T. N. Canning
YOU?
Author Swipe
View article: A research study for the preliminary definition of an aerophysics free-flight laboratory facility
A research study for the preliminary definition of an aerophysics free-flight laboratory facility Open
A renewed interest in hypervelocity vehicles requires an increase in the knowledge of aerodynamic phenomena. Tests conducted with ground-based facilities can be used both to better understand the physics of hypervelocity flight, and to cal…
View article: Bimetallic devices for stirring fluids
Bimetallic devices for stirring fluids Open
Device consists of helical heating coil inside cylinder and affixed at one end. Piston is fastened at other end and is free to move axially through cylinder. Electrical power extends coil when applied to conductors. Bimetallic stirrer may …
View article: Convective and radiative heat transfer during reentry and advanced techniques for their simulation.
Convective and radiative heat transfer during reentry and advanced techniques for their simulation. Open
Convective and radiative heat transfer simulation, describing use of shock tubes and ballistic ranges and combinations thereof
View article: Investigation of Boundary-layer Transition on Flat-faced Bodies of Revolution at High Supersonic Speeds
Investigation of Boundary-layer Transition on Flat-faced Bodies of Revolution at High Supersonic Speeds Open
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 …
View article: Drag and Rolling-moment Effectiveness of Trailing-edge Spoilers at Mach Numbers 2.2 and 5.0
Drag and Rolling-moment Effectiveness of Trailing-edge Spoilers at Mach Numbers 2.2 and 5.0 Open
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 def…
View article: A simple mechanical analogue for studying the dynamic stability of aircraft having nonlinear moment characteristics
A simple mechanical analogue for studying the dynamic stability of aircraft having nonlinear moment characteristics Open
"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 …
View article: 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
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 Open
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.…
View article: The Ames supersonic free-flight wind tunnel
The Ames supersonic free-flight wind tunnel Open
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 u…
View article: 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
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 Open
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. T…
View article: Investigation of downwash and wake characteristics at a Mach number of 1.53 III : swept wings
Investigation of downwash and wake characteristics at a Mach number of 1.53 III : swept wings Open
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 lif…