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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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers

Description: The three papers collected here are: 'The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack.', 'Base Pressure on Wings and Bodies with Turbulent Boundary Layers', and 'Flow over Inclined Bodies'. The subject of the first paper is the drag of the nose section of bodies of revolution at zero angle of attack. The main object of the second paper is to summarize the prinicpal results of the many wind tunnel and free flight measurements of base pressure on both bodies o… more
Date: November 9, 1951
Creator: Seiff, Alvin; Sandahl, Carl A.; Chapman, Dean R.; Perkins, E. W. & Gowen, F. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Two Techniques Utilizing Rocket-Propelled Vehicles for the Determination of the Damping-in-Roll Derivative

Description: Report presenting rocket-powered flight investigations for the purpose of comparing damping-in-roll results obtained from a torque-nozzle technique. Results regarding basic aerodynamic quantities, data from the torque-nozzle technique, wing-dropping phenomenon, and comparison of the values of the two techniques are provided.
Date: May 3, 1951
Creator: Stone, David G. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails

Description: "Free-flight tests have been made to determine the drag at zero lift of several configurations of a missile having triangular wings and tails. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8" (p. 1).
Date: May 31, 1950
Creator: Hall, James R. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect on Transonic and Supersonic Drag of a Fuselage Protuberance of an Essential Unswept Wing-Fuselage Combination

Description: "An investigation of the effect on transonic and supersonic drag of a fuselage protuberance designed to improve the overall longitudinal distribution of cross-sectional area of an essentially unswept wing-fuselage combination has been made with free-flight rocket models. The wing-fuselage configuration was tested with and without a fuselage protuberance designed to relieve the steep area gradient over the rear portion of the wing" (p. 1).
Date: January 5, 1954
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Some Leading-Edge Modifications, Section and Plan-Form Variations, and Vertical Position on Low-Lift Wing Drag at Transonic and Supersonic Speeds

Description: Report presents information about free-flight rocket-propelled model testing to determine the effect of some wing geometry variables on low lift drag at a range of Mach numbers. Results regarding the effect of airfoil section, wing nose droop and nose flaps, plan form, and wing vertical position are provided.
Date: January 18, 1955
Creator: Welsh, Clement J.; Wallskog, Harvey A. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D-558-2 Airplane

Description: "An investigation of the rolling effectiveness at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane has been made by means of a rocket-propelled test vehicle. The variation of rolling effectiveness with Mach number is similar to that obtained previously for tapered sweptback wings having full-span, 0.2-chord ailerons" (p. 1).
Date: July 21, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a 42.7 Degree Sweptback Wing Having Partial-Span Ailerons

Description: An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.
Date: October 25, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of Several Aileron Configurations on a Tapered Wing Having 42.7 Degrees Sweepback

Description: Report presenting an investigation of several aileron modifications in conjunction with a tapered, sweptback wing with circular-arc airfoil sections of relatively large thickness ratio. This testing permits the evaluation of the wing-aileron rolling effectiveness over a range of Mach numbers. Results regarding true-contour ailerons, extended-chord ailerons, and blunt trailing-edge ailerons are provided.
Date: January 11, 1949
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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 Section Thickness and Wing Sweepback

Description: Report discusses the development and testing of a rocket-propelled test vehicle to investigate aerodynamic control effectiveness at high subsonic, transonic, and supersonic speeds. Modifications to the section thickness and wing sweepback to improve performance are also described. A description of the vehicle, instrumentation, accuracy, and evaluation of testing results is included.
Date: May 29, 1947
Creator: Sandahl, Carl A. & Marino, Alfred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of Fullspan, 0.2 Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Taper, Aspect Ratio, and Section-Thickness Ratio

