National Advisory Committee for Aeronautics (NACA) - 10 Matching Results

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Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Vee Tail

Description: "An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-ft free-spinning tunnel. Results of tests with a conventional tail have been previously reported; the results presented herein are for the model with a vee tail installed. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model. In the normal loading were determined" (p. 1).
Date: November 28, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Variations in Forebody and Afterbody Dead Rise on the Resistance and Spray Characteristics of the 22ADR Class VPB Airplane: Langley Tank Model 207, TED No. NACA 2361

Description: From Summary: "An investigation was made to determine the effects of changes in the amount and distribution of forebody and afterbody dead rise on the hydrodynamic resistance and spray characteristics of a 1/11-size model of the Bureau of Aeronautics design No. 22ADR class VPB airplane. The variations in dead rise within the range investigated had no significant effects on resistance or trim, free to trim, or on resistance or trimming moment, fixed in trim. The coordinates of the peaks of the b… more
Date: August 28, 1947
Creator: Clement, Eugene P. & Daniels, Charles J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Torsional Stiffness Criterion for Preventing Flutter of Wings of Supersonic Missiles

Description: "A formula, based on a semirational analysis, is presented for estimating the torsional stiffness necessary to prevent flutter of a sweptback or unswept uniform wing that attains supersonic speeds. Results of missile flights at speeds up to Mach number 1.4 demonstrate the usefulness of the formula" (p. 1).
Date: August 28, 1947
Creator: Budiansky, Bernard; Kotanchik, Joseph N. & Chiarito, Patrick T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85

Description: An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations.
Date: April 28, 1947
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnels to develop optimum double-slotted-flap configurations for seven thin NACA airfoil sections. Each was equipped with the same flaps and measured at the same Reynolds numbers. Results regarding the lift characteristics and pitching moment are provided.
Date: April 28, 1947
Creator: Cahill, Jones F. & Racisz, Stanley F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Description: From Summary: "A study has been made of the performance of the induction and the exhaust systems on the XR60 power-plant installation as part of an investigation conducted in the Cleveland altitude wind tunnel. Altitude flight conditions from 5000 to 30,000 feet were simulated for a range of engine powers from 750 to 3000 brake horsepower."
Date: March 28, 1947
Creator: Dupree, David T. & Hawkins, W. Kent
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Swept-Back Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.
Date: March 28, 1947
Creator: Zalovcik, John A. & Sawyer, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of the Full-Floating Journal Bearing

Description: "An analysis of the operating characteristics of a full-floating bearing - a bearing in which a floating sleeve is located between the journal and bearing surfaces - is presented together with charts - from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing to verify some results of the analysis are reported. The floating sleeve can operate over a w… more
Date: January 28, 1947
Creator: Shaw, M. C. & Nussdorfer, T. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Analysis and Bench Tests of a Control-Surface Booster Employing a Variable Displacement Hydraulic Pump

Description: From Summary: "The NACA is conducting a general investigation of servo-mechanisms for use in powering aircraft control surfaces. This paper presents a theoretical analysis and the results of bench tests of a control-booster system which employs a variable displacement hydraulic pump. The booster is intended for use in a flight investigation to determine the effects of various booster parameters on the handling qualities of airplanes. Such a flight investigation would aid in formulating specific… more
Date: January 28, 1947
Creator: Mathews, Charles W. & Kleckner, Harold F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical investigation of thrust augmentation of turbojet engines by tail-pipe burning

Description: Report presenting a theoretical analysis of thrust augment of turbojet engines by tail-pipe burning and charts from which the thrust augmentation produced may be evaluated from the normal engine data and performance of the tail-pipe burner. Results regarding general curves and illustrative curves are provided.
Date: January 28, 1947
Creator: Bohanon, H. R. & Wilcox, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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