WorldCat Identities

Purser, Paul E.

Overview
Works: 58 works in 97 publications in 3 languages and 473 library holdings
Genres: Conference proceedings 
Roles: Editor, Author
Classifications: TL873, 629.45
Publication Timeline
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Most widely held works by Paul E Purser
Manned spacecraft; engineering design and operation by Paul E Purser( Book )

10 editions published between 1964 and 1994 in English and Italian and held by 346 WorldCat member libraries worldwide

Wind-tunnel tests at low speed of swept and yawed wings having various plan forms by Paul E Purser( Book )

5 editions published between 1947 and 1951 in English and held by 6 WorldCat member libraries worldwide

Results are presented of wind-tunnel tests made at low speed of various small-scale models of swept-back, swept-forward, and yawed wings. The tests covered changes in aspect ratio, taper ratio, and tip shape. Some data were obtained with high-lift devices on sweptback wings and with ailerons on sweptforward wings. The data have been briefly analyzed and some comparisons have been made with the available theory
NACA hypersonic rocket and high-temperature jet facilities by Paul E Purser( Book )

3 editions published in 1957 in English and held by 5 WorldCat member libraries worldwide

Collection and analysis of hinge-moment data on control-surface tabs by Paul E Purser( Book )

2 editions published between 1946 and 1947 in English and held by 5 WorldCat member libraries worldwide

Various wind-tunnel data on the hinge-moment characteristics of control-surface tabs have been collected and analyzed. The data, all of which are for plain unbalanced tabs, were obtained from force tests of models in two- and three-dimensional flow and from pressure-distribution measurements on models in two-dimensional flow. Some data that show the effects of Mach number on tab hinge moments for representative conventional and NACA 6-series airfoil sections are presented
A.I.A.A./N.A.S.A. Third Manned Space Flight Meeting, Houston, Texas, November 4-6, 1964 by Manned Space Flight Meeting( Book )

1 edition published in 1964 in English and held by 5 WorldCat member libraries worldwide

Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails by Paul E Purser( Book )

5 editions published between 1944 and 1945 in English and held by 5 WorldCat member libraries worldwide

An analysis has been made of available data on vee-tail surfaces. Previously published theoretical studies of vee tails have been extended to include the control effectiveness and control forces in addition to the stability. Tests of two isolated tail surfaces with various amounts of dihedral provided a check of the theory. Methods for designing the vee tails were also developed and are given in the present paper
Comparison of pitching moments produced by plain flaps and by spoilers and some aerodynamic characteristics of an NACA 23012 airfoil with various types on aileron by Paul E Purser( Book )

4 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide

An analysis and comparison has been made of the pitching moment characteristics of airfoils with plain flaps and spoilers. Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devices were located nearer airfoil leading edge
Wind-tunnel investigation of an NACA 23012 airfoil with a 0.30-airfoil-chord double slotted flap by Paul E Purser( Book )

2 editions published between 1942 and 1943 in German and English and held by 3 WorldCat member libraries worldwide

Tests to determine the effect of flap position and deflection on the aerodynamic characteristics of an NACA 23012 airfoil with a double slotted flap having a chord 30 percent of the airfoil chord (0.30c) were conducted in the LMAL 7- by 10-foot tunnel. In addition, a few tests were made to determine the aerodynamic section characteristics as affected by the size and shape of the fore flap, by movement of the fore flap and rear flap as a unit, and by variation in the airfoil lower lip. Contours of rear-flap-nose position for various values of maximum section lift coefficient, section profile-drag coefficient, and section pitching-moment coefficient are presented at three selected fore-flap positions for various rear-flap deflections. The complete aerodynamic section characteristics are given at the three selected fore-flap positions for the optimum-lift and optimum-drag positions of the rear flap at several deflections
Preliminary investigation at low speed of downwash characteristics of small-scale sweptback wings by Paul E Purser( Book )

2 editions published in 1947 in English and held by 3 WorldCat member libraries worldwide

A preliminary investigation has been made at low speed of the downwash behind varios small-scale swept-back wings. The wing configurations for which data were obtained covered aspect ratios from 2.5 to 4.0, sweepback angles from 32.5 degrees to 40 degrees, and ratios of root chord to tip chord from 0.62 to 2.06
Effects of trailing-edge modifications on pitching moment characteristics of airfoils / Paul E. Purser and Harold S. Johnson by Paul E Purser( Book )

2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide

The available data on the effects of trailing-edge modifications on the pitching-moment characteristics of airfoils have been collected and briefly analyzed. With the control-surface gap sealed, the location of the airfoil aerodynamic center moved forward as the included angle between the upper and lower surfaces of the airfoil at the trailing edge was increased and as the airfoil thickness at 0.9 chord was increased. The variation of pitching-moment coefficient with control-surface deflection, at constant lift coefficient with gap sealed, decreased as the trailing-edge angle was increased by the effects of the airfoil thickness near the trailing edge could not be determined because of insufficient data
Tests to determine effects of slipstream rotation on the lateral stability characteristics of a single-engine low-wing airplane model by Paul E Purser( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

