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Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Date: January 1942
Creator: Abbott, Ira H.
Item Type: Refine your search to only Report
open access

Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Description: Report presenting pressure distribution measurements on two 24-inch chord models equipped with Fowler flaps in the two-dimensional low-turbulence pressure tunnel. Results regarding pressure-distribution diagrams and normal-force and moment coefficients are provided.
Date: January 1942
Creator: Abbott, Ira H.
Item Type: Refine your search to only Report
open access

Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons

Description: Report presenting testing in the two-dimensional tunnel of four models submitted by the Glenn L. Martin Company as intermediate sections of the wing of the XB-33 airplane. Each airfoil model had different types of flaps or no flaps at all. Results regarding the lift and drag data, lift coefficients, effect of flap positions, aileron effects, drag coefficients, and hinge-moment coefficients are provided.
Date: June 1942
Creator: Abbott, Ira H.
Item Type: Refine your search to only Report
open access

Generalized selection charts for bombers powered by one, two, four, and six 2000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by one, two, four, and six 2000-horsepower engines supercharged to 25,000 feet. The performances are computed and are based on drag coefficients equal to the best obtained on modern airplanes and on weight estimates obtained from modern Army Air Forces airplanes. A chart is provided with the coordinates of power loading and wing loading noted so that all performances can be compared.
Date: July 1942
Creator: Brevoort, M. J.; Stickle, G. W. & Hill, Paul R.
Item Type: Refine your search to only Report
open access

Effect of airplane design efficiency and engine economy on range

Description: Report presenting an examination of the effects of variations in efficiency parameters, including engine economy, aerodynamic efficiency, and structural efficiency, on airplane performance. Efficiency parameters were found to be extremely ineffective in adjusting the airplane performance to its tactical mission as compared to primary parameters like altitude, power, gross weight, and wing area.
Date: December 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Item Type: Refine your search to only Report
open access

Generalized selection charts for bombers powered by one, two, four, and six 3000-horsepower engines 1: capacity and economy

Description: Supplement using data from a previous report to show the cargo that can be carried at various ranges, pounds of cargo that can be carried per pound of fuel, and other graphs to simplify the problem of determining which cargo can be carried at any range. The assumptions, parameters, and equations from the original report are carried over in the supplement.
Date: August 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Item Type: Refine your search to only Report
open access

Generalized selection charts for bombers powered by two, four, and six 3000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by two, four, and six 3000-horsepower engines supercharged to 35,000 feet. The performances are computed and are based on drag coefficients equal to the best obtained on modern airplanes and on weight estimates obtained from modern Army Air Forces airplanes. A chart is provided with the coordinates of power loading and wing loading noted so that all performances can be compared.
Date: August 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Item Type: Refine your search to only Report
open access

Generalized selection charts for bombers with four 2000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by four 2000-horsepower engines supercharged to 25,000 feet. A series of charts is provided with the coordinates of power loading and wing loading in order to simplify the selection of the best airplane for a given purpose.
Date: May 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Item Type: Refine your search to only Report
open access

Flight Measurements of the Lateral Control Characteristics of an Airplane Equipped With a Combination Aileron-Spoiler Control System

Description: Report presenting flight tests conducted to measure the lateral-control characteristics of an airplane, equipped with a lateral-control system, in which as the flaps are lowered the ailerons droop and a gradual transition of lateral control from ailerons to spoilers takes place. The variation of maximum rolling velocity with lateral stick movement as obtained in abrupt rudder-locked rolls was satisfactorily smooth except when control was by spoiler alone.
Date: September 2, 1942
Creator: Clousing, Lawrence A. & McAvoy, William H.
Item Type: Refine your search to only Report
open access

Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel

Description: From Summary: "A pursuit type airplane encountered severe diving moments in high-speed dives which make recovery difficult. For the purpose of investigating these diving moments and finding means for their reduction, a 1/6 scale model of the airplane was tested in the 16-foot high-speed wind tunnel at Ames Aeronautical Laboratory. The test results indicate that up to a Mach number of at least 0.75, the limit of the tests, the dive-recovery difficulties can be alleviated and the longitudinal man… more
Date: October 1942
Creator: Erickson, Albert L.
Item Type: Refine your search to only Report
open access

High-Speed Wind-Tunnel Tests of a 1/6-Scale Model of a Twin-Engine Pursuit Airplane

Description: Report presenting testing of a scale model of a twin-engine pursuit airplane in order to investigate the possibility of high-speed diving difficulties and to find remedies for them. Most of the data were obtained in force tests, although some pressure-distribution measurements, elevator hinge moments, and wake surveys were also made. The tests showed that the airplane will experience serious diving moments above lift coefficients of 0.5 at a Mach number of 0.65, and 0.1 at a Mach number of 0.72… more
Date: December 1942
Creator: Ganzer, Victor M.
Item Type: Refine your search to only Report
open access

