You limited your search to:

 Decade: 1940-1949
 Year: 1947
 Month: November
 Collection: National Advisory Committee for Aeronautics Collection
The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

Date: November 1947
Creator: Reynolds, E E; Freeman, J W & White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Date: November 6, 1947
Creator: Eggers, A J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Date: November 14, 1947
Creator: Loftin, Laurence K., Jr. & Cohen, Kenneth G.
Description: Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of effect of basic design variables on subsonic axial-flow-compressor performance

Analysis of effect of basic design variables on subsonic axial-flow-compressor performance

Date: November 26, 1947
Creator: Sinnette, John T , Jr
Description: A blade-element theory for axial-flow compressors has been developed and applied to the analysis of the effects of basic design variables such as Mach number, blade loading, and velocity distribution on compressor performance. A graphical method that is useful for approximate design calculations is presented. The relations among several efficiencies useful in compressor design are derived and discussed. The possible gains in useful operating range obtainable by the use of adjustable stator blades are discussed and a rapid approximate method of calculating blade-angle resettings is shown by an example. The relative Mach number is shown to be a dominant factor in determining the pressure ratio.
Contributing Partner: UNT Libraries Government Documents Department
Comparative performance of two vaneless diffusers designed with different rates of passage curvature for mixed-flow impellers

Comparative performance of two vaneless diffusers designed with different rates of passage curvature for mixed-flow impellers

Date: November 1, 1947
Creator: Barina, Frank J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison between flight-measured and calculated span load distribution at high Mach numbers

Comparison between flight-measured and calculated span load distribution at high Mach numbers

Date: November 26, 1947
Creator: Rolls, L Stewart
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of crystal structures of 10 wrought heat resisting alloys at elevated temperatures with their crystal structures at room temperatures

Comparison of crystal structures of 10 wrought heat resisting alloys at elevated temperatures with their crystal structures at room temperatures

Date: November 1, 1947
Creator: Kittel, J Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of three theoretical methods of calculating span load distribution on swept wings

A comparison of three theoretical methods of calculating span load distribution on swept wings

Date: November 1, 1947
Creator: Van Dorn, Nicholas H & Deyoung, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Diagonal tension in curved webs

Diagonal tension in curved webs

Date: November 1, 1947
Creator: Kuhn, Paul & Griffith, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of aspect ratio and taper on the pressure drag at supersonic speeds of unswept wings at zero lift

Effect of aspect ratio and taper on the pressure drag at supersonic speeds of unswept wings at zero lift

Date: November 1, 1947
Creator: Nielsen, Jack N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of chordwise vanes on amplitude of tail buffeting

Effect of chordwise vanes on amplitude of tail buffeting

Date: November 10, 1947
Creator: Stokke, Allen R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of preheating and postheating on the quality of spot welds in aluminum alloys

The effect of preheating and postheating on the quality of spot welds in aluminum alloys

Date: November 1, 1947
Creator: Hess, W F; Wyant, R A & Winsor, F J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation to determine the hinge moments of a beveled-edge aileron on a 45 degree sweptback wing at transonic and low supersonic speeds

Flight investigation to determine the hinge moments of a beveled-edge aileron on a 45 degree sweptback wing at transonic and low supersonic speeds

Date: November 12, 1947
Creator: Gardner, William N & Curfman, Howard J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a VEE Tail

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

Date: November 28, 1947
Creator: Berman, Theodore
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. Tests of the model in the long-range loading also were made. The investigation included leading-edge-flap, spin-recovery-parachute, and rudder-pedal-force tests. The recovery characteristics of the model were satisfactory for the normal loading. Deflecting the leading-edge flaps improved recoveries. The results indicated that with the external wing tanks installed (long-range loading) recoveries may be poor and, therefore, if a spin is inadvertently entered in this condition the tanks should be jettisoned if recovery does not appear imminent immediately after it is attempted. A 10-foot spin-recovery tail parachute with a towline 40 feet long and a drag coefficient of 0.63 was found to be effective for spin recovery. The rudder pedal force required for spin recovery was indicated to be within the capabilities of the pilot.
Contributing Partner: UNT Libraries Government Documents Department
High-speed wind-tunnel investigation of high lift and aileron-control characteristics of an NACA 65-210 semi-span wing

