National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

Search Results

prev Results: 13351 - 13374 next
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack: Subsonic, Transonic, and Supersonic Speeds

Description: Note presenting the effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels. Results regarding effect of impact-opening size, effect of varying the shape of the internal chamber, effect of external shape, effect of slant profile, effect of venting of shielded tubes, effect of varying the probe position and the throat diame… more
Date: May 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack -- Subsonic, Transonic, and Supersonic Speeds

Description: "The effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes has been determined for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels at the Langley Aeronautical Laboratory" (p. 495).
Date: January 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a plain aileron and a balanced aileron on a tapered wing with full-span duplex flaps

Description: Report presenting an investigation 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. Increments of maximum lift coefficient of 0.82 and 1.04 were obtained from the inboard flap alone and from the duplex-flap combination.
Date: July 1942
Creator: Rogallo, F. M. & Lowry, John G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing

Description: Report presenting an investigation in the 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 tested included various amounts of symmetrical and unsymmetrical thickening and beveling of the aileron trailing edge. Results regarding coefficients and corrections, characteristics with ailerons neutral, characteristics with ailerons deflected, aileron trim characteristics, and e… more
Date: January 1943
Creator: Purser, Paul E. & McKee, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind tunnel investigation of a plain aileron with various trailing-edge modifications on a tapered wing 2: ailerons with thickened and beveled trailing edges

Description: Report presenting an investigation in the 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 stick forces and rates of roll were estimated for a fighter airplane with the plain and modified ailerons.
Date: October 1942
Creator: Rogallo, F. M. & Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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 controlllability at low speeds.
Date: January 1943
Creator: Purser, Paul E. & Rogallo, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Plain and a Slot-Lip Aileron on a Wing With a Full-Span Flap Consisting of an Inboard Fowler and an Outboard Slotted Flap

Description: Report presenting an investigation of a slot-lip aileron and a plain aileron, singly and in combination, on an NACA 23012 wing with a full-span flap. The characteristics of these lateral-control devices were essentially the same as those of similar devices on the wing with full-span NACA slotted flaps as tested in a previous investigation.
Date: June 1941
Creator: Rogallo, F. M. & Schuldenfrei, Marvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Plain and Slot-Lip Aileron on a Wing With a Full-Span Slotted Flap

Description: Report presenting an investigation of a slot-lip aileron and a plain aileron singly and in combination with an NACA 23012 wing with a full-span slotted flap. Static rolling, yawing, and hinge moments were determined and are presented for several angles of attack and flap deflection.
Date: April 1941
Creator: Rogallo, Francis M. & Spano, Bartholomew S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a ram-jet canard missile model having a wing and canard surfaces of delta plan form with 70 degree swept leading edges: Longitudinal and lateral stability and control characteristics at a Mach number of 1.60

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the longitudinal and lateral stability and control characteristics of a ramjet canard missile with a center-of-gravity location -19.5 percent of the wing mean aerodynamic chord.
Date: August 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Ram-Jet Missile Model Having a Wing and Canard Surfaces of Delta Plan Form With 70 Degree Swept Leading Edges: Force and Moment Characteristics of Various Combinations of Components at a Mach Number of 1.6

Description: Report presenting testing of a ram-jet canard missile model with a wing and horizontal and vertical canard surfaces of delta plan form with 70 degree swept leading edges in the supersonic pressure tunnel. Two ram-jet nacelles were mounted in the vertical plane near the rear of the body and various combinations of components were tested. Results regarding the longitudinal and lateral characteristics, comparison with theory, and effect of nacelles on the model are presented.
Date: March 9, 1953
Creator: Hamilton, Clyde V.; Driver, Cornelius & Sevier, John R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Ram-Jet Model Having a Wing and Canard Surfaces of Delta Plan Form With 70 Degrees Swept Leading Edges: Force and Moment Characteristics at Combined Angles of Pitch and Sideslip for Mach Number 2.01

Description: Results presenting an investigation in the supersonic pressure tunnel to determine the static stability and control characteristics of a ram-jet canard missile at Mach number 2.01. The missile had wings, canard surfaces of delta plan form with 70 degree swept leading edges, and two ram-jet nacelles. Results regarding the longitudinal and lateral characteristics are provided.
Date: April 26, 1956
Creator: Driver, Cornelius & Hamilton, Clyde V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated, Balanced Double Split Flaps for Use as Aerodynamic Brakes

Description: Flat-plate flaps with no wing cutouts and flaps having Clark Y sections with corresponding cutouts made in wing were tested for various flap deflections, chord-wise locations, and gaps between flaps and airfoil contour. The drag was slightly lower for wing with airfoil section flaps. Satisfactory aileron effectiveness was obtained with flap gap of 20% wing chord and flap-nose location of 80 percent wing chord behind leading edge. Airflow was smooth and buffeting negligible.
Date: April 1945
Creator: Ivey, Margaret F. & Toll, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a section of the horizontal tail surface for the Bell XP-63 airplane

