UNT Libraries Government Documents Department - 16 Matching Results

Search Results

Altitude Test Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 2: Effects of Gutter Width and Blocked Area on Operating Range and Combustion Efficiency

Description: Altitude-test-chamber investigation of effects of flame-holder blocked area and gutter width on performance of 28-inch diameter ram jet at simulated flight Mach number of 2.0 for altitudes from 40,000 to 55,000 feet was conducted at NACA Lewis laboratory. Ten flame holders investigated covered gutter widths from 1.00 to 2.50 inches and blocked areas from 40.5 to 62.0 percent of combustion-chamber area. Gutter width did not appreciably affect combustion efficiency.
Date: November 6, 1950
Creator: Shillito, T. B.; Jones, W. L. & Kahn, R. W.

Dynamic Investigation of Turbine-Propeller Engine Under Altitude Conditions

Description: Memorandum presenting an investigation of the dynamics of a turbine-propeller engine in the altitude wind tunnel employing the frequency-response technique for a range of pressure altitudes form 10,000 to 30,000 feet. The investigation showed that the dynamic responses generalized for pressure altitude over the range of frequencies investigated. Results regarding steady-state characteristics, the linearity investigation, and dynamic characteristics are provided.
Date: December 6, 1950
Creator: Krebs, Richard P.; Himmel, Seymour C.; Blivas, Darnold & Shames, Harold

Effect of aspect ratio on the air forces and moments of harmonically oscillating thin rectangular wings in supersonic potential flow

Description: This report treats the effect of aspect ratio on the air forces and moments of an oscillating flat rectangular wing in supersonic potential flow. The linearized velocity potential for the wing undergoing sinusoidal torsional oscillations simultaneously with sinusoidal vertical translations is derived in the form of a power series in terms of a frequency parameter. The series development is such that the differential equation for the velocity potential is satisfied to the required power of the frequency parameter considered and the linear boundary conditions are satisfied exactly. The method of solution can be utilized for other plan forms, that is, plan forms for which certain steady-state solutions are known.
Date: January 6, 1950
Creator: Watkins, Charles E.

Experimental investigation of thrust augmentation of 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures in compressor

Description: Report presenting an experimental investigation of thrust augmentation of a 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures into the compressor at sea-level, zero-ram conditions. the number, size, and arrangement of interstage nozzles were varied to produce a satisfactory augmentation system of minimum complication. Results regarding the unaugmented performance with and without interstage-injection nozzles, augmented performance with three-stage system, augmented performance with other injection systems, temperature surveys, and engine operation are provided.
Date: April 6, 1950
Creator: Povolny, John H.; Useller, James W. & Chelko, Louis J.

Investigation of the NACA 4-(4)(06)-057-45a and NACA 4-(4)(06)-57-45b Two-Blade Swept Propellers at Forward Mach Numbers to 0.925

Description: Report presenting an investigation of the NACA 4-(4)(06)-057-45A and NACA 4-(4)(06)-057-45B two-blade swept propellers in the high-speed tunnel at blade angles of 25 degrees, 55 degrees, 60 degrees, 65 degrees, and 70 degrees. The swept propellers were compared with straight propellers and were found to be 10 percent more efficient at a forward Mach number of 0.85 for the design blade angle of 60 degrees. Results regarding the effect of forward Mach number, blade sweep, advance ratio, and constant power coefficient on efficiency are also provided.
Date: February 6, 1950
Creator: Delano, James B. & Harrison, Daniel E.

Investigation of the pressure-ratio requirements of the Langley 11-inch hypersonic tunnel with a variable-geometry diffuser

Description: Report presenting tests in the 11-inch hypersonic tunnel at Mach number 6.86 to determine the effectiveness of an adjustable supersonic diffuser without boundary-layer control in reducing the pressure ratios across the system required to maintain supersonic flow. Testing indicated that the pressure ratio could be reduced to about one-third the pressure ratio required for starting.
Date: October 6, 1950
Creator: Bertram, Mitchel H.

Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations

Description: Report discussing an investigation of the longitudinal trim and drag characteristics of two airplane configurations through the transonic speed range. One configuration had a thin straight wing and tail and one had a thicker 35 degree sweptback wing and a 46 degree sweptback tail on the same fuselage-fin arrangement. Information about the control effectiveness and stability and application to a full-scale airplane is also provided.
Date: February 6, 1950
Creator: Parks, James H. & Mitchell, Jesse L.

Low-speed lateral stability and aileron-effectiveness characteristics at a Reynolds number of 3.5 x 10(exp 6) of a wing with leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip

Description: Report presenting results of an investigation of the lateral stability and aileron-effectiveness characteristics of a wing with the leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip. Results regarding the static lateral stability characteristics and aileron characteristics are provided.
Date: July 6, 1950
Creator: Lange, Roy H. & McLemore, Huel C.

Low-Speed Static Stability Characteristics of a Canard Model with a 45 Degree Sweptback Wing and a 60 Degree Triangular Horizontal Control Surface

Description: Memorandum presenting an investigation of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. Results regarding longitudinal stability and control and lateral stability and control are provided.
Date: September 6, 1950
Creator: Draper, John W.

Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Bevelled-Trailing-Edge Flap and Trim Tab by the NACA Wing-Flow Method

Description: The third investigation in a series to determine the fundamental characteristics of trailing-edge controls at transonic speeds. This particular report uses a 35 degree sweptback untapered airfoil model with an aspect ratio of 3 and a flap with a bevelled trailing edge with a trailing-edge angle of 23 degrees. Results regarding lift, pitching-moment, and hinge-moment characteristics are provided.
Date: January 6, 1950
Creator: Johnson, Harold I. & Brown, B. Porter

Wind-Tunnel Investigation of the Low-Speed Longitudinal and Lateral Control Characteristics of a Triangular-Wing Model of Aspect Ratio 2.31 Having Constant-Chord Control Surfaces

Description: Report presenting a wind-tunnel investigation to determine the low-speed longitudinal and lateral control characteristics of a model with a triangular wing with NACA 65(06)-006.5 airfoil sections, aspect ratio 2.31, and constant-chord control surfaces. The values of the hinge-moment parameters were found to be of somewhat greater magnitude than would be expected on unswept wings with the same aspect ratio.
Date: September 6, 1950
Creator: Wolhart, Walter D. & Michael, William H., Jr.