High-speed wind-tunnel investigation of high lift and aileron-control characteristics of an NACA 65-210 semi-span wing

Date: November 1, 1947
Creator: Fischel, Jack & Schneiter, Leslie E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation at low speed of a large-scale triangular wing of aspect ratio two I : characteristics of a wing having a double-wedge airfoil section with maximum thickness at 20-percent chord

An investigation at low speed of a large-scale triangular wing of aspect ratio two I : characteristics of a wing having a double-wedge airfoil section with maximum thickness at 20-percent chord

Date: November 13, 1947
Creator: Anderson, Adrien, E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings

An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings

Date: November 13, 1947
Creator: Walling, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel

Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel

Date: November 17, 1947
Creator: Bennett, Charles V.
Description: An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impossible to obtain satisfactory lateral-flight characteristics even with the increase in height of the vertical tail because of the negative effective dihedral, low directional stability, and large-adverse yawing moments of the ailerons.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of valve-overlap scavenging over a wide range of inlet and exhaust pressures

An investigation of valve-overlap scavenging over a wide range of inlet and exhaust pressures

Date: November 1, 1947
Creator: Creagh, John W R; Hartmann, Melvin J & Arthur, W Lewis, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Low-speed characteristics in pitch of a 42 degree sweptback wing with aspect ratio 3.9 and circular-arc airfoil sections

Low-speed characteristics in pitch of a 42 degree sweptback wing with aspect ratio 3.9 and circular-arc airfoil sections

Date: November 13, 1947
Creator: Neely, Robert H & Koven, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing Conditions

A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing Conditions

Date: November 1, 1947
Creator: Jones, Alun R; Holdaway, George H & Steinmetz, Charles P
Description: An equation is presented for calculating the heat flow required from the surface of an internally heated windshield in order to prevent the formation of ice accretions during flight in specified icing conditions. To ascertain the validity of the equation, comparison is made between calculated values of the heat required and measured values obtained for test windshields in actual flights in icing conditions. The test windshields were internally heated and provided data applicable to two common types of windshield configurations; namely the V-type and the type installed flush with the fuselage contours. These windshields were installed on a twin-engine cargo airplane and the icing flights were conducted over a large area of the United States during the winters of 1945-46 and 1946-47. In addition to the internally heated windshield investigation, some test data were obtained for a windshield ice-prevention system in which heated air was discharged into the windshield boundary layer. The general conclusions resulting from this investigation are as follows: 1) The amount of heat required for the prevention of ice accretions on both flush- and V-type windshields during flight in specified icing conditions can be calculated with a degree of accuracy suitable for design purposes. 2) A heat ...
Contributing Partner: UNT Libraries Government Documents Department
A method for calculating the heat required for windshield thermal ice prevention based on extensive flight tests in natural icing conditions

A method for calculating the heat required for windshield thermal ice prevention based on extensive flight tests in natural icing conditions

Date: November 1, 1947
Creator: Jones, A. R.; Holdaway, G. H. & Steinmetz, C. P.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method of calculating the compressive strength of Z-stiffened panels that develop local instability

A method of calculating the compressive strength of Z-stiffened panels that develop local instability

Date: November 1, 1947
Creator: Gallaher, George L & Boughan, Rolla B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Precautions for flight testing near the speed of sound

Precautions for flight testing near the speed of sound

Date: November 5, 1947
Creator: Clousing, Lawrence A
Description: From experience gained by NACA test pilots in flying at high subsonic Mach numbers and from interpretation of the data obtained, some general precautionary rules for test flying near sonic Mach numbers have been formulated. The reasons for these rules are discussed and observations are made with respect to the hazards arising from undesirable stability and control characteristics which have been noted in test flights of various airplanes. This paper, although written primarily for the attention of test pilots, contains general information of interest to those who are concerned with various phases of flight testing near sonic Mach numbers.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 NEXT LAST