Lateral-control characteristics of North American XP-51 airplane (A. C. No. 41-38) with beveled trailing-edge ailerons in high-speed flight

Description: Report presenting the flight tests of beveled trailing-edge ailerons on the North American XP-51 airplane which were extended to determine the aileron characteristics in high-speed dives. Standard recording instruments were used to determine airspeed, aileron position, stick force, and rate of roll. The results show that the beveled trailing-edge form of aerodynamic balance had no abnormal or unusual characteristics in high-speed flight.
Date: November 1942
Creator: Hoover, Herbert H. & White, Maurice D.
Item Type: Refine your search to only Report
open access

Flight Measurements of the Rudder Control and Sideslip Characteristics of Four Vertical Tail Arrangements on the P-40 Series Airplanes

Description: Report presenting an investigation of rudder trim force change with speed and power, rudder force reversals in sideslips, and rudder positions in sideslips and straight flight of a P-40E airplane. Quantitative measurements of the items were made on three other vertical arrangements.
Date: October 1942
Creator: Johnson, Harold I. & Vensel, Joseph R.
Item Type: Refine your search to only Report
open access

Performance Characteristics of Mixed-Flow Impeller and Vaned Diffuser With Several Modifications

Description: Report presenting an investigation of the performance of a mixed-flow impeller and vaned diffuser unit with several modifications in a variable-component supercharger test rig. The investigation covered impeller tip speeds from 800 to 1200 feet per second over the range of air flows from wide-open throttle to incipient surge. The results showed the supercharger to have a peak efficiency of 0.77 and a peak pressure coefficient of 0.61 with the impeller frontal clearance at 0.035 inch.
Date: July 1942
Creator: King, J. Austin & Glodeck, Edward
Item Type: Refine your search to only Report
open access

Cooling Investigation of a B-24D Engine-Nacelle Installation in the NACA Full-Scale Tunnel

Description: Report presenting an investigation conducted in the full-scale tunnel to determine methods of improving the cooling of the B-24D engine installation. The B-24D is a four-engine high-wing monoplane having a span of 110 feet, a wing area of 1048 square feet, and a gross weight of 56,000 pounds.
Date: November 1942
Creator: Lehr, Robert R.; Kinghorn, George F. & Guryansky, Eugene R.
Item Type: Refine your search to only Report
open access

Power-on longitudinal-stability and control tests of the 1/8-scale model of the Brewster F2A airplane equipped with full-span slotted flaps and a new horizontal tail

Description: Report presenting tests in the 7- by 10-foot wind tunnel of the scale model of the Brewster F2A airplane equipped with full-span slotted flaps and a new horizontal tail. The primary objective was to determine the power-on static longitudinal stability and control characteristics of the model with the new horizontal tail.
Date: March 1942
Creator: Lowry, John G. & Toll, Thomas A.
Item Type: Refine your search to only Report
open access

Free-spinning-tunnel tests of a 1/23.75-scale model of the Douglas DC-3 airplane

Description: Report presenting testing of a model of the Douglas DC-3 airplane for several loading conditions. The load factor for the complete airplane, for the horizontal tail, and the force to start moving the elevator downward were estimated for some steady spins. Testing occurred at 2500 feet and 10,000 feet.
Date: June 1942
Creator: MacDougall, George F., Jr.
Item Type: Refine your search to only Report
open access

Measurements of the Flying Qualities of a Hawker Hurricane Airplane

Description: Report presenting an investigation of the flying qualities of a Hawker Hurricane airplane. Thirteen flights and approximately 17 hours of flying time were required to complete the tests, which included extensive measurements of stability, controllability, and stalling characteristics. The results were similar to the flying qualities of other previously studied pursuit airplanes.
Date: April 1942
Creator: Nissen, J. M. & Phillips, W. H.
Item Type: Refine your search to only Report
open access

Control-Motion Studies of the PBM-3 Flying Boat in Abrupt Pull-Ups

Description: Report presenting a control-motion study in flight that is part of series covering a range of types and sizes of modern airplanes. This particular one involves the PBM-3 flying boat, which is equipped with a control mechanism typical of the cable-type systems in large transport, cargo, or bomber airplanes as well as those employed in flying boats. The elasticity of the elevator control system of the PBM-3 was such to limit the obtainable acceleration to about 3g for center-of-gravity positions … more
Date: November 1942
Creator: Pearson, Henry A. & Smull, Leland K.
Item Type: Refine your search to only Report
open access

A Flight Investigation of the Stability of a Towed Body

Description: Report presenting flight tests to determine whether a towed body that was designed to meet certain specifications met the stability specification, which required that angular deviations in flight should be less than 1 degree. The requirement was met in flight in smooth air, but not in rough air, where the rolling motions were considerably larger.
Date: October 1942
Creator: Phillips, W. H.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel

Description: "The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap" (p. 1).
Date: October 1942
Creator: Purser, Paul E. & Liddell, Robert B.
Item Type: Refine your search to only Report
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