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Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine

Description: Report presenting an investigation of the performance of a diffuser static-pressure-ratio control with a normal shock-positioning limit on a ramjet engine installed in an altitude free-jet facility. Testing occurred at Mach numbers of 2.35 and 2.50, altitudes of 50,000, 60,000 and 65,000 feet, and angles of attack of 0 and 7 degrees. Results regarding the effects of control constants, effects of disturbance size and operating point, effects of flight conditions, and control limitations and poss… more
Date: January 15, 1957
Creator: Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
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

Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01

Description: "A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor pla… more
Date: January 15, 1957
Creator: Kouyoumjian, Walter L.
Item Type: Refine your search to only Report
open access

Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50

Description: Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics. Results regarding performance, longitudinal stability, lateral stability, and strakes are provided.
Date: April 15, 1959
Creator: Church, James D.
Item Type: Refine your search to only Report
open access

Preliminary Free-Jet Performance of XRJ43-MA-3 Ram-Jet Engine at a Mach Number of 2.70

Description: Report discussing an investigation to determine the free-jet performance characteristics of the XRJ43-MA-3 20B3 ram-jet engine at a Mach number of 2.70 at several angles of attack, inlet temperatures, and fuel-air ratios. Information about the inlet supercritical mass-flow ratio, diffuser-outlet Mach number contours, and effect of angle of attack and inlet temperature on engine performance is provided.
Date: April 15, 1955
Creator: Welna, Henry J. & Campbell, Carl 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

Experimental Investigation of Laminar-Boundary-Layer Control on an Airfoil Section Equipped With Suction Slots Located at Discontinuities in the Surface Pressure Distribution

Description: Memorandum presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.
Date: December 15, 1953
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Item Type: Refine your search to only Report
open access

Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Description: From Summary: "The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid … more
Date: March 15, 1954
Creator: von Glahn, Uwe H. & Gray, Vernon H.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine

Description: Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled, dynamic submarine model. Two types of control systems were evaluated. Results regarding the qualitative analysis of the control system, dive paths, equations of motion, and comparison with experimental paths are provided.
Date: April 15, 1954
Creator: McKann, Robert E. & Petynia, William W.
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

Relation of Turbojet Propulsion System Development to the Strategic Bomber Mission

Description: Memorandum presenting a generalized analysis of the effects of turbojet propulsion system development and fuel selection on ability of a strategic bomber to perform desired and minimum missions. The variation of bomber performance using a hydrocarbon, boron, or nuclear fuel is discussed.
Date: August 15, 1956
Creator: Rothrock, Addison M.; Cesaro, Richard S. & Walker, Curtis L.
Item Type: Refine your search to only Report
open access

Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane

Description: Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.
Date: April 15, 1958
Creator: Jones, George W., Jr. & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
open access

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the Douglas D-558-I Airplane for a 1 g Stall, a Speed Run to a Mach Number of 0.90, and a Wind-Up Turn at a Mach Number of 0.86

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented unanalyzed for six spanwise stations on the right wing of the Douglas D-558-I research airplane (BuAero No. 37972). The data were obtained in a 1 g stall at subcritical Mach numbers, in a speed run to a Mach number of 0.90 and in a wind-up turn at a Mach number of 0.86" (p. 1).
Date: December 15, 1950
Creator: Keener, Earl R. & Pierce, Mary
Item Type: Refine your search to only Report
open access

Some Transonic Aerodynamic Characteristics of a Model Similar to the McDonnell F3H-2N Airplane

Description: Report discussing testing of a model of the McDonnell F3H-2N to determine its pitch-up and buffet boundaries and its longitudinal stability and control data obtainable with the pulse-tail technique. Stability was found to be less at low trim angles of attack than at high trim angles of attack up to a point. The buffet boundary was not obtainable through this testing.
Date: May 15, 1956
Creator: Crabill, Norman L. & Jackson, Bruce G.
Item Type: Refine your search to only Report
open access

Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models

Description: Report discussing testing of two models of the Chance Vought Regulus II missile to determine its drag characteristics for a range of Mach numbers. The measured total-drag-coefficient data was extrapolated to external-drag-coefficient data and presented.
Date: July 15, 1954
Creator: Church, James D.
Item Type: Refine your search to only Report
open access

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 4. - Delta-Wing Heavy-Bomber Configuration With Large Store. Mach Number, 1.61

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.6 in which separate forces on a store and on a 60 degree delta-wing-fuselage combination were measured. The configuration in this report simulates a heavy-bomber delta-wing airplane and has a large external symmetrical store that represents a nacelle with a frontal area equivalent to a twin-engine nacelle. more
Date: December 15, 1955
Creator: Morris, Odell A.
Item Type: Refine your search to only Report
open access

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 3 - Swept-Wing Fighter-Bomber Configuration With Large and Small Stores. Mach Number, 1.61

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a fighter-bomber airplane with a large and a small external store.
Date: September 15, 1955
Creator: Smith, Norman F. & Carlson, Harry W.
Item Type: Refine your search to only Report
open access

Liquid Hydrogen as a Jet Fuel for High-Altitude Aircraft

Description: Memorandum presenting a review of some of the analytical and experimental studies of the use of liquid hydrogen as a jet-engine fuel and which show the possible extension of aircraft performance that will follow adequate research and development effort on the problem of its use.
Date: April 15, 1955
Creator: Silverstein, Abe & Hall, Eldon W.
Item Type: Refine your search to only Report
open access

Influence of Boric Oxide Deposition on Turbojet-Engine Operation

Description: Memorandum presenting a study of the effect of oxide-depositing fuels on engine starting, operation, and performance by using a modified production turbojet engine operated using a trimethyl borate azeotrope as a fuel. Results regarding boric oxide deposition, engine operation and performance, effect of turbine-inlet temperature, and dissipation of boric oxide deposits are provided.
Date: February 15, 1957
Creator: Useller, James W.; Burley, Richard R. & Velie, Wallace W.
Item Type: Refine your search to only Report
open access

Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50

Description: Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.
Date: September 15, 1958
Creator: Bowditch, David N. & Anderson, Bernhard H.
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
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