UNT Libraries Government Documents Department - 19 Matching Results

Search Results

Results: 1 - 19
open access

Acceleration Measurements During Landing in Rough Water of a 1/7-Scale Dynamic Model of Grumman XJR2F-1 Amphibian - Langley Tank Model 212: TED No. NACA 2378

Description: From Summary: "Tests of a 1/7 size model of the Grumman XJR2F-1 amphibian were made in Langley tank no.1 to examine the landing behavior in rough water and to measure the normal and angular accelerations experienced by the model during these landings. All landings were made normal to the direction of wave advance, a condition assumed to produce the greatest accelerations. Wave heights of 4.4 and 8.0 inches (2.5 and 4.7 ft, full size) were used in the tests and the wave lengths were varied betwe… more
Date: May 6, 1947
Creator: Land, Norman S. & Zeck, Howard
Item Type: Refine your search to only Report
open access

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

Description: From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the convention… more
Date: November 6, 1947
Creator: Eggers, A. J., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Description: "A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in … more
Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Item Type: Refine your search to only Report
open access

Analysis of Performance of Jet Engine From Characteristics of Components 1: Aerodynamic and Matching Characteristics of Turbine Component Determined With Cold Air

Description: "The performance of the turbine component of an NACA research jet engine was investigated with cold air. The interaction and the matching of the turbine with the NACA eight-stage compressor were computed with the combination considered as a jet engine. The over-all performance of the engine was then determined. The internal aerodynamics were studied to the extent of investigating the performance of the first stator ring and its influence on the turbine performance" (p. 397).
Date: June 6, 1947
Creator: Goldstein, Arthur W.
Item Type: Refine your search to only Report
open access

Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil

Description: Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date: March 6, 1947
Creator: Thompson, Jim Rogers & Marschner, Bernard W.
Item Type: Refine your search to only Report
open access

Ditching Tests with a 1/12-Scale Model of the Army A-26 Airplane in Langley Tank No. 2 and on an Outdoor Catapult

Description: Tests were conducted in calm water in Langley tank no. 2 and in calm and rough water at an outdoor catapult in order to determine the best way to make a forced landing of an Army A-26 airplane and to determine its probable ditching behavior. These tests were requested by the Air Materiel Command, Army Air Forces, in their letter of March 26, 1943, WEL:AW:50.
Date: March 6, 1947
Creator: Jarvis, George A. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

The Effectiveness at High Speeds of a 20-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil

Description: "An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.3 to 0.875. In addition, the effectiveness of the plain flap as a lift-control device has been compared with the corresponding effectiveness of both a spoiler and a dive-recovery flap on the NACA 65-210 airfoil section. The analysis indicates that the plain trailing-edge flap employed on … more
Date: May 6, 1947
Creator: Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
open access

The Effectiveness at High Speeds of a 20-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section

Description: "An analysis has been made of the lift-control effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.3 to 0.875. In addition, the effectiveness of the plain flap as a lift-control device has been compared with the corresponding effectiveness of both a spoiler and a dive-recovery flag on the INCA 65-210 airfoil section" (p. 1).
Date: May 6, 1947
Creator: Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
open access

Experimental investigation of thrust augmentation of a turbojet engine at zero ram by means of tail-pipe burning

Description: Report presenting an investigation of the performance of a turbojet engine equipped with a tail-pipe burner at zero ram over a range of rotor speeds and tail-pipe-burner fuel flows. A thrust augmentation of 40 percent was obtained at zero ram for a tail-pipe-burner fuel-air ratio of 0.043 or a total fuel-air ratio of 0.056. Results with an engine with standard tail pipe, engine with tail pipe burner and no afterburning, and engine with tail pipe burner and afterburning are provided.
Date: January 6, 1947
Creator: Lundin, Bruce T.; Dowman, Harry W. & Gabriel, David S.
Item Type: Refine your search to only Report
open access

Free-Spinning and Tumbling Tests of a 1/16-Scale Model of the McDonnell XP-85 Airplane

Description: The teat results showed that with either of the three tail arrangements, the model usually spun in flat attitudes with oscillations about the lateral and longitudinal axes. In general, full reversal of the rudder pedals did not stop the spinning rotation. To make the model satisfactorily meet-the spin-recovery requirements it was found that installation of either a very large ventral fin (l7.9 square feet, full scale) below the tail or a somewhat smaller ventral fin and rudder (12.4 square feet… more
Date: March 6, 1947
Creator: Klinar, Walter J.
Item Type: Refine your search to only Report
open access

