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 Decade: 1940-1949
 Year: 1947
 Month: December
 Collection: National Advisory Committee for Aeronautics Collection
Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds

Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds

Date: December 1947
Creator: Ellerbrock, Herman H.; Wcislo, Chester R. & Dexter, Howard E.
Description: Investigations were made to develop a simplified method for designing exhaust-pipe shrouds to provide desired or maximum cooling of exhaust installations. Analysis of heat exchange and pressure drop of an adequate exhaust-pipe shroud system requires equations for predicting design temperatures and pressure drop on cooling air side of system. Present experiments derive such equations for usual straight annular exhaust-pipe shroud systems for both parallel flow and counter flow. Equations and methods presented are believed to be applicable under certain conditions to the design of shrouds for tail pipes of jet engines.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of the heat required for wing thermal ice prevention in specified icing conditions

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

Date: December 1, 1947
Creator: Neel, C. B., Jr.; Bergrun, N. R.; Jukoff, D. & Schlaff, B. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Calculation of the Heat Required for Wing Thermal Ice Prevention in Specified Icing Conditions

The Calculation of the Heat Required for Wing Thermal Ice Prevention in Specified Icing Conditions

Date: December 1, 1947
Creator: Bergrun, Norman R.; Jukoff, David; Schlaff, Bernard A. & Neel, Carr B., Jr.
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.
Contributing Partner: UNT Libraries Government Documents Department
Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up

Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up

Date: December 11, 1947
Creator: Boshar, John
Description: A preliminary analytical investigation was made to determine the feasibility of the basic idea of controlled failure points as safety valves for the primary airplane structure. The present analysis considers the possibilities of the breakable wing tip which, in failing as a weak link, would relieve the bending moments on the wing structure. The analysis was carried out by computing the time histories of the wing and stabilizer angle of attack in a 10g pull-up for an XF8F airplane with tips fixed and comparing the results with those for the same maneuver, that is, elevator motion but with tips jettisoned at 8g. The calculations indicate that the increased stability accompanying the loss of the wing tips reduces the bending moment an additional amount above that which would be expected from the initial loss in lift and the inboard shift in load. The vortex shed when the tips are lost may induce a transient load requiring that the tail be made stronger than otherwise.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Date: December 8, 1947
Creator: Mathews, Charles W & Thompson, Jim Rogers
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections

A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections

Date: December 11, 1947
Creator: Turner, Howard L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Data Obtained in the Flight Measurements to Determine the Stability and Control Characteristics of a C-54D Airplane (AAF No. 42-72713) and a Summary of the Test Program

Data Obtained in the Flight Measurements to Determine the Stability and Control Characteristics of a C-54D Airplane (AAF No. 42-72713) and a Summary of the Test Program

Date: December 29, 1947
Creator: Talmage, Donald B. & Reeder, John P.
Description: The flight investigation of the C-54D airplane was initiated to determine the necessity of changes or additions to existing handling-qualities requirements to cove the case of instrument approaches with large airplanes. This paper gives a brief synopsis of the results and presents the measured data of tests to determine the stability and control characteristics. It was found that no new requirements were necessary to cover the problems of instrument approaches. The C-54D airplane tested met the Amy and Navy stability and control requirements except for the following items. The control-system friction with autopilot installed vas double that allowed by the requirements. The amount of friction was found to impair the controllability of the airplane in precision flying. The lateral and directional characteristics were good except that the maximum pb/2V was slightly below the minimum required, and the elevator-control forces to obtain the maximum pb/2V at low speeds were above the Army and Navy requirements. The longitudinal stability and control characteristics were good except that the elevator-control forces exceeded the limits of the Army and Navy requirements in turns and in landings. The stalling characteristics were considered good in all conditions with the stall warning in the form of tail buffeting ...
Contributing Partner: UNT Libraries Government Documents Department
Determination of plate compressive strengths

Determination of plate compressive strengths

Date: December 1, 1947
Creator: Heimerl, George J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Air-Flow Distribution and Total-Pressure Loss on Performance of One-Sixth Segment of Turbojet Combuster

