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Notes on the prediction of shock-induced boundary-layer separation

Description: The present status of available information relative to the prediction of shock-induced boundary-layer separation is discussed. Experimental results showing the effects of Reynolds number and Mach number on the separation of both laminar and turbulent boundary layer are given and compared with available methods for predicting separation. The flow phenomena associated with separation caused by forward-facing steps, wedges, and incident shock waves are discussed. Applications of the flat-plate da… more
Date: September 16, 1953
Creator: Lange, Roy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Appraisal of Ferrocene as an Igniting Agent for JP-4 Fuel and Fuming Nitric Acid

Description: From Summary: "A preliminary experimental study was made of the properties of ferrocene as a solute and as a suspension in JP-4 fuel, and of the ignition delays of ferrocene - JP-4 mixture with A.F. specification 14104 white fuming nitric acid (WFNA). The investigation covered concentrations of 4 to 10 percent by weight ferrocene, and a temperature range of -40 to 80 F. The solubility of ferrocene in JP-4 is about 5 percent at room temperature and about 1 percent (extrapolated) at -80 F. The so… more
Date: August 25, 1953
Creator: Miller, Riley O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Transient Performance Data on the J73 Turbojet Engine, 3: Altitude, 45,000 Feet

Description: "A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits encountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engine parameters with changes in engine fuel flow. The data presented in this report are for step and ramp changes in fuel flow at an altitude of 45,000 feet and flight Mach numbers of 0 and 0.8" (p. 1).
Date: July 16, 1953
Creator: McAulay, John E. & Wallner, Lewis E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Longitudinal Stability Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

Description: "A low-speed investigation was made of a 1/6-scale model of the Republic XF-84H airplane. The model had a single tractor propeller and a 40 degree swept wing of aspect ratio 3.45. This investigation was undertaken to provide information on the effects of propeller operation on longitudinal stability characteristics for the XF -84H airplane and to provide an indication of slipstream effects that might be encountered on similar swept-wing configurations" (p. 1).
Date: June 12, 1953
Creator: Sleeman, William C., Jr. & Byrnes, Andrew L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude Performance and Operational Characteristics of YJ71-A-7 Turbojet Engine

Description: "Altitude performance of a YJ71-A-7 turbojet engine, with afterburner inoperative, was determined in the NACA Lewis altitude wind tunnel over a wide range of flight conditions. Engine speed and exhaust-nozzle area were controlled independently during this investigation. The variation of corrected values of air flow, net thrust, and fuel flow with corrected engine speed was not defined by a single curve with changes in altitude at given flight Mach number" (p. 1).
Date: June 18, 1953
Creator: Smith, Ivan D.; Leonard, Charles V., Jr. & Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model

Description: Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data.
Date: May 14, 1953
Creator: Blanchard, Willard S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Determination of Drag of Normal-Shock Nose Inlets With Various Cowling Profiles at Mach Numbers From 0.9 to 1.5

Description: External-drag data are presented for normal-shock nose inlets with NACA 1-series, parabolic, and conic cowling profiles. The tests were made at an angle of attack of 0 degrees by using rocket-propelled models in free flight at Mach numbers from 0.9 to 1.5. The Reynolds number based on body maximum diameter varied from 2.5 x 10 sup 6 to 5.5 x 10 sup 6.
Date: September 8, 1953
Creator: Sears, R. I.; Merlet, C. F. & Putland, L. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds

Description: From Summary: "A method is presented for calculating the lift and centers of pressure of wing-body and wing-body-tail combinations at subsonic, transonic, and supersonic speeds. A set of design charts and a computing table are presented which reduce the computations to routine operations. Comparison between the estimated and experimental characteristics for a number of wing-body and wing-body-tail combinations shows correlation to within + or - 10 percent on lift and to within about + or - 0.02… more
Date: July 8, 1953
Creator: Pitts, William C.; Nielsen, Jack N. & Kaattari, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Equations, Tables, and Charts for Compressible Flow

Description: "This report, which is a revision and extension of NACA-TN-1428, presents a compilation of equations, tables, and charts useful in the analysis of high-speed flow of a compressible fluid. The equations provide relations for continuous one-dimensional flow, normal and oblique shock waves, and Prandtl-Meyer expansions for both perfect and imperfect gases. The tables present useful dimensionless ratios for continuous one-dimensional flow and for normal shock waves as functions of Mach number for a… more
Date: 1953
Creator: Ames Research Staff
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical combustion performance of several high-energy fuels for ramjet engines

