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Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds

Description: From Introduction: "The purpose of the present paper is to present results obtained recently relating to the characteristics of a full-span sharp-edge spoiler with an 0.02-chord projection above the wing surface at several chordwise positions and also to the relative effectiveness of the sharp-edge spoiler and a wedge-type spoiler located at the 80-percent-chord line."
Date: November 24, 1948
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Description: Report presenting several rectangular and tapered wing configurations with leading-edge and trailing-edge ailerons tested as part of a general investigation of an aerodynamic control at supersonic speeds. Results indicated that the use of the leading-edge aileron alone was ineffective or caused negative control until a high Mach number was attained. Results for the untapered configurations, tapered configurations, and drag measurements are provided.
Date: July 23, 1948
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Summary of some rocket-model investigations of effects of wing aspect ratio and thickness on aileron rolling effectiveness including some effects of spanwise aileron location for sweptback wings with aspect ratio of 8

Description: Report presenting the rolling effectiveness of 0.2-chord, trailing-edge ailerons on high-aspect-ratio sweptback wings over a range of Mach numbers. Some effects of spanwise aileron location on rolling effectiveness were measured by testing ailerons on the inboard half, the outboard half, and the full length of the exposed wings.
Date: February 17, 1954
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations at Mach numbers from 0.6 to 1.7 as determined from rocket-powered models

Description: A summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations for use at a range of Mach numbers. The values obtained were determined by the combined use of experimentally determined free-flight data and subsonic aerodynamic theory.
Date: January 22, 1952
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

The effect of spanwise aileron location on the rolling effectiveness of wings with 0 degree and 45 degree sweep at subsonic, transonic, and supersonic speeds

Description: Report discussing an investigation of the effect of spanwise aileron location on the rolling effectiveness of plain faired ailerons on untapered wing plan forms with designated sweep, airfoil sections, and aspect ratio using rocket-propelled test vehicles. Drag data is also presented for all configurations tested. Spanwise aileron location was found to have little effect on the effectiveness of the aileron on an unswept wing plan form.
Date: April 25, 1950
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Comparative tests of the rolling effectiveness of constant-chord, full-delta, and half-delta ailerons on delta wings at transonic and supersonic speeds

Description: Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.
Date: December 12, 1949
Creator: Sandahl, Carl A. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Description: From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."
Date: August 6, 1957
Creator: Strass, H. Kurt & Stephens, Emily W.
Partner: UNT Libraries Government Documents Department

An engineering method for the determination of aeroelastic effects upon the rolling effectiveness of ailerons on swept wings

Description: Report presenting a method for calculating the steady-state rolling effectiveness of flexible sweptback wings at subsonic and supersonic speeds. Comparisons between the experimental and calculated values are presented for a wide range of wing-aileron configurations.
Date: November 30, 1953
Creator: Strass, H. Kurt & Stephens, Emily W.
Partner: UNT Libraries Government Documents Department

Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback

Description: Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.
Date: October 8, 1951
Creator: Fields, E. M. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Some effects of aileron span, aileron chord, and wing twist on rolling effectiveness as determined by rocket-powered model tests and theoretical estimates

Description: A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.
Date: September 14, 1954
Creator: Strass, H. Kurt & Tucker, Warren A.
Partner: UNT Libraries Government Documents Department

Some experimental heating data on convex and concave hemispherical nose shapes and hemispherical depressions on a 30-degree blunted nose cone

Description: Report discussing heat data obtained on concave and convex hemispherical nose shapes and hemispherical depressions on a blunted 30-degree nose cone at a variety of Mach numbers. Both hot-jet tests and flight tests were carried out.
Date: March 10, 1958
Creator: Hopko, Russell N. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Flight investigation of the effect of thickening the aileron trailing edge on control effectiveness for sweptback tapered wings having sharp-and round-nose sections

Description: Report discussing an investigation of the rolling effectiveness at transonic and supersonic speeds on a 38.1 degree sweptback tapered wing with NACA 0010-64 airfoil sections and partial-span ailerons of true contour with a modified flt-side blunt trailing-edge shape. The variation of Reynolds number with Mach number and the control effectiveness is provided.
Date: May 2, 1950
Creator: Strass, H. Kurt & Fields, Edison M.
Partner: UNT Libraries Government Documents Department

Additional results in a free-flight investigation of control effectiveness of full-span, 0.2-chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, aspect ratio, taper, and section thickness ratio

Description: Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date: April 23, 1948
Creator: Sandahl, Carl A. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Rolling effectiveness of a thin tapered wing having partial-span ailerons as determined by rocket-powered test vehicles

Description: From Summary: "The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85."
Date: May 23, 1950
Creator: Sandahl, Carl A. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Recent experiences with flutter failure of sweptback, tapered wings having outboard, partial-span spoiler controls

Description: From Summary: "During the course of an investigation by the Langley Pilotless Aircraft Research Division regarding the effectiveness of spoilers and ailerons on sweptback tapered wings, it was necessary to test a given control configuration on wings of varying degrees of stiffness. In the process of conducting these tests, repeated wing failure was experienced with the weaker wing-spoiler configurations, whereas no failure occurred with any of the wing-aileron models. An investigation which was conducted by means of rocket-propelled test vehicles in free flight showed that the cause of the repeated failures was flutter of the bending-torsion type."
Date: October 5, 1953
Creator: Strass, H. Kurt & Marley, Edward T.
Partner: UNT Libraries Government Documents Department

