National Advisory Committee for Aeronautics (NACA) - 289 Matching Results

Search Results

Flight tests of the high-speed performance of a P-51B airplane (AAF no. 43-12105)

Description: Report discussing testing to check the improvement of 3 or 4 miles per hour in the maximum speed of the P-51B airplane as a result of sealing the wing-gun access doors and flap-spar lightening holes. Large variations in speed were observed during testing, so additional testing and analysis was carried out to determine the effects of various factors that were suspected of contributing to the inconsistency of the plane's performance.
Date: December 18, 1944
Creator: Voglewede, T. J. & Danforth, E. C. B.
Partner: UNT Libraries Government Documents Department

Tests of a heated low-drag airfoil

Description: Report discusses the results of an experimental investigation into the NACA 65,2-016 heated wing. Information about the effect of heating on the drag coefficients, Reynolds numbers, and stability of the laminar boundary layer.
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Partner: UNT Libraries Government Documents Department

Power-off tests of the Northrop N9M-2 tailless airplane in the 40- by 80-foot wind tunnel

Description: Report discussing tests on the N9M-2 airplane to evaluate the airplane efficiency factor and to investigate the characteristics of the aeroboost in the elevon control system. The efficiency factor compared reasonably well to conventional airplanes and the aeroboost system and valve-chatter tests were satisfactory.
Date: December 14, 1944
Creator: Stevens, Victor I., Jr. & McCormack, Gerald M.
Partner: UNT Libraries Government Documents Department

Introduction to the problem of rocket-powered aircraft performance

Description: An introduction to the problem of determining the fundamental limitations on the performance possibilities of rocket-powered aircraft is presented. Previous material on the subject is reviewed and given in condensed form along with supplementary analyses. Some of the problems discussed are: 1) limiting velocity of a rocket projectile; 2) limiting velocity of a rocket jet; 3) jet efficiency; 4) nozzle characteristics; 5) maximum attainable altitudes; 6) ranges. Formulas are presented relating the performance of a rocket-powered aircraft to basic weight and nozzle dimensional parameters. The use of these formulas is illustrated by their application to the special case of a nonlifting rocket projectile.
Date: December 1947
Creator: Ivey, H. Reese; Bowen, Edward N., Jr. & Oborny, Lester F.
Partner: UNT Libraries Government Documents Department

A method for estimating heat requirements for ice prevention gas heated hollow propeller blades

Description: Report presenting a method for determining the temperature and flow of heated gas necessary for ice prevention of hollow propeller blades in flight and icing conditions. A variety of conditions are taken into consideration and suggested simplifications and short methods are provided in order to not overcomplicate the design modifications.
Date: December 1947
Creator: Gray, V. H. & Campbell, R. G.
Partner: UNT Libraries Government Documents Department

Stability and control characteristics at low speed of an airplane model having a 38.7 degree sweptback wing with aspect ratio 4.51, taper ratio 0.54, and conventional tail surfaces

Description: Report presenting a low-speed wind-tunnel investigation of a scale model of an airplane with a 38.7 degree sweptback wing with an aspect ratio of 4.51, a taper ratio of 0.54, and conventional tail surfaces. Results regarding the lift characteristics, longitudinal stability, longitudinal control, directional stability, lateral control, and directional control are provided.
Date: December 1948
Creator: Lockwood, Vernard E. & Watson, James M.
Partner: UNT Libraries Government Documents Department

The flexible rectangular wing in roll at supersonic flight speeds

Description: From Summary: "The problem of the loss in rolling effectiveness at supersonic flight speeds is considered for the case of the rectangular wing. Equations are obtained from which can be calculated either the loss in rate of roll due to flexibility or the torsional stiffness required to maintain a given rate of roll, for two assumed variations of the spanwise distribution of torsional stiffness. A computation form and figures are provided so that calculations can be made without reference to the details of the analysis."
Date: December 1948
Creator: Tucker, Warren A. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of effects of tail length on the longitudinal and lateral stability characteristics of a single-propeller airplane model

Description: Report presenting an investigation of a powered model of a single-propeller low-wing airplane with three values of tail length and three horizontal tails to determine the effects of tail length and tail volume on the longitudinal and lateral stability.
Date: December 1948
Creator: Johnson, Harold S.
Partner: UNT Libraries Government Documents Department

Hydrodynamic impact loads in rough water for a prismatic float having an angle of dead rise of 30 degrees

Description: Report presenting an investigation in the impact basin to determine the hydrodynamic impact loads in rough water for a prismatic-float forebody with an angle of dead rise of 30 degrees. Testing occurred at fixed trim and each impact occurred into a 2-foot-high wave at 60, 45, or 30 feet in length. Results regarding the calculation of rough-water loads and comparison with smooth-water conditions are provided.
Date: December 1948
Creator: Miller, Robert W.
Partner: UNT Libraries Government Documents Department

