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Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Description: "A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The … more
Date: April 11, 1947
Creator: Adams, Richard E. & Silsby, Norman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers

Description: "The static longitudinal stability characteristics of a 0.15-scale model of the Hermes A-lE2 missile have been determined in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.98, corresponding to Reynolds numbers, based on body length, of 12.3 x 10(exp 6) to 17.1 x 10(exp 6). This paper presents results obtained with body alone and body-fins combinations at 0 degrees (one set of fins vertical and the other set horizontal) and 45 degree angle of roll. The results … more
Date: September 11, 1952
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Description: From Summary: "An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the mis… more
Date: September 11, 1956
Creator: Allen, H. Julian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Frequency-Response Characteristics of the Douglas D-558-I Airplane as Determined From Experimental Transient-Response Histories to Mach Number of 0.90

Description: Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.
Date: February 11, 1952
Creator: Angle, Ellwyn E. & Holleman, Euclid C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: "Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).
Date: February 11, 1955
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing of the Northrop MX-775A Missile With Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.
Date: February 11, 1955
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Description: Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date: March 11, 1947
Creator: Bartlett, Walter A., Jr. & Goral, Edwin B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance evaluation of reduced-chord rotor blading as applied to J73 two-stage turbine 1: over-all performance with standard rotor blading at inlet conditions of 35 inches of mercury absolute and 700 degrees R

Description: Report presenting an investigation conducted to determine the overall performance of the J73 two-stage turbine with a standard rotor-blade configuration. The turbine operated with a maximum brake internal efficiency between 0.91 and 0.92 at an overall pressure ratio of about 3.4 and 120 percent equivalent design rotor speed. Results regarding the overall performance, variation of equivalent weight flow with overall pressure ratio, and effect of limiting blade loading are provided.
Date: July 11, 1957
Creator: Berkey, William E.; Rebeske, John J., Jr. & Forrette, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability of Ballistic Reentry Bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up

Description: "A preliminary analytical investigation was made to determine the feasibility of the basic idea of controlled failure points as safety valves for the primary airplane structure. The present analysis considers the possibilities of the breakable wing tip which, in failing as a weak link, would relieve the bending moments on the wing structure. The analysis was carried out by computing the time histories of the wing and stabilizer angle of attack in a 10g pull-up for an XF8F airplane with tips fix… more
Date: December 11, 1947
Creator: Boshar, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of the combustion of a 50 percent pentaborane - 50 percent JP-4 fuel blend in a turbojet combustor at simulated altitude conditions

Description: A preliminary investigation was conducted to determine the combustion characteristics of a fuel composed of 50 percent pentaborane and 50 percent JP-4 (MIL-F-5624A) by weight in a turbojet combustor. A combustor designed to fit the housing of a J33-A-23 turbojet engine was selected for convenience. The fuel was evaluated at two engine conditions simulating altitudes of 40,000 and 57,000 feet, an engine speed of 85 percent of rated rpm, and a flight Mach number of 0.6. The pentaborane blend was … more
Date: March 11, 1957
Creator: Branstetter, J. Robert; Kaufman, Warner B. & Gibbs, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some experiments relating to the problem of simulation of hot jet engines in studies of jet effects on adjacent surfaces at a free-stream Mach number of 1.80

Description: Report presenting an investigation at a free-stream Mach number of 1.80 in a blowdown tunnel to study the effect on the pressure distribution of a zero-angle-of-attack wing surface when certain exhaust parameters of a hot turbojet engine are varied. Results regarding shock wave and pressure coefficients are provided.
Date: July 11, 1956
Creator: Bressette, Walter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines

Description: Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Date: June 11, 1948
Creator: Brightwell, Virginia L.; Peters, Max D. & Sanders, J. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling of Gas Turbines 1 - Effects of Addition of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles, and Change in Thermal Conductivity of Turbine Components

Description: "An analysis was developed for calculating the radial temperature distribution in a gas turbine with only the temperatures of the gas and the cooling air and the surface heat-transfer coefficient known. This analysis was applied to determine the temperatures of a complete wheel of a conventional single-stage impulse exhaust-gas turbine. The temperatures were first calculated for the case of the turbine operating at design conditions of speed, gas flow, etc. and with only the customary cooling a… more
Date: February 11, 1947
Creator: Brown, W. Byron
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Extension of boundary-layer heat-transfer theory to cooled turbine blades

