Technical Report Archive & Image Library (TRAIL) - 11 Matching Results

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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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of a Submerged Air Scoop Utilizing Boundary-Layer Suction to Obtain Increased Pressure Recovery

Description: Report presenting an investigation of a submerged air scoop consisting of a conventional scoop located in a dimple in the fuselage surface at low speeds. Results regarding a study of the basic inlet without suction, a comparison of arrangements using boundary-layer control, the performances of the most desirable configurations with a certain boundary layer, and variation of boundary-layer thickness are provided.
Date: March 17, 1950
Creator: Nichols, Mark R. & Pierpont, P. Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Turbines With Adjustable Stator Blades and Effect of These Turbines on Jet-Engine Performance

Description: From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."
Date: July 17, 1950
Creator: Silvern, David H. & Slivka, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of outside-surface heat-transfer coefficients for cascades of turbine blades

Description: A comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibl… more
Date: July 17, 1950
Creator: Hubbartt, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of an Autopilot Sensitive to Yawing Velocity on the Lateral Stability of the Douglas D-558-II Airplane

Description: A theoretical investigation has been made to determine the effect on the lateral stability of the Douglas D-58-II airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of tire lag in the autopilot were also determined. The flight conditions investigated included landing at sea level, approach condition at 12,000 feet, and cruising at 50,000 feet at Mach numbers of 0.80 and 1.2. The results of the investigation indicated th… more
Date: August 17, 1950
Creator: Gates, Ordway B., Jr. & Sternfield, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.90 to 1.95 of 1/14-Scale Model of the Northrop MX-775B Pilotless Aircraft with Small Body

Description: A flight test was made a t high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/14-scale model of the Northrop MX-775B pilotless aircraft with small small body. The triangular wing of the model had 67.5 deg leading-edge sweep and 15 deg. trailing-edge sweep, The wing airfoil sections were modified NACA 0004 sections. The drag coefficient based on total wing area was 0.0107 at Mach number 1.60. At transonic speeds the maximum drag co… more
Date: August 17, 1950
Creator: Gillespie, Warren, Jr. & Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Wind-Up Turns at Approximately 15,000 Feet and 22,500 Feet

Description: Report presenting time histories of horizontal-tail loads, elevator loads, and deformations on a jet-powered bomber airplane at wind-up turns. Results regarding total tail loads, elevator loads and elevator positions, stabilizer and elevator twist, and fuselage deflection are provided.
Date: August 17, 1950
Creator: McGowan, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of a Ducted-Fan Power Plant Designed for High Output and Good Cruise Fuel Economy

Description: Theoretical analysis of performance of a ducted-fan power plant designed both for high-output, high-altitude operation at low supersonic Mach numbers and for good fuel economy at lower fight speeds is presented. Performance of ducted fan is compared with performance (with and without tail-pipe burner) of two hypothetical turbojet engines. At maximum power, the ducted fan has propulsive thrust per unit of frontal area between thrusts obtained by turbojet engines with and without tail-pipe burner… more
Date: October 17, 1950
Creator: Behun, M.; Rom, F. E. & Hensley, R. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Aerodynamic Characteristics of a Series of Swept Wings Having NACA 65A006 Airfoil Sections (Revised)

Description: Report presenting an investigation to determine the effect of sweep, taper ratio, and aspect ratio on the aerodynamic characteristics of nine semispan wings with NACA 65A006 airfoil sections with and without split flaps. Lift, drag, pitching-moment, and wing-root bending-moment characteristics are presented for a range of Reynolds numbers.
Date: October 17, 1950
Creator: Cahill, Jones F. & Gottlieb, Stanley M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-temperature ignition-delay characteristics of several rocket fuels with mixed acid in modified open-cup-type apparatus

Description: Summaries of low-temperature self-ignition data of various rocket fuels with mixed acid (nitric plus sulfuric) are presented. Several fuels are shown to have shorter ignition-delay intervals and less variation in delay intervals at moderate and sub-zero temperatures than crude N-ethylaniline (monoethylaniline),a rocket fuel in current use.
Date: October 17, 1950
Creator: Miller, Riley O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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