Determination of plate compressive strengths

Description: From Summary: "Results of local-instability tests of H-, Z-, and C-section plate assemblies of four extruded aluminum alloys and two magnesium alloys, obtained in an extensive investigation to determine plate compressive strengths of aircraft structural materials, are summarized. On the basis of the general relationships found between the plate compressive strengths and the compressive stress-strain curves, methods applicable to flat plates and based upon the use of the compressive stress-strain curve are suggested for determining the critical compressive stress and the average stress at maximum load."
Date: December 1947
Creator: Heimerl, George J.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)

Description: Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Date: December 1949
Creator: Schaefer, Raymond F. & Smith, Hamilton A.
Partner: UNT Libraries Government Documents Department

Analysis of means of improving the uncontrolled lateral motions of personal airplanes

Description: From Summary: "The purpose of this investigation was to determine whether such airplanes could be made to fly uncontrolled for an indefinite period of time without getting into dangerous attitudes and for a reasonable period of time (one to three minutes) without deviating excessively from their original course. The results of this analysis indicated that the uncontrolled motions of a personal airplane could be made safe as regards spiral tendencies and could be greatly improved as regards maintenance of course without resort to an autopilot."
Date: December 1949
Creator: McKinney, Marion O., Jr.
Partner: UNT Libraries Government Documents Department

Experimental investigation of flutter of a propeller with Clark Y section operating at zero forward velocity at positive and negative blade-angle settings

Description: Report presenting an investigation of the flutter of a small one-blade wooden propeller with a Clark Y section. The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment, with flutter speed increasing in this region with decreasing pressure.
Date: December 1949
Creator: Baker, John E. & Paulnock, Russell S.
Partner: UNT Libraries Government Documents Department

Control considerations for optimum power proportionment in turbine-propeller engines

Description: Report presenting an analysis of a turbine-propeller engine operating at constant speed in order to provide information regarding factors influencing optimum proportionment of power between propeller and jet, improvement in engine performance attainable from controlled proportionment of power, and control relations for optimum proportionment of power.
Date: December 1948
Creator: Heidmann, Marcus F. & Novik, David
Partner: UNT Libraries Government Documents Department

The effects of variations in Reynolds number between 3.0 x 10 to the power 6 and 25.0 x 10 to the power 6 upon the aerodynamic characteristics of a number of NACA 6-series airfoil sections

Description: The results of an investigation to determine the two-dimensional lift and drag characteristics of nine NACA 6-series airfoil sections at three different Reynolds numbers and a comparison with a different report. The airfoils selected represent sections with variations in thickness, thickness form, and camber.
Date: December 1948
Creator: Loftin, Laurence K., Jr. & Bursnall, William J.
Partner: UNT Libraries Government Documents Department

Flight tests of an apparatus for varying dihedral effect in flight

Description: Report presenting a new apparatus for varying the effective dihedral in flight by means of servo actuation of the ailerons in response to sideslip angle. Results regarding the characteristics of the effective-dihedral control in steady sideslips, in abrupt rudder kicks, and in lateral oscillations are provided.
Date: December 1948
Creator: Kauffman, William M.; Smith, Allan; Liddell, Charles J., Jr. & Cooper, George E.
Partner: UNT Libraries Government Documents Department

Charts for the conical part of the downwash field of swept wings at supersonic speeds

Description: Report presenting analytical expressions derived from the downwash throughout the entire induced flow field of lifting triangles of infinite chord with the leading edges forward or behind the Mach cone. Results regarding the downwash charts, variation of downwash distribution with leading-edge sweep angle, and additional factors affecting the downwash are provided.
Date: December 1948
Creator: Nielsen, Jack N. & Perkins, Edward W.
Partner: UNT Libraries Government Documents Department

The calculation of the heat required for wing thermal ice prevention in specified icing conditions

Description: Flight tests were made in natural icing conditions with two 8-ft-chord heated airfoils of different sections. Measurements of meteorological variables conducive to ice formation were made simultaneously with the procurement of airfoil thermal data. The extent of knowledge on the meteorology of icing, the impingement of water drops on airfoil surfaces, and the processes of heat transfer and evaporation from a wetted airfoil surface have been increased to a point where the design of heated wings on a fundamental, wet-air basis now can be undertaken with reasonable certainty.
Date: December 1947
Creator: Bergrun, Norman R.; Jukoff, David; Schlaff, Bernard A. & Neel, Carr B., Jr.
Partner: UNT Libraries Government Documents Department