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NACA Research Memorandums
5,157
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4,107
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1,438
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1,423
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1,263
NACA Advanced Restricted Reports
533
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338
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The Theory of the Pitot and Venturi Tubes, Part 2
Report discussing several aspects of pitot and venturi tubes, including the energy equation for steady adiabatic flow, introduction of mean speed into the energy equation, isentropic flow of an ideal gas, the theory of the pitot tube, and the theory of the venturi meter.
Date:
1989?
Creator:
Buckingham, E.
Object Type:
Report
System:
The UNT Digital Library
Flow and Drag Formulas for Simple Quadrics
The pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid are calculated. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. Formulas for the velocity at all points of the flow field are given. Pressure and pressure drag are discussed for a sphere, a round cylinder, the elliptic cylinder, the prolate and oblate spheroid, and the circular disk. The velocity and pressure in an oblique flow are examined.
Date:
December 1979
Creator:
Zahm, A. F.
Object Type:
Report
System:
The UNT Digital Library
Flow and Force Equations for a Body Revolving in a Fluid
A general method for finding the steady flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle is described. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. The application of the steady flow method for calculating the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms is presented and graphs those quantities for the latter forms.
Date:
December 1979
Creator:
Zahm, A. F.
Object Type:
Report
System:
The UNT Digital Library
Graphic Construction of Joukowski Wings
Memorandum presenting a description and formulas that can be used to plot the cross-sectional outline of a Joukowski wing.
Date:
1979-12?
Creator:
Trefftz, E.
Object Type:
Report
System:
The UNT Digital Library
The Minimum Induced Drag of Aerofoils
Equations are derived to demonstrate which distribution of lifting elements result in a minimum amount of aerodynamic drag. The lifting elements were arranged (1) in one line, (2) parallel lying in a transverse plane, and (3) in any direction in a transverse plane. It was shown that the distribution of lift which causes the least drag is reduced to the solution of the problem for systems of airfoils which are situated in a plane perpendicular to the direction of flight.
Date:
1979-12?
Creator:
Munk, Max M.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Forces on Airship Hulls
The new method for making computations in connection with the study of rigid airships, which was used in the investigation of Navy's ZR-1 by the special subcommittee of the National Advisory Committee for Aeronautics appointed for this purpose is presented. The general theory of the air forces on airship hulls of the type mentioned is described and an attempt was made to develop the results from the very fundamentals of mechanics.
Date:
1979%
Creator:
Munk, Max M.
Object Type:
Report
System:
The UNT Digital Library
Applications of Modern Hydrodynamics to Aeronautics Part 1: Fundamental Concepts and the Most Important Theorems. Part 2: Applications
A discussion of the principles of hydrodynamics of nonviscous fluids in the case of motion of solid bodies in a fluid is presented. Formulae are derived to demonstrate the transition from the fluid surface to a corresponding 'control surface'. The external forces are compounded of the fluid pressures on the control surface and the forces which are exercised on the fluid by any solid bodies which may be inside of the control surfaces.
Date:
1979%
Creator:
Prandtl, L.
Object Type:
Report
System:
The UNT Digital Library
Smoking Characteristics of Various Fuels as Determined by Open-Cup and Laboratory-Burner Smoke Tests
Report discussing tests in a combustion chamber to obtain smoking characteristics data on a variety of hydrocarbon fuels. Details about the smoking tendencies and burning rates of the fuels in uncontrolled and controlled tests are provided.
Date:
{1945-06,1945-09}
Creator:
Ebersole, Earl R. & Barnett, Henry C.
Object Type:
Report
System:
The UNT Digital Library
Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane
"An investigation has been made of a 1/28-scale model of the Grumman A-6A airplane in the Langley spin tunnel. The erect spin and recovery characteristics of the model were determined for the flight design gross weight loading and for a loading with full internal fuel and empty external wing fuel tanks. The effects of extending slats and deflecting flaps were investigated" (p. 1).
Date:
July 1964
Creator:
Lee, Henry A. & Healy, Frederick M.
Object Type:
Report
System:
The UNT Digital Library
Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane
"An investigation has been made in the Langley spin tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried" (p. 1).
Date:
June 1964
Creator:
Lee, Henry A.
Object Type:
Report
System:
The UNT Digital Library
Some Research on the Lift and Stability of Wing-Body Combinations
The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
Date:
July 2, 1959
Creator:
Purser, Paul E. & Fields, E. M.
Object Type:
Report
System:
The UNT Digital Library
An Analytical Evaluation of the Effects of an Aerodynamic Modification and of Stability Augmenters on the Pitch Behavior and Probable Pilot Opinion of Two Current Fighter Airplanes
Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.
Date:
April 21, 1959
Creator:
Sadoff, Melvin & Stewart, John D.
Object Type:
Report
System:
The UNT Digital Library
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
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.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of the X-15/B-52 combination
Report presenting an investigation to determine the carry loads and mutual aerodynamic interference effects from high-speed wind-tunnel tests and the drop characteristics of the X-15 through the B-52 flow field from low-speed dynamic-model drop tests and six-degree-of-freedom calculations. The X-15 installation was found to increase drag at cruise conditions by approximately 15 percent.