Effect of Air-Flow Distribution and Total-Pressure Loss on Performance of One-Sixth Segment of Turbojet Combuster

Date: December 10, 1947
Creator: Hill, Francis U. & Mark, Herman
Description: An investigation has been conducted on a one-sixth segment of an annular turbojet combustor to determine the effects of modification in air-flow distribution and total-pressure loss on the performance of the segment. The performance features investigated during this series of determinations were the altitude operational limits and the temperature-rise efficiency. Altitude operational limits of the combustor segment, for the 19XB engine using the original combustor-basket design were approximately 38,000 feet at 17,000 rpm and 26,000 feet at 10,000 rpm. The altitude operational limits were approximately 50,000 feet at 17,000 rpm and 38,000 feet at 10,000 rpm for a combustor-basket design in which the air-passage area in the basket was redistributed so as to admit gradually no more than 20 percent of the air along the first half of the basket. In this case the total pressure loss through the combustor segment was not appreciably changed from the total-pressure loss for the original combustor basket design. Altitude operational limits of the combustor segment for the 19XB engine were above 52,000 feet at 17,000 rpm and were approximately 23,000 feet at 10,000 rpm for a combustor-basket design in which the distribution of the air-passage area in the basket was that of the ...
Contributing Partner: UNT Libraries Government Documents Department
Effect of changing manifold pressure, exhaust pressure, and valve timing on the air capacity and output of a four-stroke engine operated with inlet valves of various diameters and lifts

Effect of changing manifold pressure, exhaust pressure, and valve timing on the air capacity and output of a four-stroke engine operated with inlet valves of various diameters and lifts

Date: December 1, 1947
Creator: Livengood, James C & Eppes, James V D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Elasto-Plastic Stability of Plates

The Elasto-Plastic Stability of Plates

Date: December 1, 1947
Creator: Ilyushin, A. A.
Description: This article explains results developed from the following research: 'The Stability of Plates and Shells beyond the Elastic Limit.' A significant improvement is found in the derivation of the relations between the stress factors and the strains resulting from the instability of plates and shells. In a strict analysis, the problem reduces to the solution of two simultaneous nonlinear partial differential equations of the fourth order in the deflection and stress function, and in the approximate analysis to a single linear equation of the Bryan type. Solutions are given for the special cases of a rectangular plate buckling into a cylindrical form, and of an arbitrarily shaped plate under uniform compression. These solutions indicate that the accuracy obtained by the approximate method is satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 12, 1947 to July 18, 1947 at Clinton County Army Air Field, Ohio

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 12, 1947 to July 18, 1947 at Clinton County Army Air Field, Ohio

Date: December 8, 1947
Creator: Funk, Jack
Description: The gust and draft velocities from records of NACA instruments installed in P-61c airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from July 12, to July 18, 1947 are presented.
Contributing Partner: UNT Libraries Government Documents Department
Experimental Investigation of a Preloaded Spring-Tab Flutter Model

Experimental Investigation of a Preloaded Spring-Tab Flutter Model

Date: December 15, 1947
Creator: Smith, N H; Clevenson, S A & Barmby, J G
Description: An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one. Frequency of the tab was the most significant parameter in this study, and an increase in flutter speed with increasing frequency is indicated. At a given frequency, the tab of high aspect ratio is shown to have a slightly lower flutter speed than the one of low aspect ratio. Because the frequency of the preloaded spring tab was found to vary radically with amplitude, the flutter speed decreased with increase in initial displacement of the tab.
Contributing Partner: UNT Libraries Government Documents Department
An experimental investigation of NACA submerged air inlets on a 1/5-scale model of a fighter airplane

An experimental investigation of NACA submerged air inlets on a 1/5-scale model of a fighter airplane

Date: December 5, 1947
Creator: Gault, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099) - Stalling Characteristics

Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099) - Stalling Characteristics

