UNT Libraries Government Documents Department - 189 Matching Results

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Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations

Description: From Introduction: "This report makes further comparisons of the theoretical computing method with available experimental results, showing effects of wing plan-form changes, and the effect of an airfoil-section change on a wing of given plan form."
Date: August 15, 1955
Creator: Holdaway, George H.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing with a spanwise variation in thickness ratio. The wings investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: January 15, 1952
Creator: Morrison, William D., Jr. & Fournier, Paul G.
Item Type: Refine your search to only Report
open access

Aerodynamic Loads on an External Store Adjacent to a 45 Degree Sweptback Wing at Mach Numbers From 0.70 to 1.96, Including an Evaluation of Techniques Used

Description: "Aerodynamic forces and moments have been obtained in the Langley 9- by 12-inch blowdown tunnel on an external store and on a 45 degree swept-back wing-body combination measured separately at Mach numbers from 0.70 to 1.96. The wing was cantilevered and had an aspect ratio of 4.0; the store was independently sting-mounted and had a Douglas Aircraft Co. (DAC) store shape. The angle of attack range was from -3 degrees to 12 degrees and the Reynolds number (based on wing mean aerodynamic chord) va… more
Date: November 15, 1955
Creator: Guy, Lawrence D. & Hadaway, William M.
Item Type: Refine your search to only Report
open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

Description: Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.
Date: August 15, 1949
Creator: Jones, J. Lloyd & Demele, Fred A.
Item Type: Refine your search to only Report
open access

Altitude Free-Jet Investigation of Dynamics of a 28-Inch-Diameter Ram-Jet Engine

Description: From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."
Date: January 15, 1957
Creator: Wentworth, Carl B.; Dunbar, William R. & Crowl, Robert J.
Item Type: Refine your search to only Report
open access

Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine

Description: From Introduction: "Altitude-chamber and wind-tunnel investigations of the performance of turbojet engines such as those reported in references 1 to 4 have shown that the conventional correction factors fail to generalize the engine performance variables at high altitudes. An investigation was therefore made at the NACA Lewis laboratory to determine the altitude performance of the J33-A-23 turbojet engine and to demonstrate the magnitude of departure of actual altitude performance from that pre… more
Date: May 15, 1951
Creator: Wilsted, H. D. & Grey, R. E.
Item Type: Refine your search to only Report
open access

Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free-Jet Facility at Mach Number 3.0

Description: Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.
Date: June 15, 1953
Creator: Smolak, George R. & Wentworth, Carl B.
Item Type: Refine your search to only Report
open access

Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free Jet Facility at Mach Number 3.0

Description: Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.
Date: June 15, 1953
Creator: Smolak, George R. & Wentworth, Carl B.
Item Type: Refine your search to only Report
open access

Altitude performance of compressor, turbine, and combustor components of 600-B9 turbojet engine

Description: From Introduction: "The purpose of this report is (1) to describe the performance of each component over a range of altitudes, (2) to show the effect of flight conditions on operating point of each component, and (3) to summarize briefly the effects of changes in component performance with flight condition on the over-all engine performance."
Date: March 15, 1954
Creator: Prince, William R. & Wile, Dorwin B.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine

Description: From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date: December 15, 1950
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of J47 turbojet-engine performance

Description: From Introduction: "Data are presented in graphical form to show the engine performance over a range of altitudes from 5000 to 50,000 feet and flight Mach numbers from 0.21 to 0.97. Curves are presented to show the windmilling characteristics of the engine. All engine performance data obtained in the investigation are also presented in tabular form."
Date: November 15, 1949
Creator: Conrad, E. William & Sobolewski, Adam E.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine IV: performance with tail-pipe burning and water injection

Description: From Introduction: "Thrust augmentation of an axial-flow-type turbojet engine by burning fuel in the tail pipe is discussed in references 1 to 3. Thrust augmentation of the same turbojet engine by water injection at the compressor inlet is reported in reference 4."
Date: June 15, 1948
Creator: Dietz, Robert O., Jr.; Wishnek, George & Kuenzig, John K.
Item Type: Refine your search to only Report
open access

Analysis of the Effects of Various Mass, Aerodynamic, and Dimensional Parameters on the Dynamic Lateral Stability of the Douglas D-558-2 Airplane