Date:
1959
Creator:
Alford, William J., Jr. & Taylor, Robert T.
Object Type:
Report
System:
The UNT Digital Library
Boundary-Layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6
"Measurements are presented for pressure gradients induced by a laminar boundary layer on a flat plate in air at a Mach number of 9.6 and for the drag of thin wings at a Mach number of about 6.8 and zero angle of attack. The pressure measurements at a Mach number of 9.6 were made in the presence of substantial heat transfer from the boundary layer to the plate surface. The measured pressure distribution o the surface of the plate was predicted with good accuracy by a modification to insulated-plate displacement theory which allows for the effect of the heat transfer and temperature gradient along the surface on the boundary-layer displacement thickness" (p. 1).
Date:
1959
Creator:
Bertram, Mitchel H.
Object Type:
Report
System:
The UNT Digital Library
Forty-Fourth Annual Report of the National Advisory Committee for Aeronautics Administrative Report Including Technical Reports Nos. 1342 to 1392
"In accordance with act of Congress, approved March 3, 1915, as amended (U.S.C., title 50, .sw 151), which established the National Advisory Committee for Aeronautics, the Committee submits its Forty-fourth Annual Report for the fiscal year 1958. This is the Committee's final report to the Congress. The National Aeronautics and Space Act of 1958 (Public Law 85-568) provides in section 301 that the NACA "shall cease to exist" and "all functions, powers, duties, and obligations, and all real and personal property, personnel (other than members of the Committee), funds, and records of the NACA shall be transferred to the National Aeronautics and Space Administration" (p. ix).
Date:
1959
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine
Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydrogen injection, and oxygen atomization by two impinging jets with variations in hydrogen injection.
Date:
September 30, 1958
Creator:
Heidmann, M. F. & Baker, Louis, Jr.
Object Type:
Report
System:
The UNT Digital Library
Off-Design Performance of Divergent Ejectors
Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.
Date:
September 30, 1958
Creator:
Beheim, Milton A.
Object Type:
Report
System:
The UNT Digital Library
Off-Design Performance of Divergent Ejectors
"The off-design performance of fixed- and of variable-geometry divergent ejectors was investigated. The ejectors, which were designed for turbojet operation at Mach 3, were investigated in the Mach number range of 0.8 to 2. The performance of a fixed-geometry ejector with high secondary-flow rates was competitive with that of more complex variable-geometry ejectors. Variable-geometry ejectors with compromises to reduce mechanical complexity produced performance reasonably close to that of an ideal variable ejector" (p. 1).
Date:
September 30, 1958
Creator:
Beheim, Milton A.
Object Type:
Report
System:
The UNT Digital Library
Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8
Report presenting some experimental free-flight data at a range of Mach numbers regarding the normal force and pitching effectiveness of several small pulse rockets in the fuselage of a rocket propelled model. Wing-damping data was also obtained from the wing bending response to the pulse-rocket excitations, and longitudinal stability data was determined from the model response. Results regarding pulse-rocket effectiveness, wing damping, and model stability data are provided.
Date:
September 30, 1958
Creator:
Martz, C. William
Object Type:
Report
System:
The UNT Digital Library
Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination
Report presenting an exploratory study of the screaming tendency of the gaseous-hydrogen-liquid-oxygen propellant combination in 200-pound-thrust rocket engines. Four injector classes in a total of 12 different configurations were tested in a variety of chamber lengths over the usable mixture-ratio range. Results regarding acoustic oscillations, unclassified oscillations, driving and damping mechanisms, and effects of screaming on heat transfer are provided.
Date:
September 30, 1958
Creator:
Baker, Louis, Jr. & Steffen, Fred W.
Object Type:
Report
System:
The UNT Digital Library
Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
Memorandum presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process, which was inhibited by water vapor from compressor-inlet injection. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the effects of hydrogen injection on afterburner performance and effect of aluminum trimethyl afterburner fuel additive on performance are provided.
Date:
September 30, 1958
Creator:
Wanhainen, John P. & Sivo, Joseph N.
Object Type:
Report
System:
The UNT Digital Library
Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
Report presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the afterburner efficiency, afterburner stability limits, afterburner-outlet total temperature, and an application of the results to other systems are provided.
Date:
September 30, 1958
Creator:
Wanhainen, John P. & Sivo, Joseph N.
Object Type:
Report
System:
The UNT Digital Library
Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield
Report discussing a study of the effects of puncturing the heat shield of an intercontinental-ballistic-missile warhead by small projectiles. Calculations were created for both rod and sphere projectiles and experimental testing was performed on a missile model with holes drilled in the heat shield. The possibility that a projectile could have enough energy to cause mechanical damage to the interior of the warhead is also presented.
Date:
September 29, 1958
Creator:
Strass, H. K. & Goodman, V. M.
Object Type:
Report
System:
The UNT Digital Library