15 Matching Results

Search Results

Results: 1 - 15
open access

A Study of Skin Temperatures of Conical Bodies in Supersonic Flight

Description: Memorandum presenting a comparison between the time history of skin temperature measured on the nose of a V-2 and the temperature computed using Eber's experimental relation for heat-transfer coefficients for conical bodies under supersonic conditions. A general method developed for making skin-temperature calculations is used to compute the variation of skin temperature with time for a wide range of values of the pertinent parameters. Results regarding the validity of skin-temperature calculat… more
Date: January 29, 1948
Creator: Huston, Wilber B.; Warfield, Calvin N. & Stone, Anna Z.
Partner: UNT Libraries Government Documents Department
open access

The Effects of Fuel Sloshing on the Lateral Stability of a Free-Flying Airplane Model

Description: Memorandum presenting an investigation in the free-flight tunnel to determine the effect of the sloshing of fuel in partly filled, unbaffled tanks on the lateral stability of a free-flying model. Flight tests were made to determine the effects of the water sloshing for different depths of water and various masses and moments of inertia of the model. The sloshing caused small-amplitude, high-frequency lateral oscillations which were superimposed on the normal Dutch roll oscillation so that the l… more
Date: June 29, 1948
Creator: Smith, Charles C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speeds of the Pitching Derivatives of Untapered Swept Wings

Description: Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.
Date: September 29, 1948
Creator: MacLachlan, Robert & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Aileron Oscillations at Transonic Speeds on NACA 23012 and NACA 65-212 Airfoils by the Wing-Flow Method

Description: An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably w… more
Date: December 29, 1948
Creator: Crane, Harold L.
Partner: UNT Libraries Government Documents Department
open access

An analytical method of estimating turbine performance

Description: From Introduction: "An analytical method for estimating turbine performance from the blade angle8 and flow areas was therefore developed at the NACA Lewis laboratory and is described herein."
Date: December 29, 1948
Creator: Kochendorfer, Fred D. & Nettles, J. Cary
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Aerodynamic and Icing Characteristics of a Recessed Fuel Cell Vent Assembly 1: Rear Wall Vent Tube Mounting

Description: An investigation conducted in the icing research tunnel on a ramp type recessed fuel cell vent assembly to determine its aerodynamic, rain, and icing characteristics. Although the vent-tube openings are located in the region of maximum ramp pressure, vent-tube static pressures are marginal for a low flight speed.
Date: March 29, 1948
Creator: Ruggeri, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Loads on a Bubble-Type Canopy

Description: Report presenting the results of pressure-distribution measurements obtained in flight over the free-blown canopy of a fighter-type airplane. The measurements were compared to those of the same canopy in wind-tunnel testing to determine the degree of correlation and effects of Mach number and distortion on the pressure distribution.
Date: October 29, 1948
Creator: Matheny, Cloyce E. & Huston, Wilber B.
Partner: UNT Libraries Government Documents Department
open access

An analytical method of estimating turbine performance

Description: From Introduction: "An analytical method for estimating turbine performance from angles and flow areas was therefore developed at the NACA Lewis laboratory in 1947 and is described herein."
Date: December 29, 1948
Creator: Kochendorfer, Fred D. & Nettles, J. Cary
Partner: UNT Libraries Government Documents Department
open access

History of the reactivation of 100-B pile

Description: This report summarizes the preparations made for reactivation of the 100-B pile and the operational activities associated with the reactivation and subsequent operation up to the time of reaching desired power level. The period covered is from approximately June 1, 1948 until July 16, 1948.
Date: October 29, 1948
Creator: Filip, E. J.
Partner: UNT Libraries Government Documents Department
open access

The Radioactivity of Potassium 40: A Survey of Investigations

Description: From note: "Report discussing the history of the research of potassium 40 and its radioactivity, as well as the author's own investigations into the isotope."
Date: November 29, 1948
Creator: Weaver, B. S.
Partner: UNT Libraries Government Documents Department
open access

Aeronautical Characteristics of a Three-Blade Propeller Having NACA 10-(3)(08)-03 Blades

Description: "Data obtained in tests of a 10-foot diameter, three-blade propeller, having NACA 10-(3)(08)-03 blades, conducted in the Langley 16-foot high-speed tunnel are presented. The propeller performance quantities related by the tests are thrust, torque, efficiency, and advance ratio for various rotational speeds or stream Mach numbers with blade angle as a parameter. Advance Mach numbers varied from 0.12 to 0.64" (p. 1).
Date: October 29, 1948
Creator: Davidson, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Lateral and Directional Stability and Control Characteristics of the Grumman F8F-1 Airplane

Description: "This paper presents the results of flight tests to determine the lateral and directional stability and control characteristics of the Grumman F8F-1 airplane with three vertical-tail configurations. The data presented herein have no bearing on the performance characteristics of the airplane, which were not measured but which were considered to be exceptionally good. The conclusions reached regarding the lateral and directional stability and control characteristics are summarized in this report"… more
Date: January 29, 1948
Creator: Crane, H. L. & Reeder, J. P.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen