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Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Description: "A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Description: Report presenting an experimental investigation of several airplane configurations at Mach 3.0 in a continuous flow tunnel. The configurations had circular fuselage cross sections and a sweptback wing and either two nacelles or two side inlets.
Date: March 18, 1958
Creator: Dryer, Murray & Luidens, Roger W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Description: Report presenting an investigation of a series of wings of various plan forms in the high-velocity field of the side-wall reflection plate of the 7- by 10-foot tunnel at a range of angles of attack and Mach numbers. The results indicated that the maximum lift coefficients obtainable increased with increase in sweep angle and decreased with Mach number at the lower subsonic Mach numbers.
Date: November 18, 1952
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Description: "An investigation has been made at high subsonic speeds of the aerodynamic characteristics in pitch and sideslip of a 1/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for s… more
Date: August 18, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Description: From Introduction: "Results from the tests in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 are presented in reference 1. Reported herein are results obtained from the tests in the Langley 8-foot transonic tunnel of the model with no control deflections at Mach numbers 0.6 to 1.12 for angles of attack up to 34^o
Date: March 18, 1954
Creator: Osborne, Robert S. & Wornom, Dewey E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Description: Report presenting the effectiveness of a 50-percent-semispan, constant-percent-chord elevon, and of upper-space spoilers as lateral control surfaces for a wing-fuselage combination with a wing swept back 63 degrees over a range of Mach numbers. For the elevon, results indicated that only about half of the predicted rolling-moment effectiveness was realized. The spoilers were found to be inferior to the elevons for lateral control because of a rapid loss of effectivness above an angle of attack … more
Date: January 18, 1951
Creator: Olson, Robert N. & Mead, Merrill H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance and Operational Characteristics of YJ71-A-7 Turbojet Engine

Description: "Altitude performance of a YJ71-A-7 turbojet engine, with afterburner inoperative, was determined in the NACA Lewis altitude wind tunnel over a wide range of flight conditions. Engine speed and exhaust-nozzle area were controlled independently during this investigation. The variation of corrected values of air flow, net thrust, and fuel flow with corrected engine speed was not defined by a single curve with changes in altitude at given flight Mach number" (p. 1).
Date: June 18, 1953
Creator: Smith, Ivan D.; Leonard, Charles V., Jr. & Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Description: From Introduction: "This report presents net thrusts computed for hydrogen, diborance, and hydrazine with fuel-air ratios form stoichiometric values to 0.5. Net thrusts for fuel-rich afterburning are compared with those for stoichiometric combustion of the turbojet fuel and air augmented with a 220-second specific-impulse rocket."
Date: June 18, 1957
Creator: Morris, James F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis and Construction of Design Charts for Turbines with Downstream Stators

Description: From Introduction: "This paper describes the theoretical treatment that has been given the combustion process as it occurs in turbojet combustors. Various parts of this work have been previously published (refs. 1 to 3); this report presents a brief summary of this previous work together with new data which amplify the conclusions of references 1 to 3. Similar studies have been made of the ram-jet combustion process (ref. 4 and 5); however, the analysis for ram-jet combustion differs in some de… more
Date: November 18, 1954
Creator: Cavicchi, Richard H. & Constantine, Anita B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of a piston-type gas-generator engine

Description: From Introduction: "An analysis of an engine having a division of work such that the power of the reciprocating engine is just sufficient to drive the compressor is reported herein. This combination of a reciprocating-type internal-combustion engine that drives its own supercharging compressor and generates gas for further expansion through a turbine will be called a piston-type gas generator in this report."
Date: February 18, 1948
Creator: Tauschek, Max J. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of an automatic control to prevent rolling divergence

Description: From Introduction: "The use of automatic controls to reduce the tendency for rolling divergence has been investigated in references 2 and 3. These studies have considered the effect of artificial changes in certain stability derivatives on the rolling divergence, and have shown that increased damping in pitch may be quite effective in reducing the divergent tendency. In the present report, a different type of automatic control is investigated."
Date: April 18, 1956
Creator: Phillips, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Limitations Imposed on One-Spool Ducted-Fan-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0, 0.6, and 0.8

