UNT Libraries Government Documents Department - 1,037 Matching Results

Search Results

prev Results: 49 - 72 next
open access

Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings

Description: Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.
Date: August 24, 1948
Creator: Amer, Kenneth B.
Item Type: Refine your search to only Report
open access

Static longitudinal aerodynamic characteristics of a 52 degree sweptback wing of aspect ratio 2.88 at Reynolds numbers from 2,000,000 to 11,000,000

Description: Report presenting the effects of changes in Reynolds number on the longitudinal aerodynamic characteristics of a 52 degree sweptback wing with an aspect ratio of 2.88 and NACA 64(sub 1)-112 airfoil sections. The model was tested with the leading edge both smooth and rough. Results regarding force and pitching-moment results, flow observations, and discussion of force and moment characteristics are provided.
Date: November 16, 1948
Creator: Fitzpatrick, James E. & Foster, Gerald V.
Item Type: Refine your search to only Report
open access

Investigation of wing characteristics at a Mach number of 1.53 2: swept wings of taper ratio 0.5

Description: Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.
Date: June 28, 1948
Creator: Vincenti, Walter G.; Van Dyke, Milton D. & Matteson, Frederick H.
Item Type: Refine your search to only Report
open access

Performance investigation of can-type combustor 2: water injection at various stations in combustor

Description: Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.
Date: September 30, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
open access

High-Speed Wind-Tunnel Investigation of a Sweptback Wing With an Added Triangular Area at the Center

Description: Report discussing an investigation of two sweptback wings of different plan form in order to determine the effects of adding a triangular area to the inboard section of a conventional sweptback wing as a way to create a wing with two stages of sweepback. Lift, drag, and pitching-moment characteristics are provided for a range of Mach numbers.
Date: January 14, 1949
Creator: Henry, Beverly Z., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Description: Report presenting a wind-tunnel investigation of a semispan model of a wing swept back 63 degrees with an aspect ratio of 3.5 and a taper ratio of 0.25. The tests were conducted to evaluate the effects of Reynolds and Mach number on the aerodynamic characteristics of the wing. Results regarding the characteristics of the wing with the elevon undeflected, effectiveness of the elevon, effects of roughness strips, and effect of model deflection under varying loads are provided.
Date: October 11, 1948
Creator: Reynolds, Robert M. & Smith, Donald W.
Item Type: Refine your search to only Report
open access

Effect of Taper Ratio on the Low-Speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2.61

Description: Report discussing testing on a series of tapered swept wings under conditions simulating rolling flight. The lift, longitudinal-force, and pitching-moment characteristics for three swept wings are provided. The results indicated that a decrease in taper ratio on a swept wing caused a small decrease in damping in roll at low and moderate lift coefficients.
Date: November 9, 1948
Creator: Brewer, Jack D. & Fisher, Lewis R.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Low Speeds of the Pitching Derivatives of Untapered Swept Wings

Description: Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.
Date: September 29, 1948
Creator: MacLachlan, Robert & Fisher, Lewis R.
Item Type: Refine your search to only Report
open access

Performance investigation of can-type combustor 1: instrumentation, altitude operational limits and combustion efficiency

Description: Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-press… more
Date: September 16, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of Various Ailerons on a 42 Degree Sweptback Wing for Lateral Control at Transonic Speeds

Description: Report presenting an investigation at transonic speeds in the high speed tunnel to determine the rolling-effectiveness characteristics of several aileron arrangements for use on a 42 degree sweptback wing. Results regarding the rolling-moment coefficients, variation of coefficient with Mach number, outboard cusp aileron, and use of the leading-edge flaps are provided.
Date: September 7, 1948
Creator: Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D.
Item Type: Refine your search to only Report
open access

Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel 2: the effectiveness and hinge moments of a constant-chord plain flap

Description: Report presenting a semispan triangular wing with a constant-chord trailing-edge flap to evaluate the aerodynamic characteristics of the wing with landing speeds up to a Mach number of 0.95. Tests were included to ascertain the effects of the addition of a body and of modifications to the airfoil section. Results regarding the wing alone with low Mach number, wing alone with high Mach number, effect of the body, effect of the flap, effect of Mach number, lift-drag ratio, and wing-profile modifi… more
Date: September 21, 1948
Creator: Stephenson, Jack D. & Amuedo, Arthur R.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Tests of a Swept-Blade Propeller and Related Straight Blades Having Thickness Ratios of 5 and 6 Percent

