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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Supersonic-tunnel tests of projectiles in Germany and Italy

Supersonic-tunnel tests of projectiles in Germany and Italy

Date: October 1, 1945
Creator: Ferri, Antonio
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps

Wind-tunnel investigation of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps

Date: January 1, 1946
Creator: Foster, Gerald V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental constriction effects in high-speed wind tunnels

Experimental constriction effects in high-speed wind tunnels

Date: December 1, 1944
Creator: Byrne, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

Date: March 1, 1946
Creator: Daum, Fred L. & Zalovcik, John A.
Description: Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025.
Contributing Partner: UNT Libraries Government Documents Department
Summary of data relating to the effects of wing machine-gun and cannon installations on the aerodynamic characteristics of airplanes

Summary of data relating to the effects of wing machine-gun and cannon installations on the aerodynamic characteristics of airplanes

Date: January 1, 1945
Creator: Quinn, John H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Supersonic Axial-Flow Compressor

The Supersonic Axial-Flow Compressor

Date: January 1, 1950
Creator: Kantrowitz, Arthur
Description: An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained.
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane

Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane

Date: June 1, 1943
Creator: Kleckner, Harold F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers

Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers

Date: February 1, 1944
Creator: Von Doenhoff, Albert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane

Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane

Date: April 1, 1945
Creator: Skoog, Richard B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of dive-recovery flaps on an XP-51 airplane

Flight tests of dive-recovery flaps on an XP-51 airplane

Date: May 1, 1945
Creator: Williams, Walter G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes

Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes

Date: April 1, 1945
Creator: Dingeldein, Richard C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical investigation of the effects of elevator-fabric distortion on the longitudinal stability and control of an airplane

An analytical investigation of the effects of elevator-fabric distortion on the longitudinal stability and control of an airplane

Date: May 1, 1944
Creator: Mathews, Charles W
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 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 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 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 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 a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour

Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour

Date: February 1, 1945
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of Wing Inlets

Development of Wing Inlets

Date: March 1, 1946
Creator: Racisz, Stanley F.
Description: Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil.
Contributing Partner: UNT Libraries Government Documents Department
A flight investigation of NACA aileron modifications for the improvement of the lateral control characteristics of a high-speed fighter airplane

A flight investigation of NACA aileron modifications for the improvement of the lateral control characteristics of a high-speed fighter airplane

Date: December 1, 1945
Creator: Williams, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of flight data on limit pressure coefficients and their relation to high-speed burbling and critical tail loads

Correlation of flight data on limit pressure coefficients and their relation to high-speed burbling and critical tail loads

Date: September 1, 1944
Creator: Rhode, Richard V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling Characteristics of a Pratt and Whitney R-2800 Engine Installed in an NACA Short-Nose High-Inlet-Velocity Cowling

Cooling Characteristics of a Pratt and Whitney R-2800 Engine Installed in an NACA Short-Nose High-Inlet-Velocity Cowling

Date: June 1, 1944
Creator: Corson, Blake W. & McLellan, Charles H.
Description: An investigation was made of the cooling characteristics of a P and W R-2800 engine with NACA short-nose high inlet-velocity cowling. The internal aerodynamics of the cowling were studied for ranges of propeller-advance ratio and inlet-velocity ratio obtained by deflection of cowling flaps. Tests included variations of engine power, fuel/air ratio and cooling-air pressure drop. Engine cooling data are presented in the form of cooling correlation curves, and an example for calculation of cooling requirements in flight is included.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary aerodynamic and structural tests showing the effect of compressive load on the fairness of a low-drag wing specimen with chordwise hat-section stiffeners

Preliminary aerodynamic and structural tests showing the effect of compressive load on the fairness of a low-drag wing specimen with chordwise hat-section stiffeners

Date: December 1, 1943
Creator: Rossman, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Helicopter Performance of Modifications in Profile-Drag Characteristics of Rotor-Blade Airfoil Sections

Effect of Helicopter Performance of Modifications in Profile-Drag Characteristics of Rotor-Blade Airfoil Sections

Date: August 1, 1944
Creator: Gustafson, F.B.
Description: Rough conventional, smooth conventional, and laminar-flow or low-drag sections were tested. The items covered are rotor thrust for fixed power in hovering, range and endurance at cruising speed, and power required at high-forward speed. Calculations indicated that a smooth conventional section gives marked performance gains. Smaller gains are obtainable by using a low-drag section. At high speeds or loads the low-drag section is inferior to the smooth conventional section.
Contributing Partner: UNT Libraries Government Documents Department