Description: Memorandum presenting an analysis of one-spool ducted-fan engines in order to determine the primarily limitations on ducted-fan-engine design and to compare this type with the turboprop and turbojet engines for the same application. Designs were studied at flight Mach numbers of 0 and 0.6 at sea level and Mach numbers of 0.6 and 0.8 at the tropopause. Results regarding the discussion of charts, effect of design parameters on turbine stress, effect of design parameters, effect of design paramete… more
Date: July 18, 1957
Creator: Cavicchi, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of two-stage counterrotating turbine efficiencies in terms of work and speed requirements

Description: From Introduction: "This report represents an extension of the material presented in reference 4 to the case of the counterrotating turbine where the inter-stage stator is omitted and the second-stage rotor blade velocity is in the direction opposite to that of the first-stage rotor."
Date: March 18, 1958
Creator: Wintucky, William T. & Stewart, Warner L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines

Description: From Introduction: "An analytical investigation of the problems arising in connection with this cooling method was conducted at the NACA Lewis laboratory and is presented herein. This analysis investigates: (1) the smallest diameter hole that can be made without endangering the circulation of the liquid, and (2) methods of improving the circulation in a small-diameter hole."
Date: July 18, 1950
Creator: Eckert, E. R. G. & Jackson, Thomas W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical investigation of multistage-turbine efficiency characteristics in terms of work and speed requirements

Description: From Introduction: "This report presents an analytical investigation of this aerodynamic interdependence in terms of the effect of variations in the turbine specific work output, blade speed, and stage number on turbine efficiency."
Date: February 18, 1958
Creator: Stewart, Warner L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical procedures for rapid selection of coolant passage configurations for air-cooled turbine rotor blades and for evaluation of heat-transfer, strength, and pressure-loss characteristics

Description: Report presenting a method based on geometric factors of the coolant passage was evolved for the rapid selection and evaluation of coolant passage configurations for air-cooled turbine rotor blades. The most promising coolant passage configurations are analyzed to obtain absolute values of the required cooling-air weight flow, pressure loss, and strength characteristics.
Date: September 18, 1952
Creator: Ziemer, Robert R. & Slone, Henry O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of non-afterburning turbojets to supersonic flight

Description: Report presenting a paper to consider the feasibility of attaining, through the use of non-afterburning engines, essentially the same range with an all-supersonic mission as the range currently obtained with a mission incorporating subsonic cruise and supersonic dash.
Date: November 18, 1955
Creator: Cesaro, Richard S. & Walker, Curtis L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer Measurements on Several Porous Materials With Suction Applied

Description: Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.
Date: June 18, 1952
Creator: McCullough, George B. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers base… more
Date: April 18, 1957
Creator: Chauvin, Leo T. & Speegle, Katherine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculation of Flutter Characteristics for Finite-Span Swept or Unswept Wings at Subsonic and Supersonic Speeds by a Modified Strip Analysis

Description: Report presenting a method for calculating flutter characteristics of finite-span swept or unswept wings at subsonic and supersonic speeds. Flutter characteristics were calculated using this method for 12 wings of varying sweep angle, aspect ratio, taper ratio, and center-of-gravity position at a range of Mach numbers.
Date: March 18, 1958
Creator: Yates, E. Carson, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a Transonic Test Section With Various Slot Shapes in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting a large wind tunnel that has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of a slotted wind tunnel has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality can be produced.
Date: October 18, 1951
Creator: Wright, Ray H. & Ritchie, Virgil S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of flap-type spoiler ailerons at various locations on a 60 degree delta wing with a double slotted flap

Description: Report presenting a low-speed wind-tunnel investigation to determine the static lateral control characteristics of flap-type spoiler ailerons on a thin delta wing equipped with a double slotted flap. A spoiler located on the flap gave rolling-moment coefficients that varied fairly linearly with spoiler projects and with about the same magnitude for either the flap-retracted or flap-deflected position.
Date: December 18, 1952
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling

Description: Report presenting the performance characteristics of a turbine with nontwisted rotor blades suitable for air cooling. Results regarding overall performance and flow surveys at the stator and rotor exits are provided.
Date: March 18, 1952
Creator: Heaton, Thomas R.; Slivka, William R. & Westra, Leonard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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