Allen, H. Julian
Overview
Works:  42 works in 89 publications in 1 language and 214 library holdings 

Roles:  Author, Contributor 
Publication Timeline
.
Most widely held works about
H. Julian Allen
 Harry Julian Allen : 19101977 by Nicholas J Hoff( )
 Harry J. Allen( )
Most widely held works by
H. Julian Allen
Prospects for obtaining aerodynamic heating results from analysis of meteor flight data by
H. Julian Allen(
Book
)
3 editions published in 1964 in English and held by 32 WorldCat member libraries worldwide
3 editions published in 1964 in English and held by 32 WorldCat member libraries worldwide
Effect on meteor flight of cooling by radiation and ablation by
H. Julian Allen(
Book
)
2 editions published in 1965 in English and held by 19 WorldCat member libraries worldwide
2 editions published in 1965 in English and held by 19 WorldCat member libraries worldwide
A method for computing luminous efficiencies from meteor data by
Barrett S Baldwin(
Book
)
3 editions published in 1968 in English and held by 18 WorldCat member libraries worldwide
3 editions published in 1968 in English and held by 18 WorldCat member libraries worldwide
Pressure distribution and some effects of viscosity on slender inclined bodies of revolution by
H. Julian Allen(
Book
)
5 editions published in 1950 in English and held by 14 WorldCat member libraries worldwide
The simplified solution for the pressure distribution of slender inclined bodies of revolution is developed. The solution should be suitable for bodies of high fineness ratio even at low supersonic speeds, provided the angle of attack is small. Comparison with lowspeed experimental results indicates that the observed flow separation phenomena can be explained in terms of the calculated pressure distributions together with the theory of oblique viscous flows
5 editions published in 1950 in English and held by 14 WorldCat member libraries worldwide
The simplified solution for the pressure distribution of slender inclined bodies of revolution is developed. The solution should be suitable for bodies of high fineness ratio even at low supersonic speeds, provided the angle of attack is small. Comparison with lowspeed experimental results indicates that the observed flow separation phenomena can be explained in terms of the calculated pressure distributions together with the theory of oblique viscous flows
A comparative analysis of the performance of longrange hypervelocity vehicles by
Alfred J Eggers(
Book
)
8 editions published between 1957 and 1959 in English and held by 9 WorldCat member libraries worldwide
8 editions published between 1957 and 1959 in English and held by 9 WorldCat member libraries worldwide
A comparative analysis of the performance of longrange hypervelocity vehicles by
A. J Eggers(
)
2 editions published in 1957 in English and held by 9 WorldCat member libraries worldwide
Longrange hypervelocity vehicles are studied in terms of their motion in powered flight, and their motion and aerodynamic heating in unpowered flight. Powered flight is analyzed for an idealized propulsion system which rather closely approaches presentday rocket motors. Unpowered flight is characterized by a return to earth along a ballistic, skip, or glide trajectory. Only those trajectories are treated which yield the maximum range for a given velocity at the end of powered flight. Aerodynamic heating is treated in a manner similar to that employed previously by the senior authors is studying ballistic missiles (NACA RM A53D28), with the exception that radiant as well as convective heat transfer is considered in connection with glide and skip vehicles
2 editions published in 1957 in English and held by 9 WorldCat member libraries worldwide
Longrange hypervelocity vehicles are studied in terms of their motion in powered flight, and their motion and aerodynamic heating in unpowered flight. Powered flight is analyzed for an idealized propulsion system which rather closely approaches presentday rocket motors. Unpowered flight is characterized by a return to earth along a ballistic, skip, or glide trajectory. Only those trajectories are treated which yield the maximum range for a given velocity at the end of powered flight. Aerodynamic heating is treated in a manner similar to that employed previously by the senior authors is studying ballistic missiles (NACA RM A53D28), with the exception that radiant as well as convective heat transfer is considered in connection with glide and skip vehicles
A study of effects of viscosity on flow over slender inclined bodies of revolution by
H. Julian Allen(
Book
)
4 editions published in 1951 in English and held by 8 WorldCat member libraries worldwide
4 editions published in 1951 in English and held by 8 WorldCat member libraries worldwide
The Effect of compressibility on the growth of the laminar boundary layer on lowdrag wings and bodies by
H. Julian Allen(
Book
)
2 editions published in 1947 in English and held by 7 WorldCat member libraries worldwide
The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundarylayer thickness and the boundarylayer Reynolds number, which is a measure of the boundarylayer stability, for airfoils and bodies of revolution
2 editions published in 1947 in English and held by 7 WorldCat member libraries worldwide
