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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps

Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps

Date: September 1, 1943
Creator: Kauffman, William M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cascade investigation of buckets for a modern aircraft turbosupercharger

Cascade investigation of buckets for a modern aircraft turbosupercharger

Date: November 1, 1944
Creator: Erwin, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for determining propeller efficiency

Charts for determining propeller efficiency

Date: September 1, 1944
Creator: Talkin, Herbert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for estimation of the characteristics of a helicopter rotor in forward flight I : profile drag-lift ratio for untwisted rectangular blades

Charts for estimation of the characteristics of a helicopter rotor in forward flight I : profile drag-lift ratio for untwisted rectangular blades

Date: August 1, 1944
Creator: Gustafson, F B
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
Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed

Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed

Date: December 1, 1944
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Climb and high-speed tests of a Curtiss number 714-1C2-12 four-blade propeller on the Republic P-47C airplane

Climb and high-speed tests of a Curtiss number 714-1C2-12 four-blade propeller on the Republic P-47C airplane

Date: December 1, 1944
Creator: Vogeley, A W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Collection of balanced-aileron test data

Collection of balanced-aileron test data

Date: January 1, 1944
Creator: Rogallo, F M
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
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
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