Description: Report presenting force tests conducted on a model of a section of the XP-63 horizontal tail surface in the 4- by 6-foot closed-throat vertical wing tunnel. The angle-of-attack range was from the negative to the positive stall for all flap deflections.
Date: August 1941
Creator: Ames, Milton B., Jr. & Hoggard, H. Page, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds

Description: Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date: January 22, 1952
Creator: Gracey, William; Pearson, Albin O. & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Spoiler-Slot Aileron on an NACA 23012 Airfoil With a Full-Span Fowler Flap

Description: Report presenting an investigation of a spoiler-slot aileron on an NACA 23012 airfoil with a full-span 30-percent-chord Fowler flap. The static rolling, yawing, and hinge moments were determined for several angles of attack and flap deflections. The ineffective region could be eliminated by a provision in the aileron linkage that would automatically uprig the ailerons as the flap is deflected.
Date: December 1941
Creator: Rogallo, F. M. & Spano, Bartholomew S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Systematic Series of Modifications to a Flying-Boat Hull

Description: Note presenting an investigation to determine, for one representative hull form, the effect on some of the aerodynamic characteristics of systematic variations in the shape and disposition of the chines at and near the bow and in the depth of the step. Results regarding the effect of bow shape, depth of step, and rounded chines on drag, and a comparison with other hulls and a body of revolution are provided.
Date: May 1948
Creator: Fullmer, Felicien F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a tailless triangular-wing fighter aircraft at Mach numbers from 0.5 to 1.5

Description: Report presenting a wind-tunnel investigation to determine the respective variations with Mach number of the static longitudinal stability, the drag, and the effectiveness of a constant-chord control surface for a tailless fighter aircraft with a triangular wing of aspect ratio 2.31.
Date: June 24, 1949
Creator: Lawrence, Leslie F. & Summers, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a tapered wing with a plug-type spoiler-slot aileron and full-span slotted flaps

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of several arrangements of a plug-type spoiler-slot aileron on a tapered wing model of a typical fighter airplane with a full-span slotted flap. When the aileron is deflected, the plug projects from the upper surface of the wing as a spoiler and makes a slot appear behind the spoiler.
Date: July 1942
Creator: Lowry, John G. & Liddell, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Wing-Fuselage Combination With External Stores

Description: Report presenting an investigation of a basic wing-fuselage combination with several types of external-store installations meant to delay the advent of airplane buffet caused by external stores. Modifications for airplane design in order to minimize the effect of drag are provided. Some of the arrangements tested included the tandem-mounted arrangement, flush-mounted arrangement, store with a fan-shaped tail, and auxiliary airfoil arrangement.
Date: July 9, 1948
Creator: Silvers, H. Norman & Spreemann, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Wing-Root Inlet Configuration With Various Modifications at Mach Numbers of 1.41, 1.81, and 2.01

Description: Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.
Date: September 26, 1957
Creator: Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a wing-root inlet configuration with various modifications at Mach numbers of 1.41, 1.81, and 2.01

Description: Report presenting a wing-root inlet configuration with varying inlet components that were tested in the supersonic pressure tunnel at several Mach numbers, angles of attack, and sideslip angles. The intent was to determine the effects on inlet performance and engine-face total-pressure distributions of variations in these variables. Some inlet-lip stagger was found to improve pressure recoveries at high angles of attack with little to not compromise at an angle of attack of 0.
Date: September 26, 1957
Creator: Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on NACA 65(sub 2)-415, 65(sub 3)-418 and 65(sub 4)-421 airfoil sections

Description: Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on three different airfoil sections. The aileron effectiveness parameter decreased very slightly with an increase in airfoil thickness. Results regarding the plain-airfoil section characteristics, aileron effectiveness, lift characteristics, and effects of airfoil thickness are provided.
Date: August 1944
Creator: Braslow, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of ailerons on a low-drag airfoil 1: The effect of aileron profile

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20-chord plain sealed aileron and a 0.15-chord plain sealed aileron on an NACA 66,2-216 airfoil. Thickening of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing section lift curve, and reduce the hinge-moment coefficients. Results regarding the section data, aileron effectiveness, aileron hinge moments, lift, pitching moment, dra… more
Date: January 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of ailerons on a low-drag airfoil 2: the effect of thickened and beveled trailing edges

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications to the trailing edge of a 0.20-chord plain sealed aileron on an NACA 66,2-216 airfoil. The modifications considered consisted of various amounts of symmetrical thickening and beveling of the aileron trailing edge. Results regarding aileron effectiveness, aileron hinge moments, aileron control forces, lift, pitching moment, drag, and Reynolds number are provided.
Date: January 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen