National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

Search Results

prev Results: 13393 - 13416 next
open access

Flight Investigation of Effects of Retreating-Blade Stall on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade

Description: Note presenting flight tests conducted with a medium-size single-rotor helicopter, one blade of which was equipped with strain gages, to determine the effects of retreating-blade stall on the rotor blade bending and torsional moments during high-speed flight and pull-up maneuvers. The results indicate that retreating-blade stall has a substantial effect on the periodic rotor blade moments. Results regarding the effect of stall in steady forward flight and effect of stall in pull-up maneuvers ar… more
Date: May 1958
Creator: Ludi, LeRoy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

General solutions for flow past slender cambered wings with swept trailing edges and calculation of additional loading due to control surfaces

Description: Report presenting the use of the slender-wing-type analysis to obtain general expressions for the surface pressure, lift, and rolling moment for cambered wings with swept trailing edges. The results are specialized to give the additional loading due to the deflection of trailing-edge control surfaces and the loading due to a particular type of wing twist. A numerical example for aileron control is included.
Date: May 1958
Creator: Klunker, E. B. & Harder, Keith C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement of the Effect of an Axial Magnetic Field on the Reynolds Number of Transition in Mercury Flowing Through a Glass Tube

Description: Note presenting experiments conducted to determine the effect of a strong axial magnetic field on the flow of mercury through a circular channel. The magnetic induction was 15,000 gauss, and the channel was a pyrex tube 17-1/4 inches long and 0.027 inch inside diameter. The results indicated that the stabilizing effect occurred only at Reynolds number above 5,000, so that the region of practical applicability seems to be at fairly high Reynolds numbers and when there are only slight disturbance… more
Date: May 1958
Creator: Bader, Michel & Carlson, William C. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A performance analysis of methods for handling excess inlet flow at supersonic speeds

Description: Report presenting a comparison of several methods for handling excess inlet flow for the Mach number range from 1.5 to 4.0. The following techniques were examined and evaluated: normal- and oblique-shock spillage, bypassing through an auxiliary exit, bypassing to an ejector exhaust nozzle, and bypassing the excess flow through an auxiliary ramjet engine. Charts are presented for the thrust penalties at a variety of Mach numbers.
Date: May 1958
Creator: Hearth, Donald P. & Connors, James F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Survey of Propulsion Using Chemical Energy Stored in the Upper Atmosphere

Description: Ram-jet cycles that use the chemical energy of dissociated oxygen for propulsion in the ionosphere are presented. After a review of the properties and compositions of the upper atmosphere, the external drag, recombination kinetics, and aerodynamic-heating problems of an orbiting ram jet are analyzed. The study indicates that the recombination ram jet might be useful for sustaining a satellite at an altitude of about 60 miles. Atmospheric composition and recombination-rate coefficients were too … more
Date: May 1958
Creator: Baldwin, Lionel V. & Blackshear, Perry L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Rectangular Wing of Aspect Ratio 2 Oscillating About the Midchord

Description: Report presenting some measurements of the aerodynamic forces and moments on a rectangular wing of aspect ratio 2 which oscillated about the midchord. The measurements were made at four frequencies over a range of Mach and Reynolds numbers. Results regarding the calculated values of various theories and coefficients of lift and moment are provided.
Date: May 1958
Creator: Widmayer, Edward, Jr.; Clevenson, Sherman A. & Leadbetter, Sumner A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Study of ground-reaction forces measured during landing impacts of a large airplane

Description: Report presenting the results of tests conducted on a large bomber-type airplane to determine the ground-reaction forces imposed on the main landing gear under actual landing conditions. The vertical force on the landing gear truck at which the oleopneumatic shock strut began to compress varied over a wide range. Results regarding vertical forces, drag forces, and side forces are provided.
Date: May 1958
Creator: Hall, Albert W.; Sawyer, Richard H. & McKay, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of experimental heat-transfer measurements in turbulent flow for a Mach number range from 0.87 to 5.05

Description: Report presenting heat-transfer measurements made in turbulent flow at a variety of Mach and Reynolds numbers through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. The results are presented as Stanton number and recovery factor as a function of Reynolds number. Stanton number was found to decrease with an increase in Reynolds number and usually decreases with an increase in Mach number.
Date: May 1958
Creator: Brevoort, Maurice J. & Arabian, Barbara D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Moment-of-Area-Rule Modifications on the Zero-Lift Drag of Three Wing-Body Combinations

