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Induced Side Forces on Bodies of Revolution at High Angle of Attack
Linear regression techniques are used to establish a quantitative description of side forces on bodies at high incidence. A data base is assembled concerning the key side force characteristics of maximum observed side force, angle of occurrence, and minimum angle of attack at which a side force is observed. This information is examined to determine the important trends and a predictive model for side force based on the crossflow analogy is developed to suggest other important variables. A linear regression model for these quantities is developed to include only those variables which are statistically significant. Results indicate that peak side force coefficients are a function of Mach number and only weakly of Reynolds number. Nose fineness is the critical model dimension which suggests that peak side force is a product of the nose flow field. The angle at which peak side forces occur is found to be dependent on model length and Mach number, while the onset angle of attack is a function of model length only.
Interactions Between a Multicomponent Flow and a Laser Beam
A theoretical model of the interaction between a hypersonic multicomponent flow and a high-power laser beam is described. The properties of the gaseous wedge (composed of the vapor of liquid-air droplets irradiated by a laser beam) are calculated. Conditions under which a steady-state shock wave will form ahead of the gaseous wedge and serve as an effective mechanism to separate the droplets from the carrier gas are described. The concept of generating a gaseous wedge to separate particles from the carrier gas is discussed. (Modified author abstract).
Self-compensating Store Ejection
The report concerns the concept of a continuously adjustable ejector system which accounts for the aircraft flight condition and ejects a store with an initial angular rate and linear velocity that results in a safe, repeatable, predictable nearly ballistic trajectory throughout the aircraft/store carriage envelope. The concept is especially important in the supersonic regime where the aerodynamic forces in the disturbed flow field control the initial trajectory. (Modified author abstract).
Handbook of Blunt-body Aerodynamics
The report describes methods for quickly estimating the normal force and center of pressure of blunt free-fall shapes of l/d = 0.5 to 10 over a Mach number range of 0.4 to 2.5 and up to alpha = 90 degrees. Charts and equations presented in the report are from cited reference material and original sources. Methods based on slender-body theory tested on blunt shapes and modifying factors were developed where needed.
Interacting Supersonic Turbulent Boundary Layers Over a Two-dimensional Protuberance
The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author).
An Investigation of the Damping in Pitch Characteristics of a Ten Degree Cone
A series of one-degree-of-freedom dynamic wind tunnel measurements were made for a standard Supersonic Tunnel Association ten degree cone with varying bluntnesses of .25, .1, .0167, and .07. Variations of the stability coefficients with angle-of-attack, bluntness, Reynolds number, and Mach number are obtained including Mach 18 data points for which no previous data existed. An explanation of reported difference between measured dynamic stability as obtained from ballistic range and wind tunnel techniques is offered. The equations of motion, data reduction techniques and experimental methods are also developed.
Experimental Study of Forces and Moments on Circular Bodies at High Angle of Attack
Twelve different slender bodies were tested at Mach 2 and 3 in the angle of attack range of 20 and 58 degrees. Normal and yaw forces and moments were monitored. On select models vortex paths were traced using schlieren pictures. Normal forces and moments were studied using the cross flow analogy. The accuracy of this analog appears to be best when the crossflow is supersonic.
Approximate Analysis of Heat Transfer in Transpired Boundary Layers at Limiting Prandtl Numbers
A simple procedure is developed for approximate calculations of wall heat-transfer rates in transpired boundary layers. Applications of this procedure are illustrated by various examples of incompressible, laminar flows in the limits of large and small Prandtl numbers. A distinguished limit of large Prandtl number and small mass-transfer rate is easily identified, and some limiting solutions are presented for the porous-plate configuration. Calculations for the cases with small Prandtl numbers explicitly demonstrate the usefulness of the method in studying transient heat-conduction problems. The remarkable combination of accuracy and simplicity represents the principal merit of the method. (Author).
