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Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil With Partical-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the st… more
Date: March 15, 1954
Creator: von Glahn, Uwe H. & Gray, Vernon H.
Item Type: Refine your search to only Report
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NACA Investigations of Icing-Protection Systems for Turbojet-Engine Installations

Description: "Investigations have been made in flight and in wind tunnels to determine which components of turbojet installations are most critical in icing conditions, and to evaluate several methods of icing protection. From these studies, the requirements necessary for adequate icing protection and the consequent penalties on engine performance can be estimated. Because investigations have indicated that the compressor-inlet screen constitutes the greatest icing hazard and is difficult to protect, comple… more
Date: May 2, 1951
Creator: von Glahn, Uwe; Callaghan, Edmund E. & Gray, Vernon H.
Item Type: Refine your search to only Report
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An Experimental Investigation of Two-Dimensional, Supersonic Cascade-Type Inlets at a Mach Number of 3.11

Description: Memorandum presenting an investigation of two-dimensional, supersonic cascade-type inlets at a free-stream Mach number of 3.11. Two cascade-type inlets utilizing different methods of internal-flow compression were designed and tested. Results regarding the cascade inlet and stepped-cascade inlet are provided.
Date: August 25, 1954
Creator: Óffenhartz, Edward
Item Type: Refine your search to only Report
open access

Flight Experience With Two High-Speed Airplanes Having Violent Lateral-Longitudinal Coupling in Aileron Rolls

Description: "During flight tests of two high-speed airplane configurations, violent cross-coupled lateral and longitudinal motions were encountered following abrupt rudder-fixed aileron rolls. The speeds involved ranged from a Mach number of 0.7 to 1.05. The motions were characterized by extreme variations in angles of attack and sideslip which resulted in load factors as large as 6.7g (negative) and 7g (positive) normal acceleration and 2g transverse acceleration" (p. 1).
Date: February 4, 1955
Item Type: Refine your search to only Report
open access

A Survey and Evaluation of Flutter Research and Engineering

Description: Memorandum presenting a survey and evaluation of flutter research and flutter engineering, with particular emphasis placed on the design of primary fixed surfaces and primary controls. Analyses are made of recent flutter occurrences to delineate past and future problems, and detailed appraisals are given of the status of the various engineering branches involved in the analytical and experimental prediction of flutter.
Date: October 5, 1956
Item Type: Refine your search to only Report
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