Description: Report discussing the aerodynamic characteristics of three sets of blades over as wide a range of operating conditions as possible. One set of blades was conventional, one had blades that embodied sweep, and one was a nonswept set with thinner blade sections. The sweptback blades were found to be generally inferior to the straight blades, but the Mach numbers tested were not high enough to include speeds that might benefit from sweepback.
Date: November 10, 1948
Creator: Gray, W. H.
Item Type: Refine your search to only Report
open access

Investigation of Flow Conditions and the Nature of the Wall-Constriction Effect Near and at Choking by Means of the Hydraulic Analogy

Description: Report presenting an investigation of the closed wind-tunnel phenomenon of choking and the wall-constriction effects in the subsonic Mach number range where supersonic Mach numbers appear using the hydraulic analogy. Application of the results to wind tunnel testing, the subsonic choking phenomena, and effects of the walls are described.
Date: September 1, 1948
Creator: Matthews, Clarence W. & Wright, Ray H.
Item Type: Refine your search to only Report
open access

Performance of several air ejectors with conical mixing sections and small secondary flow rates

Description: An investigation of several ejector configurations to determine the ability to handle the air required for engine cooling. The results are limited to investigations of conical-type mixing-section ejectors at ratios of mixing-section minimum diameter to primary-jet-nozzle diameter using unheated air. Results regarding experimental data, generalization of experimental data, spacing for maximum weight-flow ratio, ejector thrust, ejector configurations for constant weight-flow ratio, and selection … more
Date: July 19, 1948
Creator: Huddleston, S. C.; Wilsted, H. D. & Ellis, C. W.
Item Type: Refine your search to only Report
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: D-588-1 Speed-Reduction Brake and Symmetrical-Profile Wing Characteristics

Description: Report presenting the results of pitching-moment, lift, and drag measurements on a model of the D-558-1 with speed reduction brakes and a symmetrical profile wing at a range of Mach numbers. Only a small decrement in Mach number is produced with no nose-inlet flow and the speed-reduction brakes deflected.
Date: June 15, 1948
Creator: Wright, John B.
Item Type: Refine your search to only Report
open access

Flight Tests to Determine the Drag of Fin-Stabilized Parabolic Bodies at Transonic and Supersonic Speeds

Description: Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.
Date: April 21, 1948
Creator: Alexander, Sidney R.; Chauvin, Leo T. & Rumsey, Charles B.
Item Type: Refine your search to only Report
open access

Ice protection of turbojet engines by inertia separation of water 1: alternate-duct system

Description: Aerodynamic and icing investigations of internal water-inertia separation inlets designed to prevent automatically entrance of large quantities of water into a turbojet engine in icing conditions was conducted on a one-half scale model. A simplified analytical approach to the design of internal water-inertia separation inlets is included. Results show that in order to be effective in preventing screen and guide-vane icing for an inlet of this type, a ram-pressure recovery of 75 percent was atta… more
Date: May 28, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
open access

Flight Characteristics at Low Speed of a 1/12 Scale Model of the Consolidated Vultee 7002 Airplane (Flying Mock-Up of XP-92)

Description: Contains the results of an investigation in the Langley free-flight tunnel to determine the stability and control characteristics of a 1/12-scale dynamic free-flying model of the Consolidated Vultee 7002 airplane (a flying mock-up of the XP-92 airplane). The wing and vertical tail of this model were of triangular plan form with 60 degree sweepback of the leading edge. The results of both force and flight tests of the model are presented.
Date: February 1948
Creator: Tosti, Louis P. & Bates, William R.
Item Type: Refine your search to only Report
open access

Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92

Description: Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87.
Date: April 19, 1948
Creator: Drake, Hubert M.; McLaughlin, Milton D. & Goodman, Harold R.
Item Type: Refine your search to only Report
open access

Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 2: effects of slots upon an inlet enclosing 61.5 percent of the maximum circumference of the forebody

Description: Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop duct inlet that had slots in the walls of the duct contiguous to the forebody and immediately behind the inlet. The mass flow and total-pressure recovery through the diffusor were measured during tests in which the slot length was constant and the slot width and ramp angle were varied. Results regarding mass flow and total-pressure recovery are provided.
Date: June 9, 1948
Creator: Davis, Wallace F. & Goldstein, David L.
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Control Characteristics at Transonic Speeds of a Semispan Airplane Model Having a 45 Degree Sweptback Wing and Tail as Obtained by the Transonic-Bump Method

Description: Report presenting a wind-tunnel investigation using the transonic-bump method to determine the longitudinal stability and control characteristics of a semispan airplane model with a 45 degree sweptback wing and tail at transonic speeds. An increase in the rate of change of the pitching-moment coefficient with lift coefficient at a constant Mach number through the transonic range was noted.
Date: June 30, 1948
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Back to Top of Screen