Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the Ames supersonic free-flight wind tunnel, which is a new piece of equipment for aerodynamic research at high supersonic Mach numbers. It has a wide Mach number range extending from low supersonic speeds to Mach numbers in excess of 10. The air stream in the tunnel is imperfect, mainly due to a symmetrical pair of oblique shock waves which reflect down the test section.
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Partner: UNT Libraries Government Documents Department