UNT Libraries Government Documents Department - 19 Matching Results

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An active particle diffusion theory of flame quenching for laminar flames

Description: An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be con… more
Date: March 4, 1952
Creator: Simon, Dorothy M. & Belles, Frank E.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Description: From Introduction: "The investigation covered a range of Mach numbers from 0.66 to 1.12 and included measurements of angle of attack, pitching moment, normal force, and chord force. The drag at zero lift obtained in this investigation was reported in reference 1, but without the correction for tare of the end plate."
Date: March 4, 1949
Creator: Lina, Lindsay J.
Item Type: Refine your search to only Report
open access

Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds

Description: Report presenting an investigation of the jet effects on several afterbody shapes of a single-engine fighter-airplane model in the 16-foot transonic tunnel at a range of Mach numbers and angles of attack. The afterbody-geometry variables were boattail angle, afterbody length, and base area. Results regarding evaluation of support interference, afterbody-pressure-distribution characteristics, and drag characteristics are provided.
Date: March 4, 1958
Creator: Norton, Harry T., Jr. & Swihart, John M.
Item Type: Refine your search to only Report
open access

The effect of several jet-engine air-inlet configurations on the low-speed static lateral stability characteristics of a 1/6-scale model of the MX-1764 airplane

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The inlet configurations generally had only small effects on the lateral stability.
Date: March 4, 1954
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
open access

The Effect of Several Jet-Engine Air-Inlet Configurations on the Low-Speed Static Lateral Stability Characteristics of a 1/6- Scale of the MX-1764 Airplane

Description: Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally had only small effects on the lateral stability.
Date: March 4, 1954
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
open access

The effects of a modified roll-command system on the flight-path stability and tracking accuracy of an automatic interceptor

Description: From Summary: "In order to improve the tracking characteristics of an automatic interceptor, a revised roll-command computer was tested both on an analog computer and in flight. This report presents flight-test results which indicate a significant improvement in flight-path stability and tracking accuracy. The modified roll computer was designed on the basis of previous analytical studies."
Date: March 4, 1958
Creator: Triplett, William C.
Item Type: Refine your search to only Report
open access

Initial Flight Tests of the NACA FR-2, a High-Velocity Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting initial flight tests of two simplified flutter vehicles. Test results were in agreement with the results of the freely-falling-body test in that the wing failures in the transonic range occurred at velocities greater than the flutter velocity calculated from the two-dimensional theory.
Date: March 4, 1948
Creator: Barmby, J. G. & Teitelbaum, J. M.
Item Type: Refine your search to only Report
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 1: turbine-design requirements for several engine operating conditions

Description: In order to insure satisfactory turbine performance under five turbojet-engine operating conditions, turbine design requirements were determined for the following operating conditions: take-off, maximum thrust at altitude, altitude cruising at rated rotative speed, altitude cruising with maximum-thrust exhaust nozzle area, and engine acceleration at 80 percent equivalent design rotative speed. If cruising is to be at rated engine speed, both cruising and take-off should be considered in turbine… more
Date: March 4, 1952
Creator: English, Robert E.; Silvern, David H. & Davison, Elmer H.
Item Type: Refine your search to only Report
open access

Observation of Laminar Flow on an Air-Launched 15 Degree Cone-Cylinder at Local Reynolds Numbers to 50 X 10(Exp 6) at Peak Mach Number of 6.75

Description: Report presenting an investigation of a free-flight test vehicle to obtain boundary-layer-transition and heat-transfer data. The model had a 15-degree-included-angle cone-cylinder and a 10 degree conically flared afterbody. Results regarding the free-stream conditions, conditions at outer edge of boundary layer, temperatures and heat-transfer coefficients, and boundary-layer stability conditions are provided.
Date: March 4, 1957
Creator: Rabb, Leonard & Krasnican, Milan J.
Item Type: Refine your search to only Report
open access

Preliminary Flight Measurements of the Total-Pressure Recovery of a Split-Wing Ram-Jet Inlet at Mach Numbers from 1.4 to 3.16

Description: "Flight tests were made to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a Mach number range from 1.4 to 3.16. Total-pressure-recovery measurements at the diffuser exist station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range. Comparisons of average total-pressure recovery with the theoretical total-pressure recovery showed good agreement" (p. 1).
Date: March 4, 1954
Creator: Hinners, Arthur H., Jr.
Item Type: Refine your search to only Report
open access

Preliminary Flight Measurements of the Total-Pressure Recovery of a Split-Wing Ram-Jet Inlet at Mach Numbers From 1.4 to 3.16

