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 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer

Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer

Date: February 1, 1945
Creator: Baals, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Date: September 1, 1943
Creator: Bogdonoff, Seymour M.
Description: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
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
Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility

Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility

Date: October 1, 1944
Creator: Cleary, Harold E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Date: December 1, 1943
Creator: Sears, Richard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface

Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface

Date: March 1, 1944
Creator: Lowry, John G.; Maloney, James A. & Garner, I Elizabeth
Description: Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle

An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle

Date: February 1, 1945
Creator: Rubert, Kennedy F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers

Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers

Date: February 1, 1944
Creator: Crigler, John L
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
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
Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers

Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers

Date: April 1, 1944
Creator: Alexander, S R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles

A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles

Date: December 1, 1943
Creator: Draley, Eugene C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Date: January 1, 1945
Creator: Zimmey, Charles M. & Lappi, Viola M.
Description: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
Contributing Partner: UNT Libraries Government Documents Department
Considerations of wake-excited vibratory stress in a pusher propeller

Considerations of wake-excited vibratory stress in a pusher propeller

Date: February 1, 1944
Creator: Miller, Mason, F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An interim report on the stability and control of tailless airplanes

An interim report on the stability and control of tailless airplanes

Date: October 1, 1944
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Simple curves for determining the effects of compressibility on pressure drop through radiators

Simple curves for determining the effects of compressibility on pressure drop through radiators

Date: September 1, 1944
Creator: Baals, Donald D
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
Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap

Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap

Date: September 1, 1944
Creator: Wallace, Arthur R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 65(Sub 3)-418, A=1.0 Airfoil Section

Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 65(Sub 3)-418, A=1.0 Airfoil Section

Date: August 1, 1944
Creator: Tucker, Warren A. & Quinn, John H.
Description: Wind-tunnel tests, investigating low drag wing performance in small-scale tests, showed a large increase in minimum drag coefficient, and a decrease of maximum lift coefficient occurred with decreasing Reynolds Number above certain designated values. The lift-curve slope varied up to 6% between high and low turbulence levels. Low Reynolds Number test data are unreliable for low drag airfoils either to estimate full-scale characteristics or to determine merits of airfoils for higher Reynolds numbers.
Contributing Partner: UNT Libraries Government Documents Department
Effect of a trailing-edge extension on the characteristics of a propeller section

Effect of a trailing-edge extension on the characteristics of a propeller section

Date: September 1, 1944
Creator: Stickle, George W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The theory of propellers III : the slipstream contraction with numerical values for two-blade and four-blade propellers

The theory of propellers III : the slipstream contraction with numerical values for two-blade and four-blade propellers

Date: November 1, 1944
Creator: Theodorsen, Theodore
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The theory of propellers II : method for calculating the axial interference velocity

The theory of propellers II : method for calculating the axial interference velocity

Date: November 1, 1944
Creator: Theodorsen, Theodore
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The theory of propellers IV : thrust, energy, and efficiency formulas for single- and dual-rotating propellers with ideal circulation distribution

The theory of propellers IV : thrust, energy, and efficiency formulas for single- and dual-rotating propellers with ideal circulation distribution

Date: January 1, 1944
Creator: Theodorsen, Theodore
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The theory of propellers I : determination of the circulation function and the mass coefficient for dual-rotating propellers

The theory of propellers I : determination of the circulation function and the mass coefficient for dual-rotating propellers

Date: August 1, 1944
Creator: Theodorsen, Theodore
Description: None
Contributing Partner: UNT Libraries Government Documents Department