Description: An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinder… more
Date: August 11, 1950
Creator: Brown, W. Byron & Donoughe, Patrick L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures

Description: Analytical methods are presented for the determination of local values of outside and inside heat-transfer coefficients and effective gas temperatures by use of turbine-blade-temperature measurements. The methods are derived for a number of configurations that can be applied to typical cooled-turbine-blade shapes as well as to other types of heat-transfer apparatus.
Date: August 11, 1950
Creator: Brown, W. Byron & Esgar, Jack B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling of Gas Turbines, 3, Analysis of Rotor and Blade Temperatures in Liquid-Cooled Gas Turbines

Description: A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect … more
Date: February 11, 1947
Creator: Brown, W. Byron & Livingood, John N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-Limited Performance of Triptane and 28-R Fuel Blends as Affected by Changes in Compression Ratio and in Engine Operating Variables

Description: From Summary: "A knock-limited performance investigation was conducted on blends of triptane and 28-P fuel with a 12-cylinder, V-type, liquid-cooled aircraft engine of 1710-cubic-inch displacement at three compression ratios: 6.65, 7.93, and 9.68. At each compression ratio, the effect of changes in temperature of the inlet air to the auxiliary-stage supercharger and in fuel-air ratio were investigated at engine speeds of 2280 and. 3000 rpm. The results show that knock-limited engine performance… more
Date: March 11, 1947
Creator: Brun, Rinaldo J.; Feder, Melvin S. & Fisher, William F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Empirical Design Requirements for the Prevention of Tumbling of Airplanes Having No Horizontal Tails

Description: Report presenting an investigation of the design characteristics and loadings conducive to the tumbling of airplanes with no horizontal tails. Empirical design requirements based on model testings of 18 different configurations and an explanation of the phenomena of tumbling are provided.
Date: October 11, 1950
Creator: Bryant, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbulent Convective Heat-Transfer Coefficients Measured From Flight Tests of Four Research Models (NACA RM-10) at Mach Numbers From 1.0 to 3.6

Description: Report presenting an evaluation of convective heat-transfer coefficients from skin temperatures measured along the body of a research model designated NACA RM-10. Heat-transfer data is presented for a range of Mach and Reynolds numbers based on the axial distance from the nose to the point at which the temperature measurements were made. Results regarding the recovery factor, heat transfer, correlation with different aircraft models, and Reynolds analogy are provided.
Date: March 11, 1955
Creator: Chauvin, Leo T. & Maloney, Joseph P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands

Description: Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Stability Characteristics of the Bell X-5 Research Airplane in Sideslips at 59 Degrees Sweepback

Description: "Flight measurements of the stability characteristics of the Bell X-5 research airplane at 59 deg sweepback were made in steady sideslips at Mach numbers from 0.62 to 0.97 at altitudes ranging between 35,000 and 40,000 feet. The results showed that the apparent directional stability was positive and increased at Mach numbers above 0.90. The apparent effective dihedral was positive and high, increasing at Mach numbers above 0.75" (p. 1).
Date: February 11, 1953
Creator: Childs, Joan M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Effect of Sideslip on the Pressure at the Static Orifices of the Boeing B-29 Airplane

Description: Report discussing testing to determine the sensitivity to sideslip of the static-pressure orifices of the Boeing B-29. The purpose was to determine the errors in indicated altitude and vertical velocity that occur when an airplane experiences oscillations in sideslip on a bombing run. The sensitivity of the orifices to sideslip was determined by measurements of pressure and sideslip angle during constant-amplitude oscillations in sideslip.
Date: April 11, 1951
Creator: Chilton, Robert G. & Brown, B. Porter
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil

Description: Report presenting an investigation of the effects of a systematic variation of trailing-edge thickness of a symmetrical, circular-arc airfoil on the aerodynamic force, moment, base-pressure, and wake fluctuations using the transonic-bump testing technique. Results regarding the effects of a systematic variation of the trailing-edge thickness, investigation of a boattailed trailing edge, and wake fluctuation characteristics are provided.
Date: December 11, 1951
Creator: Cleary, Joseph W. & Stevens, George L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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