National Advisory Committee for Aeronautics (NACA) - 4,160 Matching Results

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Wind-tunnel investigation of effect of yaw on lateral-stability characteristics 3: symmetrically tapered wing at various positions on circular fuselage with and without a vertical tail

Description: Report presenting testing of model combinations of an NACA 23012 tapered wing and a circular fuselage to determine the effect of longitudinal wing position on the change in lateral stability due to interference. Results regarding wing-fuselage interference and effect of wing-fuselage interference on vertical tail are provided.
Date: September 1941
Creator: Recant, Isidore G. & Wallace, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics 5: Symmetrically Tapered Wing With a Circular Fuselage Having a Horizontal and a Vertical Tail

Description: Report discussing testing to determine the effect of a horizontal tail on the lateral-stability characteristics of a high-wing, a midwing, and a low-wing monoplane. The model was created from a circular fuselage, an NACA 23012 tapered wing, and an NACA 0009 horizontal tail surface. Information about the effective aspect ratio of the tail, restoring moment of yaw, and vertical-tail effectiveness as compared to the wing position is provided.
Date: June 1943
Creator: Wallace, Arthur R. & Turner, Thomas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics: [Part] 4 - Symmetrically Tapered Wing With a Circular Fuselage Having a Wedge-Shaped Rear and a Vertical Tail

Description: Report presenting testing of combinations of an NACA 23012 tapered wing and a circular fuselage with a wedge-shaped rear to determine the effect of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. Results regarding the lateral stability at small and large angles of yaw are provided.
Date: March 1942
Creator: Recant, I. G. & Wallace, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
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Wind-tunnel investigation of effects of tail length on the longitudinal and lateral stability characteristics of a single-propeller airplane model

Description: Report presenting an investigation of a powered model of a single-propeller low-wing airplane with three values of tail length and three horizontal tails to determine the effects of tail length and tail volume on the longitudinal and lateral stability.
Date: December 1948
Creator: Johnson, Harold S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model

Description: Report presenting a wind-tunnel investigation to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane. Extreme asymmetry in the horizontal tail was found to cause issues with the longitudinal stability, but the "practical" arrangement tested did not show much improvement. Results regarding the longitudinal stability tests, computations, and lateral and directional trim are provided.
Date: October 1947
Creator: Purser, Paul E. & Spear, Margaret F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of end-plate effects of horizontal tails on a vertical tail compared with available theory

Description: A vertical-tail model with stub fuselage was tested in combination with various simulated horizontal tails to determine the effect of horizontal-tail span and location on the aerodynamic characteristics of the vertical tail. Available theoretical data on end-plate effects were collected and presented in the form most suitable for design purposes. Reasonable agreement was obtained between the measured and theoretical end-plate effects of horizontal tails on vertical tails, and the data indicated… more
Date: April 1946
Creator: Murray, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel investigation of fuselage stability in yaw with various arrangements of fins

Description: "An investigation was made in the 7-by-10 foot wind tunnel to determine the effects of dorsal-type fins and various arrangements of fins on the aerodynamic characteristics of a streamline circular fuselage. Comparative plots of the aerodynamic characteristics of the fuselage alone and the fuselage with various fin arrangements are given to show their effects on coefficients of yawing moment, drag, and lateral force. Results are also given for one case in which a rear fin on a circular fuselage … more
Date: November 1940
Creator: Hoggard, H. Page, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of High-Lift and Stall-Control Devices on a 37 Degree Sweptback Wing of Aspect Ratio 6 at High Reynolds Numbers

Description: "Results are presented of an investigation in the Langley 19-foot pressure tunnel of the longitudinal characteristics of a semispan model wing having 37 degrees sweepback of the leading edge, an aspect ratio of 6, and NACA 641-212 airfoil section perpendicular to the 27-percent-chord line. Several types of stall-control devices including extensible round-nose leading-edge flaps, a leading-edge slat, and a drooped leading edge were investigated; partial- and full-span trailing-edge split and dou… more
Date: September 2, 1948
Creator: Koven, William & Graham, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Horizontal Tails 1: Unswept and 35 Degrees Swept-Back Plan Forms of Aspect Ratio 3

Description: Memorandum presenting the results of a wind-tunnel investigation of the low-speed characteristics of horizontal tails of aspect ratio 3 with unswept and swept-back plan forms. Two models were tested which had identical areas, aspect ratio, taper ratio, and airfoil section, differing only in the angle of sweepback and elevator area ratios. The major effect of sweepback was to increase the rate of change of hinge-moment coefficient with angle of attack, to reduce the rate of change with elevator … more
Date: April 22, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Horizontal Tails 2: Unswept and 35 Degree Swept-Back Plan Forms of Aspect Ratio 4.5

Description: Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. The two models had an aspect ratio of 4.5, taper ratio of 0.5, and an NACA 64A010 airfoil section. Test results are presented with and without standard roughness applied to their leading edges and with sealed and unsealed radius-nose elevators.
Date: June 3, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of horizontal tails 3: unswept and 35 degrees swept-back plan forms of aspect ratio 6

