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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Date: January 1, 1946
Creator: Lindsey, W F
Description: An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.
Contributing Partner: UNT Libraries Government Documents Department
The effect of wall interference upon the aerodynamic characteristics of an airfoil spanning a closed-throat circular wind tunnel

The effect of wall interference upon the aerodynamic characteristics of an airfoil spanning a closed-throat circular wind tunnel

Date: January 1, 1946
Creator: Graham, Donald J
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
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
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Date: December 1, 1945
Creator: Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-Foot-Span Fighter-Type Wing of NACA 230-Series Airfoil Sections

Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-Foot-Span Fighter-Type Wing of NACA 230-Series Airfoil Sections

Date: November 1, 1945
Creator: West, F E
Description: Lift characteristics and pressure distribution for a NACA 230 wing were investigated for an angle of attack range of from -10 to +24 degrees and Mach range of from 0.2 to 0.7. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Contributing Partner: UNT Libraries Government Documents Department
An infrared cloud indicator I : analysis of infrared-radiation exchange with tables and chart for calibration of the cloud indicator

An infrared cloud indicator I : analysis of infrared-radiation exchange with tables and chart for calibration of the cloud indicator

Date: November 1, 1945
Creator: Kenimer, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rubber conductors for aircraft ignition cables

Rubber conductors for aircraft ignition cables

Date: November 1, 1945
Creator: Dietrich, Joseph R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails

Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails

Date: October 1, 1945
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Experimental Investigation of NACA Submerged-Duct Entrances

An Experimental Investigation of NACA Submerged-Duct Entrances

Date: October 1, 1945
Creator: Frick, Charles W.; Davis, Wallace F.; Randall, Lauros M. & Mossman, Emmet A.
Description: The results of a preliminary investigation of submerged duct entrances are presented. It is shown that an entrance of this type possess desirable critical speed and pressure recovery characteristics when used on a fuselage or nacelle in a region of low incremental velocity and thin boundary layer. The data obtained indicate that submerged entrances are most suitable for use with internal-flow systems which diffuse the air only a small amount: for example, those used with jet motors which have axial-flow compressors. Where complete diffusion of the air is required, fuselage-nose or wing leading edge inlets may prove to be superior. The results of the investigation have been prepared in such a form as to permit their use by a designer and the application of these data to a specific design is discussed.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane

Flight investigation of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane

Date: October 1, 1945
Creator: Zalovcik, J. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited power outputs from a CFR engine using internal coolants II : six aliphatic amines

Knock-limited power outputs from a CFR engine using internal coolants II : six aliphatic amines

Date: October 1, 1945
Creator: Evvard, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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
Bibliography and review of information relating to the hydrodynamics of seaplanes

Bibliography and review of information relating to the hydrodynamics of seaplanes

Date: September 1, 1945
Creator: Bidwell, Jerold M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wing modifications on the longitudinal stability of a tailless all-wing airplane model

Effect of wing modifications on the longitudinal stability of a tailless all-wing airplane model

Date: September 1, 1945
Creator: Ankenbruck, Herman O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for helicopter-performance estimation

Charts for helicopter-performance estimation

Date: August 1, 1945
Creator: Talkin, Herbert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A simple method for estimating terminal velocity including effect of compressibility on drag

A simple method for estimating terminal velocity including effect of compressibility on drag

Date: August 1, 1945
Creator: Bielat, Ralph P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Blade design data for axial-flow fans and compressors

Blade design data for axial-flow fans and compressors

Date: July 1, 1945
Creator: Bogdonoff, Harriet E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The development and application of high-critical-speed nose inlets

The development and application of high-critical-speed nose inlets

Date: July 1, 1945
Creator: Wright, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

Date: July 1, 1945
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of the lift coefficient on propeller flutter

Effect of the lift coefficient on propeller flutter

Date: July 1, 1945
Creator: Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An additional investigation of the high-speed lateral-control characteristics of spoilers

An additional investigation of the high-speed lateral-control characteristics of spoilers

Date: June 1945
Creator: Summers, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)

Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)

Date: June 1, 1945
Creator: Ferri, Antonio
Description: Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects.
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel

The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel

Date: June 1, 1945
Creator: Gabriel, David S.; Carmen, Robert L. & Trautwein, Elmer E
Description: Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates that the changes in turbine efficiency with Inlet pressure and temperature may be principally a Reynolds number effect.
Contributing Partner: UNT Libraries Government Documents Department