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 Collection: Technical Report Archive and Image Library
Wind-tunnel investigation of the aerodynamic characteristics of a 1/15-scale model of the Northrop MX-775A missile

Wind-tunnel investigation of the aerodynamic characteristics of a 1/15-scale model of the Northrop MX-775A missile

Date: October 5, 1951
Creator: Phelps, E Ray & Lazzeroni, Frank A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96

Date: January 1, 1958
Creator: Evans, Albert J & Liner, George
Description: An investigation of the characteristics of a full-scale supersonic-type propeller has been made in the Langley 16-foot transonic tunnel with the 6000-horsepower propeller dynamometer. The tests covered a range of blade angles from 20.2 degrees to 60.2 degrees at forward Mach numbers up to 0.96. The results showed that envelope efficiency at an advance ratio of 2.8 decreased from 86 percent to 72 percent when the forward Mach number was increased from 0.70 to 0.96. A comparison of the experimental results with calculated results showed that maximum propeller efficiency can be calculated with good accuracy by using ordinary subsonic strip theory when the blade-section speeds are supersonic. The investigation also showed favorable power-absorption properties of the supersonic-type propeller at high speeds.
Contributing Partner: UNT Libraries Government Documents Department
A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

Date: January 4, 1951
Creator: Evans, Albert J & Liner, George
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the aerodynamic characteristics of a series of swept, highly tapered thin wings at transonic speeds : transonic bumb method

Wind-tunnel investigation of the aerodynamic characteristics of a series of swept, highly tapered thin wings at transonic speeds : transonic bumb method

Date: January 4, 1957
Creator: Few, Albert G , Jr & Fournier, Paul G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the air load distribution on two combinations of lifting surface and fuselage

Wind-tunnel investigation of the air load distribution on two combinations of lifting surface and fuselage

Date: May 1, 1947
Creator: Sandahl, Carl A & Vollo, Samuel D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the behavior of parachutes in close proximity to one another

Wind-tunnel investigation of the behavior of parachutes in close proximity to one another

Date: August 13, 1953
Creator: Scher, Stanley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the boundary layer and wake and their relation to airfoil characteristics.NACA 65(sub 1)-012 airfoil with a true contour flap and a beveled-trailing-edge flap

Wind-tunnel investigation of the boundary layer and wake and their relation to airfoil characteristics.NACA 65(sub 1)-012 airfoil with a true contour flap and a beveled-trailing-edge flap

Date: June 1, 1947
Creator: Mendelsohn, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the boundary layer on an NACA 0009 airfoil having 0.25- and 0.50- airfoil chord plain sealed flaps

Wind-tunnel investigation of the boundary layer on an NACA 0009 airfoil having 0.25- and 0.50- airfoil chord plain sealed flaps

Date: April 1, 1948
Creator: Brewer, Jack D & Polhamus, Josephine F
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 the contribution of a vertical tail to the directional stability of a fighter-type airplane

Wind-tunnel investigation of the contribution of a vertical tail to the directional stability of a fighter-type airplane

Date: January 1, 1952
Creator: Marino, Alfred A & Mastrocola, N
Description: Contributions of vertical tail and fuselage to directional stability are determined from pressure distributions measured over wide ranges of angle of attack and angle of yaw with stabilizer in each of three vertical positions, with stabilizer removed and with both stabilizer and vertical tail removed. Results point out inadequacies of current design methods and show that more accurate methods must treat separately contributions of vertical tail, fuselage area above stabilizer, and fuselage area below stabilizer.
Contributing Partner: UNT Libraries Government Documents Department