Description: Report presenting an aerodynamic-control-effectiveness investigation using free-flight rocket-propelled RM-5 test vehicles at high subsonic, transonic, and supersonic speeds. Results regarding aileron control characteristics and drag measurements are provided.
Date: August 13, 1947
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Longitudinal Stability and Control of a Rocket-Propelled Missile Model Having Cruciform, Triangular, Interdigitated Wings and Tails

Description: Report presenting flight testing of a missile model with cruciform, triangular, interdigitated wings and tails to determine the longitudinal stability and control characteristics over a range of Mach numbers. Results regarding static stability and damping, control effectiveness, and control hinge moments are provided.
Date: July 10, 1951
Creator: Sandahl, Carl A. & Hall, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Rolling Effectiveness of a Wing-Spoiler Arrangement at High Subsonic, Transonic, and Supersonic Speeds

Description: Report presenting an investigation of the rolling effectiveness of a wing-spoiler arrangement using a rocket-propelled test vehicle in free flight. The configuration investigated in the report is likely not optimum and indicates a need for further exploration.
Date: May 17, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Rolling Effectiveness of Several Delta Wing - Aileron Configurations at Transonic and Supersonic Speeds

Description: Report presenting testing of several delta wing-aileron configurations as part of a general investigation of their rolling effectiveness characteristics at transonic and supersonic speeds. Results regarding wing-aileron rolling effectiveness and drag are provided.
Date: August 27, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Zero-Lift Drag of Several Wings at Supersonic Mach Numbers Extending to 2.6

Description: Report presenting testing of the zero-lift drag of several wings at supersonic Mach numbers. The delta wings had the lowest drag over the entire Mach number range. Results regarding the variation of Reynolds number with Mach number, total drag coefficient, wing-plus-interference drag coefficients, and skin friction drag are provided.
Date: December 2, 1952
Creator: Hopko, Russell N. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Free-Flight Investigation of the Effect of Airfoil Section on Aileron Rolling Effectiveness at Transonic and Supersonic Speeds

Description: "Results have been obtained by means of a free-flight technique utilizing rocket propulsion which indicate that aileron-rolling-effectiveness characteristics are affected adversely by variations in airfoil section which procedure large increases in the trailing-edge angle" (p. 1).
Date: June 25, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Rolling Effectiveness of a Thin Tapered Wing Having Partial-Span Ailerons as Determined by Rocket-Powered Test Vehicles

Description: "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" (p. 1).
Date: May 23, 1950
Creator: Sandahl, Carl A. & Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Rolling Effectiveness of Wing-Tip Ailerons as Determined by Rocket-Powered Test Vehicles and Linear Supersonic Theory

Description: Report presenting testing of the rolling effectiveness and drag of half-delta wing-tip ailerons on rectangular and tapered wings sweptback 0 and 45 degrees for a range of Mach numbers. The rolling effectiveness was relatively uniform across the Mach number range and was lower at subsonic speeds and higher at supersonic speeds than the partial-span plain ailerons.
Date: August 29, 1950
Creator: Sandahl, Carl A.; Strass, H. Kurt & Piland, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Effects of a Pusher Propeller on Lift, Profile Drag, Pressure Distribution, and Boundary-Layer Transition of a Flapped Wing

Description: Report presenting some of the effects of pusher-propeller operation on the aerodynamic characteristics of a flapped wing in the propeller-research tunnel. The effects are primarily related to the effects of propeller inflow on the aerodynamic characteristics of the wing.
Date: April 1945
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Air Load Distribution on Two Combinations of Lifting Surface and Fuselage

Description: Report presenting wind tunnel measurements of the air load distribution on a canard-type model. Two combinations of lifting surface and fuselage were obtained by removing the wing and stabilizer of the model. Results regarding the fuselage pressure distribution, spanwise loading curves, and variation of lift, drag, and pitching-moment coefficients with angle of attack are provided.
Date: May 1947
Creator: Sandahl, Carl A. & Vollo, Samuel D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft, TED No. NACA DE332

Description: "Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about… more
Date: March 16, 1950
Creator: Hall, James R. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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