WorldCat Identities

Rogallo, Francis M. (Francis Melvin) 1912-2009

Overview
Works: 30 works in 51 publications in 1 language and 85 library holdings
Genres: Conference papers and proceedings 
Roles: Author
Classifications: TL574.A4, 629.1323
Publication Timeline
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Most widely held works about Francis M Rogallo
 
Most widely held works by Francis M Rogallo
Preliminary investigation of a paraglider by Francis M Rogallo( Book )

3 editions published in 1960 in English and held by 16 WorldCat member libraries worldwide

A preliminary investigation of the aerodynamic and control characteristics of a flexible glider similar to a parachute in construction has been made at the Langley Research Center to evaluate its capabilities as a reentry glider. Preliminary weight estimates of the proposed vehicle indicate that such a structure can be made with extreamly low wing loading. Maximum temperatures during the reentry maneuver might be held as low as about 1,500 degrees F
Internal-flow systems for aircraft by Francis M Rogallo( Book )

3 editions published between 1940 and 1941 in English and held by 6 WorldCat member libraries worldwide

When an internal-flow system tends to decrease the final velocity of its wake, the results showed that it should be arranged in series with the propulsive system; the inlet opening should be located at a forward stagnation point; and the outlet opening should be so shaped and located as to recover the kinetic energy of the jet without increasing the drag of other portions of the aircraft. When an internal-flow system tends to increase the final velocity of its wake, as does a propeller, location of the inlet opening in the boundary layer or in the wake of the wing or the fuselage may be desirable
Wind-tunnel investigation of trimming tabs on a thickened and beveled aileron on a tapered low-drag wing by Francis M Rogallo( Book )

3 editions published in 1943 in English and held by 5 WorldCat member libraries worldwide

Effects of gaps at aileron and tab noses were determined for three inset tabs, and effects of alignment of top cover plate on the aileron characteristics were determined with tab sealed in neutral position. Results indicated that inset tab with chord 50% of aileron chord provided most satisfactory trimming characteristics on beveled aileron. Attached tab, a satisfactory trimming device, increased control-operating force. Tab arrangements tested showed no appreciable change in aileron effectiveness
Wind-tunnel development of a plug-type spoiler-slot aileron for a wing with a full-span slotted flap and a discussion of its application by Francis M Rogallo( Book )

3 editions published in 1941 in English and held by 4 WorldCat member libraries worldwide

Wind-tunnel tests were made regarding aileron to determine static rolling, yawing, and hinge moments for several angles of attack and flap deflections. Aileron is essentially a tapered plug which is fitted into slot through wing and conforms to external wing contour when in neutral position. Results indicated aileron has negligible drag in neutral position and provides satisfactory lateral control for airplanes equipped with full-span slotted flaps; it is unsatisfactory with full-span split flap. Application of aileron to pursuit type airplane is considered and resultant characteristics are estimated
Collection of balanced-aileron test data by Francis M Rogallo( Book )

4 editions published in 1944 in English and held by 4 WorldCat member libraries worldwide

Test data of balanced ailerons have been collected from NACA and British sources. These data, which are presented in the form of charts, are grouped as A - ailerons with Frise balances, B - ailerons with blunt-nose balances, C - ailerons with internal balances, D - ailerons with contour modifications, and E - ailerons with tabs. Results of flight tests and wind tunnel tests in both two- and three-dimensional flow are presented but no correlation nor resume of the data has been included. Resumes are being published separately as completed
Wind-tunnel investigation of a plain and a slot-tip aileron on a wing with a full-span flap consisting of an inboard Fowler and an outboard slotted flap by Francis M Rogallo( Book )

3 editions published in 1941 in English and held by 4 WorldCat member libraries worldwide

Slot-lip and plain aileron are used singly and in combination on wing with Fowler flap over the inboard 63 percent of span and modified slotted flap over remainder of the wing. Static, rolling, yawing, and hinge moments are presented for several angles of attack and various combinations of deflections of inboard and outboard flaps. Devices should provide acceptable lateral control characteristics throughout useful flight range. System described gave estimated 14% increase in maximum lift coefficient over full-span NACA slotted flap
Wind-tunnel investigation of a plain and a slot-lip aileron on a wing with a full-span slotted flap by Francis M Rogallo( Book )

2 editions published in 1941 in English and held by 3 WorldCat member libraries worldwide

An investigation was made in the NACA 7- by 10-foot wind tunnel of a slot-lip aileron and a plain aileron singly and in combination on an NACA 23012 wing with a 0.2566c full-span slotted flap. The static rolling, yawing, and hinge moments were determined and are presented for several angles of attack and flap deflections. The aileron-control characteristics were computed for slot-lip and plain ailerons linked together in several different ways. The results indicated that these devices may be combined so as to provide satisfactory aileron-control characteristics throughout the useful flight range on a wing with a full-span slotted flap. Flight tests are recommended
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 )

2 editions published in 1942 in English and held by 3 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
Wind-tunnel investigation of a spoiler-slot aileron on an NACA 23012 with a full-span Fowler flap by Francis M Rogallo( Book )

2 editions published in 1941 in English and held by 3 WorldCat member libraries worldwide