Description: Memorandum presenting an experimental investigation to determine the effect on drag of applying the moment-of-area-rule modifications to wing-body combinations with various wing plan forms. The effect of mounting air-to-air type missiles on the wing-mounted bodies of revolution which are part of the moment-of-area-rule modification was also investigated.
Date: May 2, 1958
Creator: Dickey, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives

Description: Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date: May 2, 1958
Creator: Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of modifications to a control surface on a 6-percent-thick unswept wing on the transonic control-surface flutter derivatives

Description: Report presenting a determination of transonic flutter characteristics from pressure cell measurements on control surfaces sinusoidally oscillated at an amplitude of plus or minus 1.08 degrees at frequencies from 5 to 30 cycles per second. Various control-surface configurations were investigated, including internal and external aerodynamic balance, vortex generators, a splitter-plate type of control surface, and superposition of triangular shaped wedges or tetrahedra along the rear portion of t… more
Date: May 2, 1958
Creator: Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental results of an investigation of two methods of inflight thrust measurement applicable to afterburning turbojet engines with ejectors

Description: Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique a… more
Date: May 2, 1958
Creator: Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87

Description: Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date: May 2, 1958
Creator: Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87

Description: Report presenting the results of a supersonic flutter investigation of three low-aspect-ratio control surfaces, two which had all-movable controls and one with a fixed cutout. Experimental results are provided and compared to calculations using the piston theory for plan form 2. Modifications for improving the flutter of the various control surfaces are also described.
Date: May 2, 1958
Creator: Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Area-Suction Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane

Description: "A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying area-suction boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effect of boundary-layer control in the handling qualities and operation of the airplane, particularly during landing. The wind-tunnel and flight tests indicated that area suction applied to the trailing-edge flaps pro… more
Date: May 6, 1958
Creator: Cook, Woodrow L.; Anderson, Seth B. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approac… more
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Flight-Measured Carrier-Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Report presenting lift and drag characteristics in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements using flight testing. Minimum comfortable approach speeds were evaluated by four test pilots. Suggestions for achieving optimal speeds for approach under various conditions are also provided.
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone

Description: Report presenting testing of two blunt-nose models, a flat-face-cone and a hemisphere-cone, at Mach numbers up to 4.7. The main purpose was to determine information about heating rates and transition for different blunt nose shapes for long-range ballistic missiles. Information about pressure measurements and heat transfer is provided.
Date: May 8, 1958
Creator: Speegle, Katherine C.; Chauvin, Leo T. & Heberlig, Jack C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of an All-Moveable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: "Results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane are presented herein. Tests at a Mach number of 6.86 were made on the scaled model and on several other configurations having lower stiffness. Flexibility influence coefficients and calculated modes and frequencies for the weakest configuration are presented" (p. 1).
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Basic XJ79-GE-1 Turbojet Engine and Its Components

Description: Memorandum presenting an investigation to determine the performance of the XJ79-GE-1 turbojet engine and its components, while operating as integral parts of the engine, conducted in an altitude test chamber. Data were obtained over a range of Reynolds number indices and for various settings of the variable compressor stators and variable-area exhaust nozzle from fully open to fully closed positions. Results regarding the component performance and engine performance are provided.
Date: May 8, 1958
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Four Aluminum-Alloy Models of 20-Inch Chord and Span With 0.064-Inch-Thick Skin, 0.025-Inch-Thick Ribs and Webs, and Zero, One, Two, or Three Chordwise Ribs

Description: Report presenting testing of four multiweb wing models were tested at Mach number 2 in a free jet to investigate structural effects of aerodynamic heating and loading. All of the models were the same except for the number of chordwise internal stiffening ribs; each had zero, one, two, or three. Results regarding laboratory vibration tests, jet tests, model behavior, temperatures, stresses, and discussion of failure are provided.
Date: May 8, 1958
Creator: Davidson, John R.; Rosecrans, Richard & Vosteen, Louis F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control

Description: Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date: May 12, 1958
Creator: Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control

Description: Memorandum presenting an acceleration-limiting control used on a turbojet engine to study the feasibility of its use as an acceleration control. A proportional-plus-integral type of controller was used in this investigation. Results regarding one-loop control and two-loop control are provided.
Date: May 12, 1958
Creator: Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen