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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1943
 Collection: Technical Report Archive and Image Library
Wind tunnel investigation of control-surface characteristics XI : various large overhang and internal-type aerodynamic balances for a straight- contour flap on the NACA 0015 airfoil

Wind tunnel investigation of control-surface characteristics XI : various large overhang and internal-type aerodynamic balances for a straight- contour flap on the NACA 0015 airfoil

Date: January 1, 1943
Creator: Hoggard, H Page
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel investigation of control surface characteristics XII : various cover-plate alinements on the NACA 0015 airfoil with a 30 percent chord flap and large sealed internal balance

Wind tunnel investigation of control surface characteristics XII : various cover-plate alinements on the NACA 0015 airfoil with a 30 percent chord flap and large sealed internal balance

Date: January 1, 1943
Creator: Hoggard, H Page, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Wind-tunnel investigation of control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Date: July 1, 1943
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XIV : NACA 0009 airfoil with a 20-percent-chord double plain flap

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

Date: June 1, 1943
Creator: Purser, Paul E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XV : various contour modifications of a 0.30-airfoil-chord plain flap on an NACA 66(215)-014 airfoil

Wind-tunnel investigation of control-surface characteristics XV : various contour modifications of a 0.30-airfoil-chord plain flap on an NACA 66(215)-014 airfoil

Date: December 1, 1943
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of Devices for Improving the Diving Characteristics of Airplanes

Wind-Tunnel Investigation of Devices for Improving the Diving Characteristics of Airplanes

Date: April 23, 1943
Creator: Erickson, Albert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of effect of yaw on lateral-stability characteristics V : symmetrically tapered wing with a circular fuselage having a horizontal and a vertical tail

Wind-tunnel investigation of effect of yaw on lateral-stability characteristics V : symmetrically tapered wing with a circular fuselage having a horizontal and a vertical tail

Date: June 1, 1943
Creator: Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: January 1, 1943
Creator: Underwood, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel investigation of rear underslung fuselage ducts

Wind tunnel investigation of rear underslung fuselage ducts

Date: September 1, 1943
Creator: Nelson, W J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

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

Date: February 1, 1943
Creator: Toll, Thomas A.
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of trimming tabs on a thickened and beveled aileron on a tapered low-drag wing

Wind-tunnel investigation of trimming tabs on a thickened and beveled aileron on a tapered low-drag wing

Date: March 1, 1943
Creator: Crandall, Stewart M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of wing ducts on a single engine pursuit airplane

Wind-tunnel investigation of wing ducts on a single engine pursuit airplane

Date: October 1, 1943
Creator: Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of a piston-type control booster on an airfoil and aileron model

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

Date: November 1, 1943
Creator: Mendelsohn, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of a twin-engine model to determine the effect of direction of propeller rotation on the static-stability characteristics

Wind-tunnel tests of a twin-engine model to determine the effect of direction of propeller rotation on the static-stability characteristics

Date: January 1, 1943
Creator: Swanson, Robert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: June 1, 1943
Creator: Letko, W; Denaci, H. G. & Freed, C
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Date: June 1, 1943
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of ailerons at various speeds III : ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil

Wind-tunnel tests of ailerons at various speeds III : ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil

Date: September 1, 1943
Creator: Kemp, W B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil

Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil

Date: August 1, 1943
Creator: Anderson, R A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of ailerons at various speeds V : pressure distributions over the NACA 66,2-216 and NACA 23012 airfoils with various balances on 0.20-chord ailerons

Wind tunnel tests of ailerons at various speeds V : pressure distributions over the NACA 66,2-216 and NACA 23012 airfoils with various balances on 0.20-chord ailerons

Date: November 1, 1943
Creator: Denaci, H G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of four full-scale seaplane floats

Wind-tunnel tests of four full-scale seaplane floats

Date: July 1, 1943
Creator: Maynard, Julian D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of single and dual-rotating tractor propellers at low blade angles and of two-and three-blade tractor propellers at blade angles up to 65 degrees

Wind-tunnel tests of single and dual-rotating tractor propellers at low blade angles and of two-and three-blade tractor propellers at blade angles up to 65 degrees

Date: February 1, 1943
Creator: Gray, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of the 1/9-Scale Model of the Curtiss XP-62 Airplane with Various Vertical Tail Arrangements

Wind-Tunnel Tests of the 1/9-Scale Model of the Curtiss XP-62 Airplane with Various Vertical Tail Arrangements

Date: July 1, 1943
Creator: Wallace, Arthur R. & Recant, I.G.
Description: The effect of various vertical tail arrangements upon the stability and control characteristics of an XP-62 fighter model was investigated. Rudder-free yaw characteristics with take-off power and flaps deflected were satisfactory after dorsal fin modifications. Directional stability was obtained with all modified vertical tails. Satisfactory rudder effectiveness resulted partly because the dual-rotation propellers produced no asymmetric yawing moments. Pedal forces in sideslips were undesirably large but may be easily reduced.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Date: October 1, 1943
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of two tapered wings with straight trailing edges and with constant-chord center sections of different spans

Wind-tunnel tests of two tapered wings with straight trailing edges and with constant-chord center sections of different spans

Date: March 1, 1943
Creator: Neely, Robert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department