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Preliminary Drag Tests in Flight of Low-Drag Wing on the Curtiss XP-60 Airplane
"The following preliminary drag results obtained in flight on the low-drag wing of the Curtiss XP-60 airplane are given herewith in compliance with the request of the Army Air Corps" (p. 1).
Date:
December 1941
Creator:
Jacobs, Eastman N.
System:
The UNT Digital Library
Pressure-Distribution Measurements of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation
"Pressure-distribution measurements were made at the request of the Materiel Division, U.S. Army Air Corps, on a 24-inch-chord wooden model equipped with a slotted flap and submitted by the Curtiss-Wright Corporation. The tests were made in the Langley two-dimensional tunnel at a Reynolds number of about 5,600,000" (p. 1).
Date:
December 1941
Creator:
Abbott, Ira H.
System:
The UNT Digital Library
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation
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.
System:
The UNT Digital Library
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane
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.
System:
The UNT Digital Library
The Aerodynamic Tests of Three Edo Floats for the SB2U-3, 0S2U-2, and XSB2C-2 Seaplanes - NACA Models 106-K, 107-K, and 125-AH
Report presenting aerodynamic testing of scale models of the Edo seaplane floats for the SB2U-3, OS2U-2, and XSB2C-2 seaplanes. Various coefficients, pitching moment, yawing moment, and drag coefficients are provided.
Date:
March 1942
Creator:
Liddell, Robert B.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
Wind Tunnel Tests of Wickwire-Spencer Propeller
Report presenting a propeller tested to determine the aerodynamic properties. The propeller was designed for operation on a small target airplane capable of flying at about 200 miles per hour at 1600 feet altitude with a 175-horsepower engine. Results regarding aerodynamic tests and functional tests are provided.
Date:
March 1942
Creator:
Valentine, E. Floyd & Mastrocola, Nicholas
System:
The UNT Digital Library
Measurements of the Flying Qualities of a Hawker Hurricane Airplane
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.
System:
The UNT Digital Library
Generalized selection charts for bombers with four 2000-horsepower engines
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.
System:
The UNT Digital Library
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
Report presenting tests in the two-dimensional low-turbulence pressure tunnel of a model of the NACA 66,2-116, a = 0.6 airfoil section representing the root section of the wing for the XP-63 airplane. The model was of 24-inch chord, built of wood with dural slot cover plates for the flap.
Date:
May 1942
Creator:
Underwood, William J. & Abbott, Frank T., Jr.
System:
The UNT Digital Library
Cooling in Cruising Flight With Low Fuel-Air Ratios
Report presenting testing of a Pratt & Whitney R-1830-43 engine mounted in a B-24D nacelle in the full-scale wind tunnel in order to investigation the potential improvements of fuel economy. Suggestions for improving the cruising power and cruising range by operating at specified fuel-air ratios are provided.
Date:
June 1942
Creator:
Silverstein, Abe & Wilson, Herbert A., Jr.
System:
The UNT Digital Library
Free-spinning-tunnel tests of a 1/23.75-scale model of the Douglas DC-3 airplane
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.
System:
The UNT Digital Library
Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons
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.
System:
The UNT Digital Library
Generalized selection charts for bombers powered by one, two, four, and six 2000-horsepower engines
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.
System:
The UNT Digital Library
Investigation of Means for Extending the Range of Several Bombers to 6000 Miles
Report presenting an investigation of means to increase the range of several airplanes to 6000 miles, including the B-17E, B-24D, B-26C, and B-25A. Tank-wing trailers and tank gliders were found to be the most practical ways of increasing range and calculations are provided for determining the proper loading and dimensions.
Date:
July 1942
Creator:
Ribner, H. S. & Harmon, S. M.
System:
The UNT Digital Library
Performance Characteristics of Mixed-Flow Impeller and Vaned Diffuser With Several Modifications
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
System:
The UNT Digital Library
Aerodynamic Tests of an M-31 Bomb in the 8-Foot High-Speed Tunnel
Report presenting aerodynamic tests of a 300-pound M-31 demolition bomb. Force tests at a range of angles of attack were made at Mach number 0.725, which corresponds to a speed of 810 feet per second at sea level. Results regard the drag, lift, and pitching moment are provided.
Date:
August 1942
Creator:
Baals, Donald D.
System:
The UNT Digital Library
Generalized selection charts for bombers powered by one, two, four, and six 3000-horsepower engines 1: capacity and economy
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.
System:
The UNT Digital Library
Generalized selection charts for bombers powered by two, four, and six 3000-horsepower engines
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.
System:
The UNT Digital Library
Flight Measurements of the Lateral Control Characteristics of an Airplane Equipped With a Combination Aileron-Spoiler Control System
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.
System:
The UNT Digital Library
Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel
"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.
System:
The UNT Digital Library
Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane
Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.
Date:
October 1942
Creator:
Underwood, William J.
System:
The UNT Digital Library
A Flight Investigation of the Stability of a Towed Body
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.
System:
The UNT Digital Library
Flight Measurements of the Rudder Control and Sideslip Characteristics of Four Vertical Tail Arrangements on the P-40 Series Airplanes
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.
System:
The UNT Digital Library