Description: Report presenting an investigation of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 airplane. Results regarding an airplane with the flaps and gear retracted, airplane at sea level with flaps deflected 50 degrees and landing gear lowered, and effect of assumed modifications to airplane are provided.
Date: April 15, 1949
Creator: Queijo, M. J. & Michael, W. H., Jr.
Item Type: Refine your search to only Report
open access

An Analytic Study of Turbojet Engine Thrust Augmentation With Liquid Hydrogen, Pentaborane, Magnesium Slurry, and JP-4 Afterburner Fuels and a 220-Second Impulse Rocket

Description: Memorandum presenting a computation and comparison of the thrust augmentation and accompanying total fuel flow for four afterburner fuels and a rocket. Four turbojet engines burning JP-4 primary fuel and several operating conditions were selected for the analyses.
Date: August 15, 1956
Creator: Morris, James F.
Item Type: Refine your search to only Report
open access

Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail

Description: Report presenting an investigation of the effect of reducing the static stability by a practical center-of-gravity shift in swept-wing airplanes of low aspect ratio with no horizontal tail. Results regarding relocating the center of gravity, the effect of lift due to elevator deflection, the effect of increased total elevator effectiveness, and the effect of response characteristics over long time periods are provided.
Date: October 15, 1954
Creator: Stone, Ralph W., Jr.
Item Type: Refine your search to only Report
open access

Applications of power spectral analysis methods to maneuver loads obtained on jet fighter airplanes during service operations

Description: Report presenting power spectral densities of normal load factor obtained for two service operational training flights of a Republic F-84G airplane and three service operational training flights of a North American F-86A airplane in order to indicate the load-factor frequency content and possible uses of power spectral methods in analyzing maneuver load data. Results regarding the spectra of the two different planes, an analytical representation of maneuver load spectrum, and probability distri… more
Date: January 15, 1957
Creator: Mayer, John P. & Hamer, Harold A.
Item Type: Refine your search to only Report
open access

An assessment of the airplane drag problem at transonic and supersonic speeds

Description: Report presenting the airplane drag problem at transonic and supersonic speeds. The area rule is shown to be a powerful tool that provides guidance for designers in selecting aerodynamic features compatible with low wave drag. Analytical methods have been developed that permit quantitative evaluation of the wave-drag level likely to be experienced with a given design.
Date: July 15, 1954
Creator: Donlan, Charles J.
Item Type: Refine your search to only Report
open access

Calculation of Aerodynamic Forces on a Propeller in Pitch or Yaw

Description: Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.
Date: February 15, 1949
Creator: Crigler, John L. & Gilman, Jean, Jr.
Item Type: Refine your search to only Report
open access

Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Description: Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain opera… more
Date: August 15, 1947
Creator: Dittrich, Ralph T.
Item Type: Refine your search to only Report
open access

Combustion performance evaluation of magnesium-hydrocarbon slurry blends in a simulated tail-pipe burner

Description: Report presenting an experimental investigation to determine the combustion properties of several magnesium-hydrocarbon slurry blends and to indicate the feasibility of the application of slurry-type fuels to high-speed aircraft. High-concentration magnesium slurries showed large improvements in combustion stability and tail-pipe-burner net thrust.
Date: May 15, 1951
Creator: Tower, Leonard K. & Branstetter, J. Robert
Item Type: Refine your search to only Report
open access

Comparison of calculated and experimental temperatures of water-cooled turbine blades

Description: Report presenting analytical methods to calculate average and local turbine-blade temperatures. The temperatures were compared with experimental data obtained in a forced-convection, water-cooled aluminum turbine over a range of turbine-inlet-gas temperatures and coolant-mass velocities. Results regarding comparison of calculated and experimental aluminum turbine blade temperatures, comparison of calculated and experimental stationary-blade temperatures, stationary water-cooled blade operating … more
Date: July 15, 1952
Creator: Schum, Eugene F.; Freche, John C. & Stelpflug, William J.
Item Type: Refine your search to only Report
open access

Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches

Description: Memorandum presenting a calculation of the amount of possible correction for coordinated turns with limited bank angle and level sideslips for a large transport airplane, the C-54D. The results indicate that for all instances from the end of the runway, coordinated turns are the more effective maneuver.
Date: December 15, 1949
Creator: Faber, Stanley
Item Type: Refine your search to only Report
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