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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 1, 1947
Creator: Ellerbrock, Herman H.
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.
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.
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
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.
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.
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
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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