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Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine

Description: Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.
Date: October 3, 1957
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
open access

Method for Estimating Lift Interference of Wing-Body Combinations at Supersonic Speeds

Description: Memorandum presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations adapted to combinations with other than triangular wings. The methods are applied to the prediction of the lit-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.
Date: December 31, 1951
Creator: Nielsen, Jack N. & Kaattari, George E.
Item Type: Refine your search to only Report
open access

Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Description: Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.
Date: July 26, 1955
Creator: Welna, Harry J. & Reilly, Dwight H.
Item Type: Refine your search to only Report
open access

Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane

Description: Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.
Date: April 15, 1958
Creator: Smith, Samuel L., III & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
open access

Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1

Description: Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.
Date: April 24, 1957
Creator: Tomazic, William A.; Kutina, Franklin J., Jr. & Rothenberg, Edward A.
Item Type: Refine your search to only Report
open access

Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor

Description: Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
Date: April 22, 1958
Creator: Kerslake, William R.
Item Type: Refine your search to only Report
open access

Altitude Performance of a Turbojet Engine Using Pentaborane Fuel

Description: Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments a… more
Date: May 20, 1957
Creator: Sivo, Joseph N.
Item Type: Refine your search to only Report
open access

Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87

Description: Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date: May 2, 1958
Creator: Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Item Type: Refine your search to only Report
open access

Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

Description: Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date: October 26, 1956
Creator: Jorgensen, Leland H. & Katzen, Elliott D.
Item Type: Refine your search to only Report
open access

Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel

Description: Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
Date: May 28, 1958
Creator: Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
Item Type: Refine your search to only Report
open access

Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
Date: November 30, 1955
Creator: Keener, Earl R. & Jordan, Gareth H.
Item Type: Refine your search to only Report
open access

Determination of Rate, Area, and Distribution of Impingement of Waterdrops on Various Airfoils From Trajectories Obtained on the Differential Analyzer

Description: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingemen… more
Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01

Description: Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
Date: October 25, 1957
Creator: Morris, Owen G. & Turner, Kenneth L.
Item Type: Refine your search to only Report
open access

Stability and Control Characteristics at Low Speed of a 1/10-Scale Model of MX-1554A Design

Description: Report discussing an investigation of the low-speed stability and control characteristics of a model of the proposed MX-1554A design with a triangular wing and triangular stabilizing surfaces. It also includes the effect of wing incidence, slotted flaps, wing and tail height, external tanks and speed brakes, ground board, spoilers, tip ailerons, flaps, differential tail deflection, and an unswept wing on stability, control, aerodynamic, longitudinal, and lateral characteristics.
Date: 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
open access

Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01

Description: Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
Date: October 16, 1956
Creator: Robinson, Ross B. & Foster, Gerald V.
Item Type: Refine your search to only Report
open access

Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design

Description: Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stabilit… more
Date: November 9, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
open access

Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design

Description: Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
Date: October 29, 1953
Creator: Lockwood, Vernard E.; Luoma, Arvo A. & Solomon, Martin
Item Type: Refine your search to only Report
open access

Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle

Description: Report discussing an investigation of the effect of curved speed brakes on the drag characteristics and longitudinal stability and control characteristics of a model of the MX-1554A with a circular jet nozzle. The speed brakes were tested at several deflections, gaps, and locations in the landing configuration and clean configuration. Results of a lateral- and directional-stability study due to reduction in the vertical tail area are also provided.
Date: January 7, 1954
Creator: Solomon, Martin
Item Type: Refine your search to only Report
open access

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53

Description: Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coe… more
Date: November 30, 1956
Creator: Turner, Kenneth L. & Fournier, Roger H.
Item Type: Refine your search to only Report
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