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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

Date: May 1, 1942
Creator: Pearson, H. A. & Amderspm. R. F.
Description: As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required.
Contributing Partner: UNT Libraries Government Documents Department
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
Compressibility Effects in Aeronautical Engineering

Compressibility Effects in Aeronautical Engineering

Date: August 1, 1941
Creator: Stack, John
Description: Compressible-flow research, while a relatively new field in aeronautics, is very old, dating back almost to the development of the first firearm. Over the last hundred years, researches have been conducted in the ballistics field, but these results have been of practically no use in aeronautical engineering because the phenomena that have been studied have been the more or less steady supersonic condition of flow. Some work that has been done in connection with steam turbines, particularly nozzle studies, has been of value, In general, however, understanding of compressible-flow phenomena has been very incomplete and permitted no real basis for the solution of aeronautical engineering problems in which.the flow is likely to be unsteady because regions of both subsonic and supersonic speeds may occur. In the early phases of the development of the airplane, speeds were so low that the effects of compressibility could be justifiably ignored. During the last war and immediately after, however, propellers exhibited losses in efficiency as the tip speeds approached the speed of sound, and the first experiments of an aeronautical nature were therefore conducted with propellers. Results of these experiments indicated serious losses of efficiency, but aeronautical engineers were not seriously concerned at the ...
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