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 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
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
Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron

Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron

Date: April 1, 1945
Creator: Purser, Paul E. & Mckinney, Elizabeth G.
Description: Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devices were located nearer airfoil leading edge.
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
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
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

Date: February 1, 1944
Creator: Nitzberg, Gerald E.
Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
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
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
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
Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests

Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests

Date: February 1, 1945
Creator: Hamilton, William T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine I

A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine I

Date: May 1, 1945
Creator: Branstetter, J Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel

Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel

Date: July 1, 1946
Creator: Pinkel, Benjamin & Rubert, Kennedy F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Date: April 1, 1946
Creator: Pardee, Otway O'm. & Heaslet, Max A.
Description: Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils.
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
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: July 1, 1943
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data

The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data

Date: February 1, 1944
Creator: Boshar, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics

Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics

Date: February 1, 1945
Creator: Harmon, S M
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
Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel

Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel

Date: February 1, 1945
Creator: Seacord, Charles L. & Campbell, John P.
Description: Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory.
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
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
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
Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron

Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron

Date: July 1, 1944
Creator: Luoma, Avro A
Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.
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
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