UNT Libraries Government Documents Department - 18 Matching Results

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open access

An Analytical Study of the Effects of Increasing Fin Chord on the Lift and Longitudinal Stability Characteristics of Constant-Span Fin-Body Combinations of Fineness Ratio 14

Description: Report presenting an analysis to determine the effect of increasing the fin-chord length while holding the span constant on the lift and longitudinal static stability of fin-body combinations. Rectangular and triangular fins with spans of 2 and 3 body diameters in combination with a fineness-ratio-14 ogive-cylinder body were tested.
Date: January 17, 1957
Creator: English, Roland D.
open access

Comparison of Locked-Rotor and Windmilling Drag Characteristics of an Axial-Flow-Compressor Type Turbojet Engine

Description: The internal drag of an axial-flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8.
Date: January 17, 1952
Creator: Vincent, K. R.; Huntley, S. C. & Wilsted, H. D.
open access

Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines

Description: For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date: January 17, 1956
Creator: Dugan, James F., Jr.
open access

Distribution of losses behind a compressor rotor as measured by a rotating rake

Description: Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of … more
Date: January 17, 1956
Creator: Godwin, William R.
open access

The effect of body contouring on the longitudinal characteristics at Mach numbers up to 0.92 of a wing-fuselage-tail and several wing-fuselage combinations having sweptback wings of relatively high aspect ratio

Description: Report presenting an investigation to determine the effect of a Küchemann type fuselage modification designed to reduce the interference velocities at the wing-fuselage junctures on the longitudinal characteristics of a wing-fuselage-tail combination and several wing-fuselage combinations. The tests were made through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. Results regarding the 64A wing-fuselage-tail combination, four-digit wing-fuse… more
Date: January 17, 1957
Creator: Sutton, Fred B. & Lautenberger, J. Walter, Jr.
open access

Effect of interstage bleed on rotating stall and blade vibration in a 13-stage axial-flow compressor in a turbojet engine

Description: The compressor case of a 13-stage axial-flow compressor was modified to incorporate air-bleed systems over the fifth and tenth rotor stages. Rotating stall-exited rotor-blade vibrations were measured in the first and second stages at 60 and 68 percent of rated speed, respectively. Either the fifth- or the tenth-stage bleeds satisfactorily eliminated the peak vibratory stresses.
Date: January 17, 1957
Creator: Calvert, Howard F.; Johnson, D. F. & Lucas, J. G.
open access

The effect of tip tanks on the rolling characteristics at high subsonic Mach numbers of a wing having an aspect ratio of 3 with quarter-chord line swept back 35 degrees

Description: Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.
Date: January 17, 1950
Creator: Kuhn, Richard E. & Myers, Boyd C., II
open access

The Effect of Trailing-Edge Bluntness on the Performance of a Small-Scale Supersonic Propeller at Forward Mach Numbers to 0.92

Description: Report presenting testing on two three-blade supersonic propellers in order to determine the effects of trailing-edge bluntness on the performance of a supersonic propeller. Results regarding propeller thrust, power, effects of Mach number and advance ratio on maximum efficiency, and a comparison to a previous test are provided.
Date: January 17, 1956
Creator: Demele, Fred A. & Kolbe, Carl D.
open access

Effects of compressor interstage bleed and adjustable inlet guide vanes on compressor stall characteristics of a high-pressure-ratio turbojet engine at altitude

Description: Report presenting the stall characteristics of the J71-A2(X-29) turbojet engine as determined in an altitude test chamber. When the normal high-speed configuration of bleeds closed, inlet guide vanes open was operated in the low-speed range, the stall-limit line intersected the operating line at 4067 and 4630 rpm. Results regarding compressor performance at steady state and stall and fuel flow at steady state and stall are provided.
Date: January 17, 1956
Creator: Mallett, William E. & Groesbeck, Donald E.
open access

An experimental study of a method for designing fuselage side air inlets for high performance at transonic and low supersonic speeds

Description: Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.
Date: January 17, 1955
Creator: Howell, Robert R. & Trescot, Charles D., Jr.
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Longitudinal Stability and Control Characteristics at Mach Numbers Up to 0.87

Description: Report presenting flight measurements using the Douglas D-558-II airplane in order to determine the longitudinal stability and control characteristics in steady and accelerated flight. Results are given for various flap positions, especially in regards to degrees of instability present.
Date: January 17, 1951
Creator: Sjoberg, S. A.; Peele, James R. & Griffith, John H.
open access

Horizontal-Tail Parameters as Determined From Flight-Test Tail Loads on a Flexible Swept-Wing Jet Bomber

Description: Report presenting an analysis of horizontal-tail loads on a flexible multi-engined jet-propelled swept-wing medium bomber to determine the tail lift-curve slope due to tail angle of attack, tail-lift curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor, and elevator effectiveness factor. The effect of the stabilizer, effects of elevator flexibility, and effects of wing stability are presented.
Date: January 17, 1957
Creator: Aiken, William S., Jr. & Fisher, Raymond A.
open access

Observations of Unsteady Flow Phenomena for an Inclined Body Fitted with Stabilizing Fins

Description: Memorandum presenting an investigation of the variations with Mach number and angle of attack of the dynamic rolling-moment characteristics of a slender body of revolution in combination with a cruciform tail in the 6- by 6-foot supersonic wind tunnel. Oscillograph records of the instantaneous rolling moment of the model were obtained for Mach numbers of 0.90, 1.20, 1.40, 1.53, 1.60, and 1.70 at a constant free-stream Reynolds number. Results regarding dynamic rolling moments and visual flow st… more
Date: January 17, 1952
Creator: Mead, Merrill H.
open access

Preliminary investigation of a fin-actuated jet-vane control system for stabilization of rocket-powered models

Description: Report presenting aerodynamic parameters and operation techniques for a fin-actuated jet-vane system for the stabilization of a rocket-powered model by means of static and flight tests. Static testing was used to obtain lift, hinge moment, and center-of-pressure location of the jet vane, while the longitudinal stability characteristics of a simplified model were determined from the results of a flight test.
Date: January 17, 1951
Creator: Wineman, Andrew R.
open access

A Simplified Method for Assessing the Effect of Steady Rolling on Angle of Attack and Sideslip

Description: Report presenting a method for analyzing the effects of inertia and aerodynamic cross-coupling on the response of airplanes in rolling maneuvers. The method is based on the concept that variations in the calculated steady-state angle of attack and sideslip with roll rate give a measure of the onset and degree of roll coupling. An evaluation of this concept from several different perspectives is also provided.
Date: January 17, 1957
Creator: Schmidt, Stanley F.; Bergrun, Norman R.; Merrick, Robert B. & Matthews, Howard F.
open access

Wind-Tunnel Investigation at High Subsonic Speeds of Spoilers of Large Projection on an NACA 65A006 Wing With Quarter-Chord Line Swept Back 32.6 Degrees

Description: Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the effects of spoiler projection on the aerodynamic characteristics of a wing-fuselage a sweptback quarter-chord line. Lift, drag, rolling, pitching, and yawing moments of the model with a wing panel equipped with 50-percent-semispan inboard spoilers located at the 70-percent-chord line.
Date: January 17, 1952
Creator: Vogler, Raymond D.
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