National Advisory Committee for Aeronautics (NACA) - 260 Matching Results

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Abnormal grain growth in S-816 alloy

Description: From Introduction: "This report presents the results obtained to date of an investigation to establish the fundamental causes of abnormal growth in S-816 alloy under conditions encountered during the forging of blades for the gas turbine of jet engines."
Date: April 1952
Creator: Rush, A I; Freeman, J W & White, A E
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Description: From Introduction: "The results of one phase of this investigation, presented in reference 1, have indicated that hull drag can be reduced without causing large changes in aerodynamic stability and hydrodynamic performance by the use of high length-beam ratios. Another phase of the investigation, reference 2, indicated that hulls of the deep-step planning-tail type have much lower air drag than the conventional type of hull and about the same aerodynamic stability; tank tests, reference 3, have indicated that this type of hull also has hydrodynamic performance equal to and in some respects superior to the conventional type of hull. Unpublished tank tests have indicated that the hull models presented in the present paper (with the possible exception of the forebody alone for which data are not available) will have acceptable hydrodynamic performance."
Date: June 1952
Creator: Riebe, John M & Naeseth, Rodger L
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of three deep-step planing-tail flying-boat hulls and a transverse-step hull with extended afterbody

Description: From Summary: "An investigation was made to determine the aerodynamic characteristics in the presence of a wing of three-step planning-tail flying-boat hulls which differed only in the amount of step fairing. The purpose of comparison, tests were also made of a transverse-step hull with an extended afterbody."
Date: August 1952
Creator: Riebe, John M & Naeseth, Rodger L
Partner: UNT Libraries Government Documents Department

The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

Description: From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date: June 1952
Creator: Beckwith, Ivan E; Ridyard, Herbert W & Cromer, Nancy
Partner: UNT Libraries Government Documents Department

The aerodynamic design of supersonic propellers from structural considerations

Description: From Summary: "The aerodynamic design of propellers from considerations of centrifugal force is presented. By applying a constant minimum value of thickness ratio from root to tip and allowing the distribution of required area to appear in the blade plan form, propellers with good efficiency are realized at high Mach numbers by the method of this paper."
Date: December 1952
Creator: Hammack, Jerome B
Partner: UNT Libraries Government Documents Department

Airfoil profiles for minimum pressure drag at supersonic velocities : application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness considerably greater than the theoretical optimum can result in an excessive drag penalty at moderate supersonic Mach numbers, though not at hypersonic Mach numbers."
Date: September 17, 1952
Creator: Chapman, Dean R
Partner: UNT Libraries Government Documents Department

Analogue-computer simulation of an autopilot servo system having nonlinear response characteristics

Description: From Introduction: "The servo system considered in this report is in the latter category, due mainly to the fact its amplifier tends to saturate. An investigation of the longitudinal dynamic response of the stabilized airplane was made and the results were reported in reference 1. In this investigation it was found that when restricted to linear methods of analysis the performance of the autopilot-aircraft combination could be predicted for only the small range of operation where the elements of the autopilot operated within their linear range."
Date: June 1, 1952
Creator: Jones, Arthur L & White, John S
Partner: UNT Libraries Government Documents Department

Analysis of flow in a subsonic mixed-flow impeller

Description: From Introduction: "A brief description of the method of analysis is presented herein considering the mean stream surface approach advanced in references 2 and 3, and both the incompressible and compressible solutions are given in detail."
Date: August 1952
Creator: Wu, Chung-Hua; Brown, Curtis A & Costilow, Eleanor L
Partner: UNT Libraries Government Documents Department

An analysis of laminar free-convection flow and heat transfer about a flat plate parallel to the direction of the generating body force

Description: From Introduction: "The problem of free-convection flow as produced by a body force about a flat plate in the direction of the body force was studied at the NACA Lewis laboratory and is treated in a formal and more general manner herein. The method used is somewhat similar to that used in reference 4 wherein consideration was given to the free-convection flow at high Grashof numbers in a horizontal cylinder which had a variable surface-temperature distribution. In addition, the numerical solutions of references 2 and 3 are herein extended to cover a more complete range of variables."
Date: February 1, 1952
Creator: Ostrach, Simon
Partner: UNT Libraries Government Documents Department

An analysis of the errors in curve-fitting problems with an application to the calculation of stability parameters from flight data

Description: From Introduction: "It is shown in the body of this report that the solution to the error problem depends upon a more or less arbitrary definition, the only criterion as to the choice of the definition being the usefulness of the solution to which it leads. In this respect, it may be said of the method derived herein that it is not difficult to apply and appears to lead reasonable values of the errors."
Date: November 1952
Creator: Shinbrot, Marvin
Partner: UNT Libraries Government Documents Department