Description: An analytical evaluation of the air and fuel specific-impulse characteristics of magnesium, magnesium octene-1 slurries, aluminum, aluminum octene-1 slurries, boron, boron octene-1 slurries, carbon, hydrogen, alpha-methylnaphthalene, diborane, pentaborane, and octene-1 is presented. While chemical equilibrium was assumed in the combustion process, the expansion was assumed to occur at fixed composition.
Date: September 14, 1953
Creator: Tower, Leonard K.; Breitwieser, Roland & Gammon, Benson E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

Description: From Summary: "A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer."
Date: April 28, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects

Description: "A solution to second order in thickness is derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency. For arbitrary frequencies, the method of solution for any specific profile is indicated, and the explicit solution derived for a single wedge" (p. 611).
Date: April 20, 1953
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Calculation of Pressure on Slender Airplanes in Subsonic and Supersonic Flow

Description: "Under the assumption that a wing, body, or wing-body combination is slender or flying at near sonic velocity, expressions are given which permit the calculation of pressure in the immediate vicinity of the configuration. The disturbance field, in both subsonic and supersonic flight, is shown to consist of two-dimensional disturbance fields extending laterally and a longitudinal field that depends on the streamwise growth of cross-sectional area. A discussion is also given of couplings, between… more
Date: November 28, 1953
Creator: Heaslet, Max A. & Lomax, Harvard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of Rocket-Model Tests at Zero Lift of the Northrop MX-775B Missile Configuration from Mach Numbers of 0.9 to 1.8

Description: Flight tests were conducted between Mach numbers of 0.9 and 1.8 over a Reynolds number range of 9(exp 6) to 30(exp 6) to determine the zero-lift drag and some rolling-effectiveness characteristics of the Northrop MX -775B missile with small and large body. The MX-775B is a proposed long range, supersonic, ground-to-ground missile having an arrow wing with 67.5 degree leading-edge sweep, 15 deg trailing-edge sweep, and a modified NACA 0004 airfoil section. The configuration has no horizontal tai… more
Date: October 1, 1953
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impingement of water droplets on wedges and double-wedge airfoils at supersonic speeds

Description: "An analytical solution has been obtained for the equations of motion of water droplets impinging on a wedge in a two-dimensional supersonic flow field with a shock wave attached to the wedge. The closed-form solution yields analytical expressions for the equation of the droplet trajectory, the local rate of impingement and the impingement velocity at any point on the wedge surface, and the total rate of impingement. The analytical expressions are utilized to determine the impingement on the fo… more
Date: April 21, 1953
Creator: Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method for studying helicopter longitudinal maneuver stability

Description: A theoretical analysis of helicopter maneuver stability is made and the results are compared with experimental results for both a single and a tandem rotor helicopter. Techniques are described for measuring in flight the significant stability derivatives for use with the theory to aid in design studies of means for achieving marginal maneuver stability for a prototype helicopter.
Date: October 1953
Creator: Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transverse Vibrations of Hollow Thin-Walled Cylindrical Beams

Description: "The variational principle, differential equations, and boundary conditions considered appropriate to the analysis of transverse vibrations of hollow thin-walled cylindrical beams are shown. General solutions for the modes and frequencies of cantilever and free-free cylindrical beams of arbitrary cross section but of uniform thickness are given. The combined influence of the secondary effects of transverse shear deformation, shear lag, and secondary effects of transverse shear deformation, shea… more
Date: 1953
Creator: Budiansky, Bernard & Kruszewski, Edwin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Photographic investigation of combustion in a two-dimensional transparent rocket engine

Description: Motion pictures at camera speeds up to 3000 frames per second were taken of the combustion of liquid oxygen and gasoline in a 100-pound thrust rocket engine. The effect of seven methods of propellant injection on the uniformity of combustion was investigated. The flame front was generally found to extend to the injector faces and all the injection systems showed considerable nonuniformity of combustion. Pressure vibration records indicated combustion vibrations that corresponded to resonant-cha… more
Date: May 22, 1953
Creator: Bellman, Donald R.; Humphrey, Jack C. & Male, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Description: "An investigation has been made at high subsonic speeds of the aerodynamic characteristics in pitch and sideslip of a 1/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for s… more
Date: August 18, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design

Description: The performance of a 13-stage development compressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised… more
Date: April 9, 1953
Creator: Hatch, James E.; Lucas, James G. & Finger, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An airborne indicator for measuring vertical velocity of airplanes at wheel contact

Description: From Introduction: "The purpose of this paper is to describe one of the means developed for measuring this quantity on a given airplane type- a trailing arm with wheel. A prototype velocity indicator was tested in the Langley impact basin to determine its accuracy. A description of the operation of this type of vertical-velocity indicator, the results of the impact-basin and flight tests, and general evaluation of the indicator are presented herein."
Date: February 1953
Creator: Dreher, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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