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Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Description: "Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the ro… more
Date: September 27, 1945
Creator: Klein, Milton M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Several NACA Airfoil Sections at Seven Reynolds Numbers From 0.7 X 10(Exp 6) to 9.0 X 10(Exp 6)

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of several NACA airfoil sections at four Reynolds numbers. Results regarding the minimum drag, maximum lift, lift-curve slope, and angle of zero lift and pitching moment are provided.
Date: May 27, 1948
Creator: Loftin, Laurence K., Jr. & Poteat, M. Irene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airship Model Tests in the Variable Density Wind Tunnel

Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at… more
Date: January 27, 1931
Creator: Abbott, Ira H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude investigation of 20-inch-diameter ram-jet engine with annular-piloted combustor

Description: From Introduction: "The combustor efficiency, combustor-inlet Mach number, and combustor total-pressure ratio of the annular-piloted combustor are presented herein. The effect of combustor-exit total pressure on combustor efficiency, and a comparison of configurations on the basis of specific fuel consumption are also presented."
Date: August 27, 1954
Creator: Henzel, James G. & Trout, Arthur M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specificatio… more
Date: August 27, 1952
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 4: Effect of Inlet-Air Temperature, Combustion-Chamber-Inlet Mach Number, and Fuel Volatility on Combustion Performance

Description: Report presenting testing of the effects of the following variables on combustion performance are determined: inlet-air temperature, combustion-chamber-inlet Mach number and pressure, and fuel density and volatility.
Date: July 27, 1951
Creator: Kahn, Robert W.; Nakanishi, Shigeo & Harp, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear- powered aircraft

Description: From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date: May 27, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear-powered aircraft

Description: From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat-exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date: May 27, 1952
Creator: Wachtl, William W. & Rom, Frank E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Stage Matching and Off-Design Performance of Multistage Axial-Flow Compressors

Description: From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."
Date: June 27, 1952
Creator: Finger, Harold B. & Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of temperature distribution in liquid-cooled turbine blades

Description: From Summary: "This report presents analytical methods for computing temperature distributions in liquid-cooled turbine blades, or in simplified shapes used to approximate sections of the blade. The individual analyses are first presented in terms of their mathematical development. Nondimensional charts to simplify some temperature-distribution calculations are also given."
Date: October 27, 1950
Creator: Livingood, John N. B. & Brown, W. Byron
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Bending and shear stresses developed by the instantaneous arrest of the root of a moving cantilever beam

Description: A theoretical and experimental investigation has been made of the behavior of a cantilever beam in transverse motion when its root is suddenly brought to rest. Equations are given for determining the stresses, the deflections, and the accelerations that arise in the beam as a result of the impact. The theoretical equations, which have been confirmed experimentally, reveal that, at a given percentage of the distance from root to tip, the bending stresses for a particular mode are independent of … more
Date: September 27, 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending of Rectangular Plates With Large Deflections

Description: "The solution of Von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to Von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, Mcpherson, and… more
Date: May 27, 1941
Creator: Levy, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Brief Summary of Experience in Boosting Aerodynamic Research Models

Description: "Approximately 2,000 flights of rocket-propelled models have been made in which model configuration, model size, type and number of booster rockets, number of booster stages, and booster arrangements varied. A brief summary of the results obtained with some of the more unusual arrangements, descriptions of boosting hardware and techniques, and discussions of some factors responsible for the choice of these configurations are presented in this paper. The results show that unconventional boosting… more
Date: July 27, 1956
Creator: Thibodaux, Joseph G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated Condenser Performance for a Mercury-Turbine Power Plant for Aircraft

Description: "As part of an investigation of the application of nuclear energy to various types of power plants for aircraft, calculations have been made to determine the effect of several operating conditions on the performance of condensers for mercury-turbine power plants. The analysis covered 8 range of turbine-outlet pressures from 1 to 200 pounds per square inch absolute, turbine-inlet pressures from 300 to 700 pounds per square inch absolute,and a range of condenser cooling-air pressure drops, airpla… more
Date: August 27, 1948
Creator: Doyle, Ronald B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Calculation of Certain Static Aeroelastic Phenomena of Wings With Tip Tanks or Boom-Mounted Lifting Surfaces

Description: Report presenting the use of the matrix-integration method for calculating static aeroelastic phenomena on a wing with concentrated aerodynamic forces at the tip due to tip tanks or boom-mounted lifting surfaces. The results indicate that the presence of a tip tank on an unswept wing tends to deteriorate its static aeroelastic characteristics and that a lift surface geared to the aileron and mounted on a boom ahead of the tip may improve the static aeroelastic characteristics to warrant conside… more
Date: August 27, 1952
Creator: Diederich, Franklin W. & Foss, Kenneth A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a Hot Jet Discharged from a Jet-Propulsion Engine

Description: From Summary: "An investigation of a heated jet was conducted in conjunction with tests of an axial-flow jet-propulsion engine in the Cleveland altitude wind tunnel. Pressure and temperature surveys were made across the jet 10 and 15 feet behind the jet-nozzle outlet of the engine. Surveys were obtained at pressure altitudes of 10,000, 20,000, 30,000, and 40,000 feet with test-section velocities from 30 to 110 feet per second and test-section temperatures from 60 F to -50 F. From measurements t… more
Date: December 27, 1946
Creator: Fleming, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Charts for estimating tail-rotor contribution to helicopter directional stability and control in low-speed flight

Description: "Theoretically derived charts and equations are presented by which tail-rotor design studies of directional trim and control response at low forward speed can be conveniently made. The charts can also be used to obtain the main-rotor stability derivatives of thrust with respect to collective pitch and angle of attack at low forward speeds. The use of the charts and equations for tail-rotor design studies is illustrated. Comparisons between theoretical and experimental results are presented. The… more
Date: October 27, 1953
Creator: Amer, Kenneth B. & Gessow, Alfred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combustion Instability in an Acid-Heptane Rocket with a Pressurized-Gas Propellant Pumping System

Description: Results of experimental measurements of low-frequency combustion instability of a 300-pound thrust acid-heptane rocket engine were compared to the trends predicted by an analysis of combustion instability in a rocket engine with a pressurized-gas propellant pumping system. The simplified analysis, which assumes a monopropellant model, was based on the concept of a combustion the delay occurring from the moment of propellant injection to the moment of propellant combustion. This combustion time … more
Date: September 27, 1951
Creator: Tischler, Adelbert O. & Bellman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions

Description: "For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratios in the presence of a swept-wing fighter-bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques."
Date: December 27, 1957
Creator: Carlson, Harry W.; Geier, Douglas J. & Lee, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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