The characteristics of the spoiler-slot aileron of the present investigation are essentially the same as those of the same device on the airfoil with a full-span NACA slotted flap as tested in the previous investigation. Up-rigging the ailerons, however, as the flap is deflected may be desirable. The test results indicate that the spoiler-slot aileron will provide acceptable lateral-control characteristics for airplanes with full-span Fowler flaps
Aerodynamic characteristics of a slot-lip aileron and slotted flapfor dive brakes by Francis M Rogallo( Book )

2 editions published in 1941 in English and held by 3 WorldCat member libraries worldwide

Section aerodynamic characteristics of an NACA 23012 airfoil with a slot-lip aileron and slotted flap have been determined over a large range of flap and aileron deflections. The results, which are presented in charts, indicate that these devices may be combined so as to provide satisfactory dive control. Additional tests are recommended for determination of the buffeting effects
Wind-tunnel investigation of a plain aileron and a balanced aileron on a tapered wing with full-span duplex flaps by Francis M Rogallo( Book )

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

An investigation was made of a plain aileron and a balanced aileron on a tapered wing with full-span duplex flaps, which consisted of an inboard NACA slotted flap and an outboard balanced split flap. The investigation was made in the 7- by 10-foot wind tunnel of the Langley Memorial Aeronautical Laboratory. Increments of maximum lift coefficient of 0.82 and 1.04 were obtained from the inboard flap alone and from the duplex-flap combination, respectively. The aileron was as effective with flaps fully extended as with flaps retracted, but a 30-percent reduction of aileron effectiveness appears unavoidable at intermediate positions of the outboard flap. If this reduction is acceptable, the wing arrangement tested should be satisfactory. Estimated rates of roll and stick forces for the arrangement on a fighter airplane are given
NASA research on flexible wings by Francis M Rogallo( Book )

2 editions published in 1967 in English and held by 3 WorldCat member libraries worldwide

Flexible wings are wings made of very loose or slack cloth whose configuration in flight is maintained by the combination of the aerodynamic forces and the reactions from the load suspension system. Such wings can be completely flexible or they may be stiffened in several ways to meet the requirements of particular applications. Wing planforms and the geometry of the load suspension system are also subject to wide variations. The overall spectrum of flexible wings investigated at the Langley Research Center is presented and the state of the art with regard to maximum lift-drag ratios obtained is defined for a wide range of wing configurations. Maximum lift-drag ratios above 3.0 were obtained on completely flexible wings; and for cylindrical-type flexible wings, values of lift-drag ratios up to 17.0 were obtained when the wing had small, tapered rigid leading edges
Wind-tunnel investigation of a plain aileron with various trailing-edge modifications on a tapered wing. 3 - Ailerons with simple and spring-linked balancing tabs by Francis M Rogallo( Book )

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

Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controllability at low speeds
Wind-tunnel of a plain aileron with various trailing-edge modifications on a tapered wing. 2 - Ailerons with thickened and beveled trailing edges 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 mode of the tapered wing of a fighter airplane. The modifications considered in the present report are various amounts of thickening and beveling of the aileron trailing edge to reduce the stick forces. The effect of the gap at the aileron nose was determined for the most promising modifications
Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination. 1 - Section characteristics, NACA 23012 airfoil 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 NACA 7- by 10-foot wind tunnel to determine the aerodynamic section characteristics of several arrangements of an NACA full-span high-lift lateral-control combination. The combination is essentially a full-span flap of airfoil profile that retracts ahead of a narrow-chord full-span aileron. In the flap-retracted condition the aileron is a conventional trailing-edge aileron of short chord and long span. In the flap-deflected condition the flap is similar to a Fowler flap and the aileron becomes a full-span slot-lip aileron. The aileron is drooped in the flap-deflected condition to improve high-lift characteristics. Tests were run at several aileron and flap angles and with several widths of slot to determine the optimum arrangement
Wind-tunnel investigation of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil by Francis M Rogallo( Book )

1 edition 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
Wind-tunnel investigation of a full-span retractable flap in combination with full-span plain and internally balanced ailerons on a tapered wing by Francis M Rogallo( Book )

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

With the flap fully extended, the aileron fully extended, the aileron effectiveness was about 50 percent greater than with the flap retracted. A reduction of aileron effectiveness of about 40 percent relative to the aileron effectiveness with the flap retracted appeared unavoidable at certain intermediate flap positions. The internal balance reduced the aileron stick forces to acceptable values for al flap positions and deflections along a selected path
Resume of recent parawing research : figures for presentation at the Course on Aerodynamic Deceleration at the Center for Continuation Study, University of Minnesota, July 8, 1965 by Francis M Rogallo( Book )

2 editions published in 1965 in English and held by 2 WorldCat member libraries worldwide

Wind-tunnel tests of a twin-engine model to determine the effect of direction of propeller rotation on the static-stability characteristics by Francis M Rogallo( Book )

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

Tests were made in the LMAL 7- by 10-foot tunnel to determine the effect of direction of propeller rotation on the static longitudinal- and lateral-stability characteristics of the 1/10-scale model of the North American B-28 airplane
Flexible wing research and development by Francis M Rogallo( Book )

in English and held by 1 WorldCat member library worldwide

This paper reviews flexible-wing research and development projects recently completed or now in progress by the National Aeronautics and Space Administration or by the industry under contract to NASA or the Department of Defense
 
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Alternative Names
Francis Rogallo Amerikaans ruimteingenieur (1912-2009)

Francis Rogallo ingegnere e inventore statunitense

Francis Rogallo US-amerikanischer Aerodynamiker

フランシス・ロガロ

Languages
English (44)