Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336 (open access)

Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336

A 1/5.5-size powered dynamic model of the Columbia XJL-1 amphibian was landed in Langley tank no. 1 in smooth water and in oncoming waves of heights from 2.1 feet to 6.4 feet (full-size) and lengths from 50 feet to 264 feet (full-size). The motions and the vertical accelerations of the model were continuously recorded. The greatest vertical acceleration measured during the smooth-water landings was 3.1g.
Date: September 25, 1947
Creator: Clement, Eugene P. & Havens, Robert F.
System: The UNT Digital Library
Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length (open access)

Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length

From Introduction: "The results of an investigation of the low-speed static stability of a simplified model of such an arrangement having one of the airfoils placed vertically on top of the body and the other two as wing panels having negative dihedral are presented in reference 1. In order to provide information for predicting the effects of changes in the basic configuration on the low-speed stability characteristics presented in reference 1, additional measurements have been made."
Date: July 25, 1955
Creator: Delany, Noel K.
System: The UNT Digital Library
Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Aspect Ratio of 3.5 and a Taper Ratio of 0.2: Effect at M = 2.01 of Nacelle Shape and Position on the Aerodynamic Characteristics in Pitch of Two Wing-Body Combinations with 47 Degree Sweptback Wings (open access)

Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Aspect Ratio of 3.5 and a Taper Ratio of 0.2: Effect at M = 2.01 of Nacelle Shape and Position on the Aerodynamic Characteristics in Pitch of Two Wing-Body Combinations with 47 Degree Sweptback Wings

Memorandum presenting an investigation at M = 2.01 in the 4- by 4-foot supersonic pressure tunnel to determine the effect of a series of nacelles on the longitudinal stability characteristics of a sweptback wing-body combination. Nacelle shape and position were varied on a configuration with a 6-percent-thick wing with an aspect ratio of 3.5, a taper ratio of 0.2, and 47 degrees of sweep at the quarter chord.
Date: July 25, 1952
Creator: Driver, Cornelius
System: The UNT Digital Library
Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method (open access)

Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method

From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.
System: The UNT Digital Library
Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04 (open access)

Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."
Date: April 25, 1955
Creator: Ulmann, Edward F. & Smith, Fred M.
System: The UNT Digital Library
Aerodynamic Characteristics of Missile Configurations With Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01 (open access)

Aerodynamic Characteristics of Missile Configurations With Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01

"An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report" (p. 1).
Date: June 25, 1957
Creator: Robinson, Ross B.
System: The UNT Digital Library
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 4: aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies (open access)

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 4: aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies

Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.
Date: January 25, 1954
Creator: Jack, John R. & Moskowitz, Barry
System: The UNT Digital Library
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance (open access)

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance

"Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers" (p. 1).
Date: April 25, 1947
Creator: Dietz, Robert O. & Kuenzig, John K.
System: The UNT Digital Library
Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine 1: Performance with tail-pipe burning (open access)

Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine 1: Performance with tail-pipe burning

From Introduction: "Performance results of the tail-pipe burning investigation on the TG-180 turbojet engine and a comparison of experimental results with theoretical calculations are presented."
Date: September 25, 1946
Creator: Fleming, W. A. & Dietz, R. O.
System: The UNT Digital Library
The Ames supersonic free-flight wind tunnel (open access)

The Ames supersonic free-flight wind tunnel

From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
System: The UNT Digital Library
The Ames Supersonic Free-Flight Wind Tunnel (open access)

The Ames Supersonic Free-Flight Wind Tunnel

Memorandum presenting a description of the Ames supersonic free-flight wind tunnel, which is a new piece of equipment for aerodynamic research at high supersonic Mach numbers. It has a wide Mach number range extending from low supersonic speeds to Mach numbers in excess of 10. The air stream in the tunnel is imperfect, mainly due to a symmetrical pair of oblique shock waves which reflect down the test section.
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
System: The UNT Digital Library
Analysis of cooling-air requirements of corrugated-insert-type turbine blades suitable for a supersonic turbojet engine (open access)

Analysis of cooling-air requirements of corrugated-insert-type turbine blades suitable for a supersonic turbojet engine

From Introduction: "This report presents the cooling-air requirements of a "paper" air-cooled turbojet engine operating over a wide range of flight Mach numbers and altitudes. The results are presented for a two-stage-turbine turbo-jet engine having a turbine-inlet temperature of 2500^o R and operating at sea-level static conditions and flight Mach numbers from 0.90 to 2.5 and flight altitudes from 40,000 to 70,000 feet. In addition, the effect of decreasing the blade-inlet cooling-air temperature on the required coolant-flow ratio is presented."
Date: April 25, 1956
Creator: Ziemer, Robert R. & Slone, Henry O.
System: The UNT Digital Library
Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity (open access)

Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity

Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.
Date: May 25, 1954
Creator: Rossbach, Richard J.; Schramm, Wilson B. & Hubbartt, James E.
System: The UNT Digital Library
An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane (open access)

An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

From Introduction: "This report presents an analysis based on flight and wind-tunnel test data directed toward the determination of the probable cause of the pitch-up. Wing pressure distribution and stability and control characteristics in the dive are also included."
Date: September 25, 1947
Creator: Brown, Harvey H.; Rolls, L. Stewart & Clousing, Lawrence A.
System: The UNT Digital Library
Analysis of V-G records from ten types of Navy airplanes in squadron operations during the period 1949 to 1953 (open access)

