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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows

Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows

Date: March 1, 1946
Creator: Tetervin, Neal
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
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: Zalovcik, J. A. & Daum, F. L.
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
A method for the calculation of external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds

A method for the calculation of external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds

Date: March 1, 1946
Creator: Parker, Hermon M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theory and application of hot-wire instruments in the investigation of turbulent boundary layers

Theory and application of hot-wire instruments in the investigation of turbulent boundary layers

Date: March 1, 1946
Creator: Klebanoff, P. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of the stability and control characteristics of a straight-wing, tailless fighter-airplane model in the Langley free-flight tunnel

Determination of the stability and control characteristics of a straight-wing, tailless fighter-airplane model in the Langley free-flight tunnel

Date: February 1, 1946
Creator: Ankenbruck, Herman O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of specific types of surface roughness on boundary-layer transition

Effects of specific types of surface roughness on boundary-layer transition

Date: February 1, 1946
Creator: Loftin, L. K., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of specific types of surface roughness on boundary-layer transition

Effects of specific types of surface roughness on boundary-layer transition

Date: February 1, 1946
Creator: Loftin, Laurence K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Occurrence of iron oxides on cast-iron engine surfaces after operation

Occurrence of iron oxides on cast-iron engine surfaces after operation

Date: February 1, 1946
Creator: Borckway, L O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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