Description: Report presenting flight tests to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a range of Mach numbers. Total-pressure-recovery measurements at the diffuser exit station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range.
Date: March 4, 1954
Creator: Hinners, Arthur H., Jr.
Item Type: Refine your search to only Report
open access

Problem of Slip Flow in Aerodynamics

Description: Memorandum presenting a survey of the present status of theory in the field of slip-flow aerodynamics, which leads to the conclusion that the Navier-Stokes equations of motion together with first-order velocity slip and temperature jump at any boundary are sufficient insofar as experimental confirmation is available.
Date: March 4, 1957
Creator: Street, Robert E.
Item Type: Refine your search to only Report
open access

Reductions in Temperature-Recovery Factor Associated With Pulsating Flows Generated by Spike-Nosed Cylinders at a Mach Number of 3.50

Description: Report presenting an investigation to determine the reductions in temperature-recovery factor associated with pulsating flows generated by spike-nose cylinders. The investigation was conducted at zero angle of incidence at a free stream Mach number of 3.50 and a free stream Reynolds number of 1.73 million.
Date: March 4, 1957
Creator: Hermach, C. A.; Kraus, Samuel & Reller, John O., Jr.
Item Type: Refine your search to only Report
open access

Some Data on Body and Jet Reaction Controls

Description: Report presenting testing of a series of rocket-propelled general-research test missiles incorporating cruciform delta wings mounted along the diagonals of a fuselage of square cross section used to obtain longitudinal trim in flight. Several combinations of controls and static and dynamic longitudinal stability of the missiles were tested at a range of Mach numbers.
Date: March 4, 1957
Creator: Henning, Allen B.; Wineman, Andrew R. & Rainey, Robert W.
Item Type: Refine your search to only Report
open access

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: lateral-directional characteristics of a triangular wing and canard

Description: Report presenting the results of an investigation of the static lateral-directional stability characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for various combinations of the canard, body, wing, and vertical tail. Data were obtained at a variety of angles of attack, sideslip angles, and canard angles.
Date: March 4, 1958
Creator: Peterson, Victor L. & Menees, Gene P.
Item Type: Refine your search to only Report
open access

Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

Description: Report using an analog computer to study the effects of aerodynamic parameters on the ability of a pilot to control a hypersonic research airplane capable of flight at very high altitudes. The results, which are based on pilot opinion of the difficulty of the control task, are illustrated by time histories of angle of attack, angle of sideslip, and roll angle. The basic airplane configuration was generally found to be unflyable and the arrangement of the information on the pilot's display was f… more
Date: March 4, 1958
Creator: Sherman, Windsor L.; Faber, Stanley & Whitten, James B.
Item Type: Refine your search to only Report
open access

Summary of Available Data Relating to Reynolds Number Effects on the Maximum Lift Coefficients of Swept-Back Wings

Description: The available foreign and American data relating to Reynolds number effects on the maximum lift coefficients of swept-back wings are summarized and discussed. The data show that at low Reynolds numbers (below about 2.0 x 10(exp 6)) higher maximum lift coefficients were measured in most cases for moderately swept-back wings than for unswept wings of similar plan form; at high Reynolds numbers, however, increasing sweepback resulted in decreasing maximum lift coefficients. A smaller rate of incre… more
Date: March 4, 1947
Creator: Sweberg, Harold H. & Lange, Roy H.
Item Type: Refine your search to only Report
open access

Tests of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- by 80-Foot Wind Tunnel. - Force and Moment Data

Description: "Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane having swept-back wings and a vee tail were conducted to determine both the stability and control characteristics of the model longitudinally, laterally, and directionally. Configurations of the model were investigated involving such variables as external fuel tanks, a landing gear, trailing-edge flaps, leading-edge slats, and a range of wing incidences and tail incidences" (p. 1).
Date: March 4, 1949
Creator: Hunton, Lynn W. & Dew, Joseph K.
Item Type: Refine your search to only Report
open access

Vertical Descent and Landing Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in Still Air, TED No. NACA DE 368

Description: "An investigation is being conducted to determine the dynamic stability and control characteristics of a 0.13-scale flying model of Convair XFY-1 vertically rising airplane. This paper presents the results of flight and force tests to determine the stability and control characteristics of the model in vertical descent and landings in still air. The tests indicated that landings, including vertical descent from altitudes representing up to 400 feet for the full-scale airplane and at rates of des… more
Date: March 4, 1954
Creator: Smith, Charles C., Jr. & Lovell, Powell M., Jr.
Item Type: Refine your search to only Report
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