Date: December 4, 1947
Creator: Anderson, Seth B. & Cooper, George E.
Description: This report contains the flight-test results of the stalling characteristics measured during the flying-qualities investigation of the Lockheed P-8OA airplane (Army No. 44-85099). The tests were conducted in straight and turning flight with and without wing-tip tanks. These tests showed satisfactory stalling characteristics and adequate stall warning for all configurations and conditions tested.
Contributing Partner: UNT Libraries Government Documents Department
Flight Tests of Rocket-Powered "Tin-Can" Models of AAF Project MX-800

Flight Tests of Rocket-Powered "Tin-Can" Models of AAF Project MX-800

Date: December 1, 1947
Creator: Purser, Paul E. & Stone, David G.
Description: Flight tests were made of six noninstrumented rocket-powered "Tin Can" models of AAF Project MX-800. Velocity and drag data were obtained by use of CU Doppler radar. The existence of stability and adequate structural strength for flight near zero lift was checked by visual and photographic observation. Drag data obtained during the tests agreed reasonably well with estimates based on experimental data from NACA RM-2 rocket-powered drag research models.
Contributing Partner: UNT Libraries Government Documents Department
Fundamental Aerodynamic Investigations for Development of Arrow-Stabilized Projectiles

Fundamental Aerodynamic Investigations for Development of Arrow-Stabilized Projectiles

Date: December 1, 1947
Creator: Kurzweg, Hermann
Description: The numerous patent applications on arrow-stabilized projectiles indicate that the idea of projectiles without spin is not new, but has appeared in various proposals throughout the last decades. As far as projectiles for subsonic speeds are concerned, suitable shapes have been developed for sometime, for example, numerous grenades. Most of the patent applications, though, are not practicable particularly for projectiles with supersonic speed. This is because the inventor usually does not have any knowledge of aerodynamic flow around the projectile nor any particular understanding of the practical solution. The lack of wind tunnels for the development of projectiles made it necessary to use firing tests for development. These are obviously extremely tedious or expensive and lead almost always to failures. The often expressed opinion that arrow-stabilized projectiles cannot fly supersonically can be traced to this condition. That this is not the case has been shown for the first time by Roechling on long projectiles with foldable fins. Since no aerodynamic investigations were made for the development of these projectiles, only tedious series of firing tests with systematic variation of the fins could lead to satisfactory results. These particular projectiles though have a disadvantage which lies in the nature cf foldable ...
Contributing Partner: UNT Libraries Government Documents Department
Further investigation of preheating and postheating in spot-welding 0.040-inch Alclad 24S-T

Further investigation of preheating and postheating in spot-welding 0.040-inch Alclad 24S-T

Date: December 1, 1947
Creator: Hess, W F & Winsor, F J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed aerodynamic characteristics of four thin NACA 63-series airfoils

High-speed aerodynamic characteristics of four thin NACA 63-series airfoils

Date: December 31, 1947
Creator: Ilk, Richard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep

High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep

Date: December 19, 1947
Creator: Luoma, Arvo A.; Bielat, Ralph P. & Whitcomb, Richard T.
Description: A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression shock and extended to higher Mach numbers the speeds at which such changes occurred.
Contributing Partner: UNT Libraries Government Documents Department
Instability of outstanding flanges simply supported at one edge   and reinforced by bulbs at other edge

Instability of outstanding flanges simply supported at one edge and reinforced by bulbs at other edge

Date: December 1, 1947
Creator: Goodman, Stanley & Boyd, Evelyn
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Introduction to the problem of rocket-powered aircraft performance

Introduction to the problem of rocket-powered aircraft performance

Date: December 1, 1947
Creator: Ivey, H Reese; Bowen, Edward N JR & Oborny, Lester F
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.
Contributing Partner: UNT Libraries Government Documents Department
An investigation at low speed of a large-scale triangular wing of aspect ratio two II : the effect of airfoil section modifications and the determination of the wake downwash

An investigation at low speed of a large-scale triangular wing of aspect ratio two II : the effect of airfoil section modifications and the determination of the wake downwash

Date: December 10, 1947
Creator: Anderson, Adrien E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Date: December 19, 1947
Creator: Conner, D. William & Foster, Gerald V.
Description: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Contributing Partner: UNT Libraries Government Documents Department
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