Analysis of V-G records from ten types of Navy airplanes in squadron operations during the period 1949 to 1953

From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."
Date: March 25, 1955
Creator: Mayer, John P. & Harris, Agnes E.
System: The UNT Digital Library
Analytic evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane in octene-1 : Supplement I - Influence of new boric-oxide vapor-pressure data on calculated performanc (open access)

Analytic evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane in octene-1 : Supplement I - Influence of new boric-oxide vapor-pressure data on calculated performanc

"The theoretical performance of pentaborane has been recalculated using recent data on the vapor pressure of boric oxide. Previous calculations were based upon vapor-pressure data obtained some years ago by a method not as accurate as that employed in current investigations. The recalculated performance data for pentaborane differ appreciably from previously published data and are considered more accurate for evaluation of the relative potentialities of boron-containing fuels" (p. 1).
Date: May 25, 1956
Creator: Tower, Leonard K.
System: The UNT Digital Library
Analytical determination of effect of turbine cooling-air-impeller performance on engine performance and comparison of experimentally determined performance of impellers with and without inducer vanes (open access)

Analytical determination of effect of turbine cooling-air-impeller performance on engine performance and comparison of experimentally determined performance of impellers with and without inducer vanes

Report presenting an analytical and experimental investigation of the effects of cooling-air impeller performance on turbojet-engine performance at 70 and 100 percent of rated engine speed. Analysis indicated that the impeller performance has little effect on engine performance at rated engine speed for the coolant flows considered. Results regarding the impeller total-pressure ratio and cooling air available with compressor bleed are provided.
Date: October 25, 1954
Creator: Schafer, Louis J., Jr. & Hickel, Robert O.
System: The UNT Digital Library
Analytical investigation of factors affecting the performance of single-stage turbines having rotor-tip discharge of cooling air (open access)

Analytical investigation of factors affecting the performance of single-stage turbines having rotor-tip discharge of cooling air

From Introduction: "The purpose of this report is to further analyze the turbine performance results of reference 1 with the objective of isolating the contribution of the cooling air to the turbine performance and establishing some systematic relation between these cooling-air effects and the turbine operational parameters."
Date: April 25, 1956
Creator: Smith, Gordon T. & Hickel, Robert O.
System: The UNT Digital Library
Applications of auxiliary air injectors to supersonic wind tunnels (open access)

Applications of auxiliary air injectors to supersonic wind tunnels

Report presenting a discussion of the adverse effects of high compression ratio requirements for supersonic wind tunnels as well as the use of second throats for alleviating those effects. The results indicated that an auxiliary air-injector system can reduce starting and running compression ratios as compared to a conventional wind tunnel with a divergent diffuser.
Date: November 25, 1953
Creator: Spiegel, Joseph M.; Hofstetter, Robert U. & Kuehn, Donald M.
System: The UNT Digital Library
Bodies of Revolution for Minimum Drag at High Supersonic Airspeeds (open access)

Bodies of Revolution for Minimum Drag at High Supersonic Airspeeds

From Summary: "Approximate shapes of nonlifting bodies having minimum pressure foredrag at high supersonic airspeeds are calculated.With the aid of Newton's law of resistance, the investigation is carried out for various combinations of the conditions of given body length, base diameter, surface area, and volume. In general it is found that when body length is fixed, the body has a blunt nose; whereas, when the length is not fixed, the body has a sharp nose."
Date: February 25, 1952
Creator: Eggers, A. J., Jr.; Dennis, David H. & Resnikoff, Meyer M.
System: The UNT Digital Library
Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil (open access)

Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil

Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are presented.
Date: March 25, 1936
Creator: Pinkerton, Robert M.
System: The UNT Digital Library
Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0 (open access)

Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: June 25, 1951
Creator: Brajnikoff, George B. & Rogers, Arthur W.
System: The UNT Digital Library
Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger (open access)

Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger

This report presents the comparative flight results of a roots supercharger and a turbocentrifugal supercharger. The tests were conducted using a modified DH-4M2 airplane. The rate of climb and the high speed in level flight of the airplane were obtained for each supercharger from sea level to the ceiling. The unsupercharged performance with each supercharger mounted in place was also determined. The results of these tests show that the ceiling and rate of climb obtained were nearly the same for each supercharger, but that the high speed obtained with the turbocentrifugal was better than that obtained with the roots. The high-speed performance at 21,000 feet was 122 and 142 miles per hour for the roots and turbocentrifugal, respectively.
Date: February 25, 1930
Creator: Schey, Oscar W. & Young, Alfred W.
System: The UNT Digital Library
Comparison of Alcogas Aviation Fuel With Export Aviation Gasoline (open access)

Comparison of Alcogas Aviation Fuel With Export Aviation Gasoline

Mixtures of gasoline and alcohol when used in internal combustion engines designed for gasoline have been found to possess the advantage of alcohol in withstanding high compression without "knock" while retaining advantages of gasoline with regard to starting characteristics. Test of such fuels for maximum power-producing ability and fuel economy at various rates of consumption are thus of practical importance, with especial reference to high-compression engine development. This report discusses the results of tests which compares the performance of alcogas with x gasoline (export grade) as a standard.
Date: November 25, 1919
Creator: Gage, V. R.; Sparrow, S. W. & Harper, D. R.
System: The UNT Digital Library