National Advisory Committee for Aeronautics (NACA) - 221 Matching Results

Search Results

Aerodynamic characteristics of damping screens

Description: From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date: January 1950
Creator: Schubauer, G B; Spangenberg, W G & Klebanoff, P S
Partner: UNT Libraries Government Documents Department

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Description: From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date: October 1950
Creator: Turner, M J & Rabinowitz, S
Partner: UNT Libraries Government Documents Department

The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Description: From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date: September 1950
Creator: Stone, Ralph W , Jr; Burk, Sanger M , Jr & Bihrle, William, Jr
Partner: UNT Libraries Government Documents Department

Analysis for control application of dynamic characteristics of turbojet engine with tail-pipe burning

Description: From Introduction: "The first basic problem that must be solved before control synthesis can proceed is that of determining the dynamic characteristics of the engine. Accordingly, an analysis of the dynamic behavior of the turbojet engine with tail-pipe burning was made at the NACA Lewis laboratory and is presented herein."
Date: September 1, 1950
Creator: Feder, Melvin S. & Hood, Richard
Partner: UNT Libraries Government Documents Department

Analysis of an induction blowdown supersonic tunnel

Description: From Introduction: "In the present paper, general ejector equations (see reference 4 or 5) and certain assumptions with regard to flow conditions and pressure losses have been utilized to calculate the running times of induction blowdown supersonic tunnels operating in the mentioned Mach number range."
Date: April 1, 1950
Creator: Bidwell, Jerold M
Partner: UNT Libraries Government Documents Department

An analysis of base pressure at supersonic velocities and comparison with experiment

Description: From Introduction: "The primary purpose of the investigation described in the present report is to formulate a method which is of value for quantitative calculations of base pressure on airfoils and bodies without boat-tailing. Part I consists of a detailed study of the base pressure in two-dimensional and axially-symmetric inviscid flow. In part II a semi-empirical theory is formulated since the results of part I indicate that an inviscid-flow theory cannot possibly be satisfactory for quantitative calculations of a viscous flow."
Date: July 1950
Creator: Chapman, Dean R
Partner: UNT Libraries Government Documents Department

Analysis of effect of variations in primary variables on time constant and turbine-inlet-temperature overshoot of turbojet engine

Description: From Introduction: "The design of turbojet-engine control systems is intimately related to the dynamic characteristics of the engine and has advanced to the stage where theoretically correct control constants can be determined for fixed dynamic properties (references 1 and 2). The use of the thermodynamic equations presupposes that the engine processes are quansi-static. Such an assumption is shown to be valid for a turbojet engine in references 3 and 4.
Date: September 1950
Creator: Heidmann, Marcus F
Partner: UNT Libraries Government Documents Department

Analysis of factors influencing the stability characteristics of symmetrical twin-intake Air-induction systems

Description: From Introduction: "Experimental investigations of air-induction systems in which the air flows of two intakes join in a common duct have inducted that many of these systems are subject to air-flow instability at low inlet-velocity ratios. Therefore, an analysis has been made to determine a proper basis for an explanation and to provide a more quantitative explanation of the flow instability and the flow reversal. This report presents the results of this analysis."
Date: March 1950
Creator: Martin, Norman J & Holzhauser, Curt A
Partner: UNT Libraries Government Documents Department