The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundarylayer thickness and the boundarylayer Reynolds number, which is a measure of the boundarylayer stability, for airfoils and bodies of revolution
Thirtyseventh annual report of the National Advisory Committee for Aeronautics. 1951. Including technical reports nos. 1003
to 1058 by
United States(
)
2 editions published in 1952 in English and held by 7 WorldCat member libraries worldwide
2 editions published in 1952 in English and held by 7 WorldCat member libraries worldwide
A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds by
H. Julian Allen(
Book
)
6 editions published between 1957 and 1958 in English and held by 7 WorldCat member libraries worldwide
6 editions published between 1957 and 1958 in English and held by 7 WorldCat member libraries worldwide
Fortyfourth annual report of the National Advisory Committee for Aeronautics, 1958. Administrative report including technical
reports Nos. 1342 to 1392. (Final report) by
United States(
)
2 editions published in 1959 in English and held by 7 WorldCat member libraries worldwide
2 editions published in 1959 in English and held by 7 WorldCat member libraries worldwide
Wall interference in a twodimensionalflow wind tunnel with consideration of the effect of compressibility by
H. Julian Allen(
Book
)
5 editions published in 1944 in English and held by 6 WorldCat member libraries worldwide
Theoretical tunnelwall corrections are derived for an airfoil of finite thickness and camber in a twodimensionalflow windtunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid, and is based upon the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. Consideration is given to the phenomenon of choking at high speeds and its relation to tunnelwall corrections. The theoretical results are compared with the small amount of lowspeed experimental data available and the agreement is seen to be satisfactory, even for relatively large values of the chordheight ratio
5 editions published in 1944 in English and held by 6 WorldCat member libraries worldwide
Theoretical tunnelwall corrections are derived for an airfoil of finite thickness and camber in a twodimensionalflow windtunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid, and is based upon the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. Consideration is given to the phenomenon of choking at high speeds and its relation to tunnelwall corrections. The theoretical results are compared with the small amount of lowspeed experimental data available and the agreement is seen to be satisfactory, even for relatively large values of the chordheight ratio
A Simplified method for the calculation of airfoil pressure distribution by
H. Julian Allen(
Book
)
3 editions published in 1939 in English and held by 6 WorldCat member libraries worldwide
Baseprofile pressurecoefficient distributions for the usual N.A.C.A. family of airfoils, which are also suitable for several other commonly employed airfoils, are included in tabular form. With these tabulated baseprofile pressures and the computed normalforce distributions, pressure distributions adequate for most engineering purposes can be obtained
3 editions published in 1939 in English and held by 6 WorldCat member libraries worldwide
Baseprofile pressurecoefficient distributions for the usual N.A.C.A. family of airfoils, which are also suitable for several other commonly employed airfoils, are included in tabular form. With these tabulated baseprofile pressures and the computed normalforce distributions, pressure distributions adequate for most engineering purposes can be obtained
A method for calculating heat transfer in the laminar flow region of bodies by
H. Julian Allen(
Book
)
3 editions published between 1942 and 1943 in English and held by 6 WorldCat member libraries worldwide
This report has been prepared to provide a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited in use to the determination of heat transfer from the forward section of such bodies when the flow is laminar. A comparison of the calculated average heattransfer coefficient for the nose section of the wing of a Lockheed 12A airplane with that experimentally determined shows a satisfactory agreement. A sample calculation is appended
3 editions published between 1942 and 1943 in English and held by 6 WorldCat member libraries worldwide
This report has been prepared to provide a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited in use to the determination of heat transfer from the forward section of such bodies when the flow is laminar. A comparison of the calculated average heattransfer coefficient for the nose section of the wing of a Lockheed 12A airplane with that experimentally determined shows a satisfactory agreement. A sample calculation is appended
Calculation of the chordwise load distribution over airfoil sections with plain, split, or serially hinged trailingedge flaps by
H. Julian Allen(
Book
)
2 editions published in 1938 in English and held by 5 WorldCat member libraries worldwide
2 editions published in 1938 in English and held by 5 WorldCat member libraries worldwide
Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere by
Murray Tobak(
Book
)
3 editions published in 1958 in English and held by 5 WorldCat member libraries worldwide