Tests have been made of a 1/5-scale powered model of a single-engine low-wing airplane with three propeller-blade settings and three values of tail length to provide information on the effects of slipstream rotation on the directional stability and control characteristics of single-engine airplanes
Wind-tunnel investigation of effects of unsymmetrical horizontal-tail arrangements on power-on static longitudinal stability of a single-engine airplane model by Paul E Purser( Book )

2 editions published in 1947 in English and held by 3 WorldCat member libraries worldwide

The results of wind-tunnel of a single-engine single-rotation airplane model indicated that, although extreme asymmetry in the horizontal tail showed a reduction in power effects on the longitudinal stability of the model, the particular "practical" arrangement tested did not show marked improvement. Disagreement between tests and analyses indicated the necessity for continued research to determine the characteristics of the slipstream behind various propeller-fuselage-wing combinations. Out-of-trim lateral forces and moments of the unsymmetrical tail arrangements that were best from consideration of longitudinal stability were no greater than those of the normal tail arrangement
Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds by Paul E Purser( Book )

2 editions published in 1952 in English and held by 3 WorldCat member libraries worldwide

Some approximate values of the yawing moment due to sideslip derivative for eight airplane-like configurations flown as rocket models for other purposes, at transonic speeds, have been collected and compared with the available subsonic and supersonic wind-tunnel data for the same configurations
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel by Paul E Purser( Book )

2 editions published in 1942 in English and held by 2 WorldCat member libraries worldwide

Tests have been made in the LMAL 7- by 10-foot tunnel for determining the aerodynamic characteristics and the flap loads of a brake-flap installation on a 0.40-scale semispan model of the F4F-3 left wing panel. The data presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap combinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and the lower (slotted) flap
Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing by Paul E Purser( Book )

2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide

An investigation was made in the LMAL 7- by 10-foot tunnel of various modifications of the trailing-edge portion of a 0.20-chord plain aileron on a partial-span model of a tapered low-drag wing. The modifications considered consisted of various amounts of symmetrical and unsymmetrical thickening and beveling of the aileron trailing edge. The effects of aileron-nose gap, nose-seal location, and tab deflection were determined for the most promising modifications. The control-wheel forces and the rates of roll were estimated for a high-speed airplane with the original aileron and with some of the modified ailerons
Wind tunnel investigation of a plain aileron with various trailing-edge modifications on a tapered wing. 1- Aileron with fixed inset tabs by Francis M Rogallo( Book )

1 edition published in 1942 in English and held by 2 WorldCat member libraries worldwide

An investigation was made in the LMAL 7- by 10-foot tunnel of various modifications to the trailing edge of a 0.155-chord plain aileron on a semispan model of the tapered wing of a fighter airplane. The modifications considered in the present report were: (1) plain and unrigged ailerons with fixed positive tabs to provide upfloating tendencies and allow reduction of stick force through the use of conventional differential aileron linkages; and (2) plain and downrigged ailerons with fixed negative tabs to provide downfloating tendencies and allow reductions of stick force through the use of reversed differential aileron linkages. The effect of a gap at the aileron nose was investigated for each of the basic modifications
Exploratory rocket flight tests to investigate the use of a freely spinning monoplane tail for stabilizing a body by Paul E Purser( Book )

2 editions published in 1952 in English and held by 2 WorldCat member libraries worldwide

Wind-tunnel investigation of 20-percent-chord plain and frise ailerons on an NACA 23012 airfoil by Francis M Rogallo( Book )

2 editions published in 1941 in English and held by 2 WorldCat member libraries worldwide

Tests indicated that the oscillation of the Frise aileron was the result of an abrupt breakaway of the flow at the lower surface of the aileron nose when the aileron was deflected to some angle between -10 and -20 degrees, the particular angle varying with the shape of the aileron and with the angle of attack of the airfoil. The flow breakaway was accomplished by a rapid increase in the hinge moment and, in general, by a decrease in the rolling-moment. The tendency to oscillate was reduced or eliminated when a bulge or a nose slat was added to the lower surface of the aileron. The nose slat, moreover, increased the effective deflection range of the aileron
A study of the application of data on various types of flap to the design of fighter brakes by Paul E Purser( Book )

2 editions published in 1942 in English and held by 2 WorldCat member libraries worldwide

An approximate method of applying available data on various types of flaps in design of fighter brakes is presented together with several examples of its use. Examples show computed results of application of various arrangements of perforated double split flaps, combinations of upper-surface perforated split flaps, and an NACA slotted flap for use as brake on a fighter airplane. Computed effects of flap type, size, location and deflection as well as effects of altitude and initial velocities on braking characteristics are shown
Experimental determination of effect of structural rigidity on rolling effectiveness of some straight and swept wings at Mach numbers from 0.7 to 1.7 by H. Kurt Strass( Book )

2 editions published in 1950 in English and held by 1 WorldCat member library worldwide

 
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