Rolling effectiveness of all-movable wings at small angles of incidence at Mach numbers from 0.6 to 1.6

Description: From Summary: "Experimental data have been obtained of the rolling effectiveness of several all-movable wing configurations by means of rocket-propelled test vehicles in free flight. The results are compared with some available methods of estimation. These results validate the use of the simple equation derived by a strip integration and originally presented in NACA RM L50G14b over a wide range of application as a means of estimating the rolling effectiveness of all-movable wings."
Date: October 9, 1951
Creator: Strass, H. Kurt & Marley, Edward T.
Partner: UNT Libraries Government Documents Department

Some effects of roughness on stagnation-point heat transfer at a Mach number of 2, a stagnation temperature of 3,530 F, and a Reynolds number of 2.5 x 10(exp 6) per foot

Description: Report presenting an investigation to determine some effects of surface roughness on heat transfer at the stagnation point. Testing occurred in the ceramic-heated jet laboratory model at a Mach number of 2, a stagnation temperature of 3,530 degrees Fahrenheit, and a stream Reynolds number of 2.5 x 10(exp 6) per foot. Results regarding the variation of stagnation-point heat-transfer coefficient with surface roughness, heat transfer at the stagnation point of a hemisphere, and heat-transfer coefficient are provided.
Date: May 26, 1958
Creator: Strass, H. Kurt & Tyner, Thomas W.
Partner: UNT Libraries Government Documents Department

Rocket-model investigation of the rolling effectiveness of a fighter-type wing-control configuration at Mach numbers from 0.6 to 1.5

Description: Report presenting an investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane from Mach numbers 0.6 to 1.5. No effects of mutual interference between the spoiler and aileron were detectable. Results regarding drag and the effect of gap upon spoiler performance are also provided.
Date: February 25, 1952
Creator: Strass, H. Kurt & Marley, Edward T.
Partner: UNT Libraries Government Documents Department

Effect of elevator-profile modifications and trailing-edge strips on elevator hinge-moment and other aerodynamic characteristics of a full-scale horizontal tail surface

Description: Report presenting results of a full-scale horizontal tail surface made to determine the effect of elevator-profile modifications and trailing-edge strips on the elevator hinge-moment characteristics for elevators having fixed plan plan form and constant balance. Results regarding the basic data with the metal elevator, effect of trailing-edge angle, effect of nose shape, and effects of trailing-edge strips are provided.
Date: June 1945
Creator: Schueller, Carl F.; Korycinski, Peter F. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.6

Description: Report presenting a collection and summary of the wing-aileron rolling-effectiveness data obtained as part of an investigation of lateral control using rocket-powered test vehicles in free flight over a range of Mach numbers. Some effects of trailing-edge angle, aileron-chord ratio, aileron span and location, aspect ratio, wing sweepback, and wing-tail interference are provided.
Date: September 2, 1955
Creator: Strass, H. Kurt; Stephens, Emily W.; Fields, E. M. & Schult, Eugene D.
Partner: UNT Libraries Government Documents Department

Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a partial-span aileron on an inversely tapered sweptback wing

Description: Report presenting an investigation of the rolling effectiveness at transonic and supersonic speeds of an inversely tapered sweptback wing with a 10-percent-thick cambered airfoil section and outboard partial-span controls made by means of rocket-propelled test vehicles.
Date: May 1, 1950
Creator: Strass, H. Kurt; Fields, E. M. & Schult, E. D.
Partner: UNT Libraries Government Documents Department

Free-flight measurements of some effects of aileron span, chord, and deflection and of wing flexibility on the rolling effectiveness of ailerons on sweptback wings at Mach numbers between 0.8 and 1.6

Description: Report presenting a free-flight investigation to determine some effects of aileron span and deflection on the rolling effectiveness of plain, sealed, 15-percent- and 30-percent-chord flap-type ailerons through a range of Mach numbers. Wings of different degrees of torsional flexibility were tested and the results were extended to estimate rigid-wing rolling-effectiveness of all aileron configurations tested.
Date: January 24, 1952
Creator: Schult, Eugene D.; Strass, H. Kurt & Fields, E. M.
Partner: UNT Libraries Government Documents Department

Effects of some airfoil-section variations on wing-aileron rolling effectiveness and drag as determined in free flight at transonic and supersonic speeds

Description: Report presenting an investigation in free flight of the rolling effectiveness of plain ailerons in conjunction with wings having 0 and 45 degrees sweepback with several airfoil sections. Results regarding the rolling characteristics of rectangular and sweptback-wing configurations and drag measurements are provided.
Date: July 22, 1949
Creator: Sandahl, Carl A.; Bland, William M., Jr. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Tests of a full-scale horizontal tail surface in the Langley 16-foot high-speed tunnel

Description: Report presenting testing to determine the aerodynamic characteristics of a full-scale semispan horizontal tail surface of a fighter airplane at a range of mach numbers. The results presented show the effects of elevator nose shape, elevator trailing-edge angle, and trailing-edge strips on the aerodynamic characteristics.
Date: May 1946
Creator: Schueller, Carl F.; Korycinski, Peter F. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department