UNT Libraries Government Documents Department - 604 Matching Results

Search Results

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Description: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
Date: September 1, 1943
Creator: Bogdonoff, Seymour M.

Wind-Tunnel Investigation of a Plain Aileron with Various Trailing-Edge Modifications on a Tapered Wing III : 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 1, 1943
Creator: Purser, Paul E. & Rogallo, F.M.

Wind-tunnel investigation of an NACA 23012 airfoil with a 0.30-airfoil-chord double slotted flap

Description: Report discusses the results of testing of flap position and deflection on the aerodynamic characteristics of a NACA 23012 airfoil with a double slotted flap with a chord 30 percent of the airfoil chord. The maximum lift coefficient, profile-drag coefficients, pitching-moment coefficients, lift, and drag are provided at several positions of the flap. The results were also compared to previous testing on several flap configurations.
Date: December 1943
Creator: Purser, Paul E.; Fischel, Jack & Riebe, John M.

Wind-tunnel investigation of control-surface characteristics [part] 14: NACA 0009 airfoil with a 20-percent-chord double plain flap

Description: Report discusses the results of force testing of the aerodynamic characteristics of an NACA 0009 airfoil with a double plain flap; it consisted of a plain forward flap with a chord 20 percent of the airfoil chord and a plan rearward flap with a chord 15 percent of the airfoil chord. Comparisons were made to the characteristics of a 0.50c single plain flap. The lift, hinge moments, drag, and pitching moments are described.
Date: June 1943
Creator: Sears, Richard I. & Purser, Paul E.

Wind-tunnel investigation of devices for improving the diving characteristics of airplanes

Description: Report discussing testing on a model of a pursuit type airplane to determine the effect of several devices that may be applied to improve the high-speed pitching-moment characteristics. Auxiliary flaps, a controllable stabilizer, and a change in wing contour were all found to help increase the amount of control when recovering from high-speed dives.
Date: April 1943
Creator: Erickson, Albert L.

Wind-tunnel investigation of effect of yaw on lateral-stability characteristics [part] 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.

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.

Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

Description: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
Date: February 1, 1943
Creator: Toll, Thomas A.

Wind-tunnel tests of a piston-type control booster on an airfoil and aileron model

Description: From Summary: "Measurements of control moments were made in the NACA stability tunnel to determine the operational characteristics of a piston-type control booster on an aileron. The booster was so constructed and installed that pressures picked up from the air stream below the wing acted on a pair of pistons. The data are presented in the form of curves of pressure coefficients acting on the pistons, hinge-moment coefficients, and booster coefficients plotted against aileron deflection."
Date: November 1943
Creator: Bird, J. D. & Mendelsohn, Robert A.

Wind tunnel tests of ailerons at various speeds I : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt nose balance on the NACA 66,2-216 airfoil

Description: Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
Date: June 1, 1943
Creator: Letko, W; Denaci, H. G. & Freed, C