UNT Libraries Government Documents Department - 22 Matching Results

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Altitude Performance Characteristics of Tail-Pipe Burner With Converging Conical Burner Section on J47 Turbojet Engine

Description: From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performan… more
Date: December 19, 1950
Creator: Prince, William R. & McAulay, John E.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 6 - Hamilton Standard 6507A-2 Four- and Three-Blade Propellers

Description: "An altitude-wind-tunnel investigation has been made to determine the performance of Hamilton Standard 6507A-2 four-blade and three-blade propellers on a YP-47M airplane at high blade loadings and high engine powers. Characteristics of the four-blase propeller were obtained for a range of power coefficients from 0.10 to 1.00 at free-stream Mach numbers of 0.20, 0.30, 0.40. Characteristics of the three-blade propeller were obtained for a range of power coefficients from 0.30 to 1.00 at a free-st… more
Date: December 19, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Item Type: Refine your search to only Report
open access

Design procedure for transpiration-cooled strut-supported turbine rotor blades

Description: From Summary: "The procedure currently employed by the NACA Lewis Laboratory in the design of transpiration-cooled strut-supported turbine rotor blades is discussed. The strut is the internal blade supporting member and also serves to partition the blade into separate cooling-air passages. Orifices in the blade base, which meter the cooling-air to each internal passage, are used in conjunction with a constant chordwise permeability."
Date: December 19, 1955
Creator: Prasse, Ernst I. & Livingood, John N. B.
Item Type: Refine your search to only Report
open access

Fundamental flame velocity, heat of combustion, and spontaneous ignition temperature of dimethylaminodiborane

Description: The following properties have been determined for a sample of dimethylaminodiborane : (1) maximum fundamental flame velocity for fuel and air at 35 degrees C, 115 +/- 5 centimeters per second ; (2) net (lower) heat of combustion of liquid fuel to gaseous nitrogen, carbon dioxide, and water, and to solid boric oxide, 19,225 +/- 100 Btu per pound ; and (3) spontaneous ignition temperature, 240 degrees +/- 10 degrees F.
Date: December 19, 1956
Creator: Hibbard, Robert R. & Dugger, Gordon L.
Item Type: Refine your search to only Report
open access

Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power

Description: Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Item Type: Refine your search to only Report
open access

Heat-Transfer and Pressure Measurements From a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 X 10(Exp 6): Coord. No. AF-AM-70

Description: "Boundary-layer transition and heat-transfer measurements were obtained from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and a Reynolds number per foot of 23 x 10(exp 6). Boundary-layer transition was observed on the nose of the model. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions. The drag coefficient of the configuration was also obtained for a Mach … more
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Item Type: Refine your search to only Report
open access

High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep

Description: "A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression sho… more
Date: December 19, 1947
Creator: Luoma, Arvo A.; Bielat, Ralph P. & Whitcomb, Richard T.
Item Type: Refine your search to only Report
open access

Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Description: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chor… more
Date: December 19, 1947
Creator: Conner, D. William & Foster, Gerald V.
Item Type: Refine your search to only Report
open access

Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel

Description: Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date: December 19, 1952
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
open access

An Investigation of the Icing and Heated-Air De-Icing Characteristics of the R-2600-13 Induction System

Description: "A laboratory investigation was made on a Holley 1685-HB carburetor mounted on an R-2600-13 supercharger assembly to determine the icing characteristics and the heated-air de-icing requirements of this portion of the B-25D airplane induction system. Icing has been found to be most prevalent at relatively small throttle openings and, consequently, all runs were made at simulated 60-percent normal rated power condition. Icing characteristics were determined during a series of 15-minute runs over … more
Date: December 19, 1946
Creator: Chapman, Gilbert E.
Item Type: Refine your search to only Report
open access

An investigation of the lift, drag, and static-stability characteristics of a triangular-wing airplane configuration at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and static-stability characteristics of a triangular-wing airplane over a range of Mach numbers, angles of attack, and angles of sideslip. The basic test configuration had values of maximum lift-drag ratios that were comparable to those obtained in previous tests of several airplane configurations designed primarily from considerations of flight at high supersonic speeds.
Date: December 19, 1956
Creator: Gloria, Hermilo R.
Item Type: Refine your search to only Report
open access

Investigation of wing characteristics at a Mach number of 1.53 1: triangular wings of aspect ratio 2

Description: Report presenting wind-tunnel testing conducted on three sharp-edge wing models with a thickness ratio of 5 percent and a common triangular plan form of aspect ratio 2. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The experimental lift and moment curves were found to conform essentially with the superposition principle of the linear theory.
Date: December 19, 1947
Creator: Vincenti, Walter G.; Nielsen, Jack N. & Matteson, Frederick H.
Item Type: Refine your search to only Report
open access

Performance and Component Frontal Areas of a Hypothetical Two-Spool Turbojet Engine for Three Modes of Operation

Description: Engine performance is better for constant outer-spool mechanical-speed operation than for constant inner-spool mechanical-speed operation over most of the flight range considered. Combustor and afterburner frontal areas are about the same for the two modes. Engine performance for a mode characterized by a constant outer-spool equivalent speed over part of the flight range and a constant outer-spool mechanical speed over the rest of the flight range is better that that for constant outer-spool m… more
Date: December 19, 1955
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
open access

Preliminary investigation of effect on performance of dividing conical-spike nose inlets into halves at Mach numbers 1.5 to 2.0

Description: Inserting a splitter plate in the subsonic diffuser caused a pressure-recovery loss of about 1 percent for an inlet with a long nearly constant-area throat section. The loss was due to the increased surface area. Another inlet, which had a comparatively rapid area increase immediately after the throat, experienced pressure-recovery losses of 5 and 6 percent at Mach numbers of 1.8 and 2.0, respectively, and about 1 percent at Mach 1.5.
Date: December 19, 1955
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

Preliminary investigation of methods to increase base pressure of plug nozzles at Mach 0.9

Description: The effects of various afterbody changes on the base pressure of a nacelle-type isentropic plug nozzle installation operating at lower-than-design jet pressure ratios were investigated at a Mach number of 0.9. Although the estimates of the net propulsive force contain some uncertainties, the results indicate that both a plain-ring base shroud and a circular-arc boattail fairing reduced the loss in net propulsive force experienced with a cylindrical nacelle installation of the plug nozzle.
Date: December 19, 1956
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
open access

Resume of Wind-Tunnel Data on the Effect of External Stores on Stability of Models of Military Airplanes

Description: Report presenting a study of static wind-tunnel data on the effects of external stores like tanks, torpedoes, bombs, and radar domes on the stability of military airplanes. The results are focused on longitudinal and lateral stability. Static longitudinal stability is affected at various Mach numbers, but the data was not sufficient to estimate the effect on the lateral stability.
Date: December 19, 1946
Creator: Silvers, H. Norman & Vogler, Raymond D.
Item Type: Refine your search to only Report
open access

Rocket-engine throttling

Description: An investigation of the performance and operating characteristics of two variable-thrust injectors over a wide thrust range using mixed oxides of nitrogen and ammonia. Specific impulse, characteristic velocity, thrust coefficient, and overall efficiency are presented as functions of thrust. A maximum thrust range of 12 during one run was obtained with a triplet impinging-jet injector.
Date: December 19, 1955
Creator: Tomazic, William A.
Item Type: Refine your search to only Report
open access

Tank investigation of a series of related hydro-skis as load-alleviation devices for landing a seaplane in waves

Description: Report presenting a tank investigation to determine the effects of hydro-skis as load-alleviation devices for landing a seaplane in waves. Results regarding the basic model without hydro-ski, effect of longitudinal location of hydro-ski, effect of landing trim, effect of hydro-ski dimensions, effect of landing speed, effect of vertical location of hydro-ski, effect of wave height, effect of angle of incidence, effect of aerodynamic stability, and consideration of hydro-skis as a ditching aid ar… more
Date: December 19, 1956
Creator: Carter, Arthur W.; Morse, Archibald E., Jr. & Woodward, David R.
Item Type: Refine your search to only Report
open access

Thermal Stability of Pentaborane in the Range 329 to 419 Degrees F

Description: "The thermal stability of pentaborane has been determined in the temperature range 329 degrees to 419 degrees Fahrenheit by measuring the increase with time in the formation of nonvolatile residue. A relationship was established between the thermal stability and the temperature. The expression permitted extrapolation to obtain the stability of pentaborane at either high temperatures and short times or at ambient temperatures and long times" (p. 1).
Date: December 19, 1956
Creator: McDonald, Glen E.
Item Type: Refine your search to only Report
open access

A transonic wind-tunnel investigation of the characteristics of a twisted and cambered 45 degree sweptback wing-fuselage configuration

Description: Report presenting an investigation in the 8-foot transonic tunnel to determine the effects of twist and camber on the aerodynamic characteristics of a sweptback wing-fuselage configuration. The wing had 45 degrees sweepback of the 0.25 chord, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A-series airfoil sections with 6-percent thickness distribution parallel to the plane of symmetry. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics … more
Date: December 19, 1952
Creator: Harrison, Daniel E.
Item Type: Refine your search to only Report
open access

Turbojet engine investigation of effect of thermal shock induced by external water-spray cooling on turbine blades of five high-temperature alloys

Description: Report presenting an investigation of the thermal-shock effect of water-spray impingement upon turbine rotor blades subjected to rated engine operating conditions using external water-spray cooling. Turbine-blade cooling water was turned on and off in cycles which employed either sudden or gradual injection of cooling water. Results regarding blades modified and unmodified for rotating injection are provided.
Date: December 19, 1955
Creator: Freche, John C. & Hickel, Robert O.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Descent Characteristics of Bodies of Revolution Simulating Anti-Personnel Bombs

Description: "An investigation has been conducted in the Langley 20-foot free spinning tunnel to study the relative behavior in descent of a number of homogeneous balsa bodies of revolution simulating anti-personnel bombs with a small cylindrical exploding device suspended approximately 10 feet below the bomb. The bodies of revolution included hemispherical, near-hemispherical, and near-paraboloid shapes. The ordinates of one near-paraboloid shape were specified by the Office of the Chief of Ordnance, U. S.… more
Date: December 19, 1951
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
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