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. Test results are provided for models with and without standard roughness on their leading edges and with sealed and unsealed radius-nose elevators. Results regarding effectiveness and hinge-moment parameters, static longitudinal stability, effect of standard roughness, and effect of removing the elevator nose … more
Date: December 17, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Horizontal Tails 4: Unswept Plan Form of Aspect Ratio 2 and a Two-Dimensional Model

Description: Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a horizontal-tail model of aspect ratio 2 with an unswept plan form and of a two-dimensional model. The two-dimensional model provides data which can be used as the basis for computing the three-dimensional lift and hinge-moment parameters by the lifting-surface-theory procedure. Results regarding the effectiveness and hinge-moment parameters, static longitudinal stability, scale eff… more
Date: December 16, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of horizontal tails. 5: 45 degree swept-back plan form of aspect ratio 2

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a 45 degree sweptback horizontal-tail model of aspect ratio 2 and a comparison of these results with results for a model of the same aspect ratio with an unswept hinge line. Results regarding the lift and hinge-moment parameters, static longitudinal stability, effect of Reynolds number, effect of standard roughness, effect of removing elevator nose seal, and visualization of the air flow… more
Date: September 27, 1949
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Icing of an Engine Cooling-Fan Installation

Description: Note presenting an investigation of the icing characteristics and means of ice protection of a typical radial-engine cooling-fan installation. The investigation was made at various icing and performance conditions in the icing research tunnel of the NACA Cleveland laboratory. The icing of the unprotected cooling-fan installation was found to present a serious operation problem.
Date: April 1947
Creator: Lewis, James P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Icing of an Engine Cooling-Fan Installation

Description: Note presenting an investigation of the icing characteristics and means of ice protection of a typical radial-engine cooling-fan installation. The icing of the unprotected cooling-fan installation was found to present a serious operational problem. Results regarding icing, steam heat de-icing, alcohol de-icing, and electrical heat de-icing are provided.
Date: April 1947
Creator: Lewis, James P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel investigation of NACA 65,3-418 airfoil section with boundary-layer control through a single suction slot applied to a plain flap

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnel of the NACA 65,3-418 airfoil section with a 25-percent-airfoil-chord plain flap and a suction slot on the flap. The primary purpose of the investigation is to determine the effect of the type of boundary-layer control on the section lift-drag ratio.
Date: February 23, 1949
Creator: Horton, Elmer A. & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel investigation of NACA 66(215)-216, 66,1-212, and 65(sub 1)-212 airfoils with 0.20-airfoil-chord split flaps

Description: Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel of three different types of NACA airfoil sections equipped with split flaps with chords 20 percent of the airfoil chord. The main purpose was to determine the maximum-lift characteristics of these low-drag airfoil sections with split flaps.
Date: July 1944
Creator: Fullmer, Felicien F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of NACA 23012, 23021, and 23030 airfoils equipped with 40-percent-chord double slotted flaps

Description: Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to determine the effect of the deflection of main and auxiliary slotted flaps on the aerodynamic section characteristics of large-chord NACA 23012, 23021, 23030 airfoils equipped with 40-percent-chord double slotted flaps. The complete aerodynamic section characteristics and envelope polar curves are given for each airfoil-flap combination. The effect of airfoil thickness is shown, and comparisons are … more
Date: 1941
Creator: Harris, Thomas A. & Recant, Isidore G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of perforated split flaps for use as dive brakes on a rectangular NACA 23012 airfoil

Description: Report presenting an investigation of the aerodynamic characteristics of a rectangular NACA 23012 airfoil with single and double perforated split flaps in the NACA 7- by 10-foot wind tunnel. A large range of flap spans and deflections and a large range of spanwise and chordwise locations of the flaps were investigated. Results regarding the double split flaps, single split flaps, diving speed, and aileron control are provided.
Date: July 1941
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA 23012 Airfoil

Description: Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated th… more
Date: November 1941
Creator: Purser, Paul E. & Turner, Thomas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of plain ailerons for a wing with a full-span flap consisting of an inboard Fowler and an outboard retractable split flap

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of three plain ailerons on an NACA 23012 wing with full-span combinations of Fowler and split-type flaps. Static rolling, yawing, and hinge moments were determined and are presented for several angles of attack and flap deflection. The results indicated that a plain sealed aileron with internal balance will provide lateral control for airplanes equipped with full-span combinations of slotted and split-type flaps.
Date: March 1941
Creator: Harris, Thomas A. & Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Description: Report presenting the results of flight investigations showing that a beveled trailing-edge aileron gives as low or a lower profile drag than a contour aileron. Section profile drag and lift coefficients with two different types of ailerons were obtained at 3 different Reynolds numbers.
Date: January 1943
Creator: Abbott, Frank T., Jr. & Underwood, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Rear Underslung Fuselage Ducts

Description: Report discussing an investigation of cooling ducts at various positions on a model of a typical pursuit airplane in the NACA full-scale tunnel. Results in the report are given for a duct located on the bottom of the fuselage with the inlet behind the leading edge of the wing. Due to the thick boundary layers at the inlets of the rear underslung fuselage duct and the serious pressure losses that resulted, a special vane was also installed to avoid boundary-layer separation.
Date: September 1943
Creator: Czarnecki, K. R. & Nelson, W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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