A fuel-distribution control for continuous-flow manifold injection on reciprocating engines

Description: "A fuel-distribution control for continuous-flow manifold injection on reciprocating engines is described. A method is installation of the control on an engine is suggested. The device controlled the flow to four spring-loaded nozzles within 2 percent of perfect distribution over a wide range of fuel-flow rates and the distribution was practically unaffected by uneven discharge-nozzle pressures" (p. 1).
Date: June 6, 1947
Creator: Gold, Harold & Straight, David M.
Item Type: Refine your search to only Report
open access

An Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression

Description: Report presenting an investigation of two sharp-edge annular inlets with conical central bodies at low airspeeds in the propeller research tunnel to obtain information concerning the surface-pressure, drag, and pressure-recovery characteristics of the inlets at subsonic flight. Results regarding the nose and inner surface of the diffuser, inlet lips, minimum surface pressures and critical Mach numbers, pressure surveys in inlets, and pressure surveys in diffusers are provided.
Date: June 6, 1947
Creator: Dennard, John S.
Item Type: Refine your search to only Report
open access

Location of Detached Shock Wave in Front of a Body Moving at Supersonic Speeds

Description: "It is shown that for velocities slightly in excess of sonic, the position of detached shock wave located in front of a given body at zero angle of attack may be estimated theoretically to a reasonable degree of accuracy. In case of bodies of revolution the result was simple, but for two-dimensional bodies, pressure coefficient varies with Mach number, and slight difficulty appears. Theory developed compares favorably with available experimental data" (p. 1).
Date: May 6, 1947
Creator: Laitone, Edmund V. & Pardee, Otway O'M.
Item Type: Refine your search to only Report
open access

Performance of Compressor of XJ-41-V Turbojet Engine 2 - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 RPM

Description: "At the request of the Air Material Command, Army Air Forces, an investigation was conducted by the NACA Cleveland laboratory to determine the performance characteristics of the compressor of the XJ-41-V turbojet engine. This report is the second in a series presenting the compressor performance and analysis of flow conditions in the compressor. The static-pressure variation in the direction of flow through the compressor and the location and the cause of the maximum flow restriction at an equi… more
Date: May 6, 1947
Creator: Dildine, Dean M. & Arthur, W. Lewis
Item Type: Refine your search to only Report
open access

Some pressure-distribution measurements on a swept-wing at transonic speeds by the NACA wing-flow method

Description: Report presenting results of chordwise pressure-distribution measurements on a 45 degree sweptback wing at transonic speeds. The two stations for measuring were located at the 18 percent chord from the root and the 87 percent chord. The changes in pressure distribution with Mach number did not indicate any appreciable net loss in section lift, but did indicate large increases in the section drag and diving moment.
Date: June 6, 1947
Creator: Johnston, J. Ford & Danforth, Edward C. B.
Item Type: Refine your search to only Report
open access

Stability derivatives of triangular wings at supersonic speeds

Description: "The analysis of the stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds, given in NACA TN no. 1423, is extended to apply to triangular wings having large vertex angles and traveling at supersonic speeds. The lift, rolling moment due to sideslip, and damping in roll and pitch for this more general case have been treated elsewhere on the basis of the theory of small disturbances. The surface potentials for angle of attack and rolling taken therefrom are u… more
Date: November 6, 1947
Creator: Ribner, Herbert S. & Malvestuto, Frank S., Jr.
Item Type: Refine your search to only Report
open access

Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift

Description: "On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms" (p. 1).
Date: October 6, 1947
Creator: Margolis, Kenneth
Item Type: Refine your search to only Report
open access

Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378

Description: From Summary: "Additional tests of a 1/7-size model of the Grumman XJR2F-1 amphibian were made in Langley tank no. 1 to compare the behavior during take-off of the model equipped with split- and slotted-type flaps. The slotted flag had a large effect on locating the forward center-of-gravity limits for stable take-offs. Stable take-offs within the normal operating range of positions of the center of gravity could be made with the split flaps deflected 45 degrees or with the slotted flaps deflec… more
Date: February 6, 1947
Creator: Land, Norman S. & Zeck, Howard
Item Type: Refine your search to only Report
Back to Top of Screen