An analysis is given of the oscillatory motions of vehicles which traverse ascending and descending paths through the atmosphere at high speed. The specific case of a skip path is examined in detail, and this leads to a form of solution for the oscillatory motion which should recur over any trajectory. The distinguishing feature of this form is the appearance of the Bessel rather than the trigonometric function as the characteristic mode of oscillation
3 editions published in 1958 in English and held by 5 WorldCat member libraries worldwide
An analysis is given of the oscillatory motions of vehicles which traverse ascending and descending paths through the atmosphere at high speed. The specific case of a skip path is examined in detail, and this leads to a form of solution for the oscillatory motion which should recur over any trajectory. The distinguishing feature of this form is the appearance of the Bessel rather than the trigonometric function as the characteristic mode of oscillation
The asymmetric adjustable supersonic nozzle for windtunnel application by
H. Julian Allen(
Book
)
3 editions published between 1948 and 1953 in English and held by 5 WorldCat member libraries worldwide
The advantages and disadvantages of this nozzle relative to the conventional interchangeablefixedblock and flexiblewall nozzles are discussed
3 editions published between 1948 and 1953 in English and held by 5 WorldCat member libraries worldwide
The advantages and disadvantages of this nozzle relative to the conventional interchangeablefixedblock and flexiblewall nozzles are discussed
A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds by
H. Julian Allen(
Book
)
2 editions published in 1957 in English and held by 5 WorldCat member libraries worldwide
A simplified analysis of the velocity and deceleration history of 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
2 editions published in 1957 in English and held by 5 WorldCat member libraries worldwide
A simplified analysis of the velocity and deceleration history of 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
The problem of longitudinal stability and control at high speeds by
Manley J Hood(
Book
)
2 editions published in 1943 in English and held by 4 WorldCat member libraries worldwide
The difficulty in pulling out of highspeed dives, experienced with some airplanes, is show to be due, to the wing, to the effect of compressibility on the lift of the wing. As the Mach number is increased above the critical for the wing, there is a marked decrease in the liftcurve slope in the downwash at the tail plane, and also a shift in the angle of attack for zero lift. These changes bring about an increase in the static longitudinal stability and alter the trim. Frequently the change in trim is such as to promote a diving tendency which, because of the increased stability, cannot be overcome by use of the normal elevator control
2 editions published in 1943 in English and held by 4 WorldCat member libraries worldwide
The difficulty in pulling out of highspeed dives, experienced with some airplanes, is show to be due, to the wing, to the effect of compressibility on the lift of the wing. As the Mach number is increased above the critical for the wing, there is a marked decrease in the liftcurve slope in the downwash at the tail plane, and also a shift in the angle of attack for zero lift. These changes bring about an increase in the static longitudinal stability and alter the trim. Frequently the change in trim is such as to promote a diving tendency which, because of the increased stability, cannot be overcome by use of the normal elevator control
Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic
heating, aerodynamic loads, and miss distance by
H. Julian Allen(
Book
)
1 edition published in 1957 in English and held by 3 WorldCat member libraries worldwide
An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry
1 edition published in 1957 in English and held by 3 WorldCat member libraries worldwide
An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry
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Related Identities
 United States National Advisory Committee for Aeronautics
 Ames Research Center
 James, Nataline A.
 Baldwin, Barrett S. (Barrett Stone) Author
 United States National Aeronautics and Space Administration
 Neice, Stanford E.
 Eggers, A. J. Author
 United States Congress Senate
 Chapman, Dean R. Contributor
 Perkins, Edward W.
Associated Subjects
Ablation (Aerothermodynamics) Acceleration (Mechanics) Aerodynamic heating Aerodynamic load Aerodynamic loadMathematical models Aerodynamics, Hypersonic Aerofoils AerofoilsMathematical models AeronauticsResearch Air flow AirplanesControl Ballistic missilesAtmospheric entry Body of revolution Boundary layer Charts, diagrams, etc Compressibility Drag (Aerodynamics) Flaps (Airplanes) Fluid dynamics HeatConvection HeatTransmission Interference (Aerodynamics) Laminar flow Mach number Mathematical analysis Mathematics Meteorites Meteoroids Meteors MeteorsPhotographic measurements Nozzles Numerical analysis Oscillations Stability of airplanes, Longitudinal Stability of rockets Supersonic nozzlesDesign and construction Supersonic wind tunnels Trajectories (Mechanics) Viscous flow Wind tunnels Wind tunnel walls
Alternative Names
Allen, H. Julian 19101977
Allen, Harry J. 19101977
Allen, Harvey 19101977
Harry Julian Allen Amerikaans ruimteingenieur (19101977)
Harry Julian Allen amerikai mérnök
هری جولین آلن
Languages