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Résumé of NACA Stability and Control Tests of the Bell P-63 Series Airplane
Report on stability and control tests of the Bell P-63 series airplanes. Information about the spin characteristics, lateral control characteristics, longitudinal stability and control characteristics and directional stability and control characteristics is provided. A chronology of testing and detailed description of the airplane and its modifications are also provided.
Date:
October 19, 1944
Creator:
Johnson, Harold I.
System:
The UNT Digital Library
Power-off wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane
"At the request of the Bureau of Aeronautics, Navy Department, tests were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane. The object of the tests was to determine the power-off static lateral and longitudinal stability and control of the complete model" (p. 1).
Date:
June 1941
Creator:
Lowry, John G.
System:
The UNT Digital Library
Power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
"At the request of the Bureau of Aeronautics, Navy Department, tests were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps. The object of the tests was to determine the power-on static lateral and longitudinal stability of the complete model with a new wing which had a full-span slotted flap and a plain and slot-lip aileron for lateral control" (p. 1).
Date:
August 1941
Creator:
Lowry, John G.
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
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
Lift and Drag Characteristics of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation
Report presenting a wooden model equipped with a slotted flap that was tested in the two-dimensional tunnel. It represented a wing section of the Curtiss-Wright P-60A airplane and the NACA 66,2-118 section. Results regarding lift characteristics, drag coefficients, and flap deflection characteristics are provided.
Date:
December 1941
Creator:
Abbott, Ira 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
Two-Dimensional Wind-Tunnel Investigation of Six Airfoil Sections for the Wing of the Vega XP2V-1 Airplane
Report discussing testing of six airfoil sections for the wing of the Vega XP2V-1 airplane in a smooth condition and with standard leading-edge roughness. Information about the lift, drag, pitching-moment characteristics, and sensitivity to roughness is provided. No airfoil was found to be superior to the others in all categories.
Date:
October 1945
Creator:
Fullmer, Felicien F., Jr.
System:
The UNT Digital Library
Free-Spinning, Longitudinal-Trim, and Tumbling Tests of 1/17.8-Scale Models of the Cornelius XFG-1 Glider
Report discussing testing on the spin and recovery characteristics, longitudinal-trimming characteristics at extreme angles of attack, and tumbling characteristics of a model of the Cornelius XFG-1 glider. The effects of loading, mass distribution, and center-of-gravity position were determined. They also explored the inverted spin characteristics and spin-recovery parachute requirements.
Date:
January 1946
Creator:
Stone, Ralph W., Jr. & Daughtridge, Lee T., Jr.
System:
The UNT Digital Library
Tests of a 1/40-Scale Wing-Hull Model and a 1/10-Scale Float-Strut Model of the Hughes-Kaiser Cargo Airplane in the Two-Dimensional Low-Turbulence Pressure Tunnel
Report presenting aerodynamic and hydrodynamic tests of a 1/10-scale wing-hull model and a 1/10-scale float-strut model of the proposed arrangement of the Hughes-Kaiser cargo airplane. The aerodynamic tests were made primarily to study the drag characteristics of these models as originally designed and to determine how the design could be improved. Results regarding the wing-hull model and float-strut model are provided.
Date:
September 1943
Creator:
Fullmer, Felicien F., Jr.
System:
The UNT Digital Library
Langley Full-Scale-Tunnel Stability and Control Tests of the Bell YP-59A Airplane
Report discussing tests of the drag clean-up and stability of the Bell YP-59A jet-propelled airplane. The general stability, static stability, and control characteristics were examined. Specific details are also included about the effects of the exhaust jet on air flow at the tail.
Date:
January 18, 1945
Creator:
Brewer, Gerald W.
System:
The UNT Digital Library
Effect of airplane design efficiency and engine economy on range
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.
System:
The UNT Digital Library
A flight investigation of the boundary-layer characteristics and profile drag of the NACA 35-215 laminar-flow airfoil at high Reynolds numbers
Report presenting testing to determine the boundary layer characteristics and profile drag of the NACA 35-215 airfoil section at high Reynolds numbers. The results indicated that a forward movement of the transition point occurred at about 3 percent of the chord due to operation of the engines and propellers.
Date:
May 1941
Creator:
Platt, Robert C.
System:
The UNT Digital Library
Ditching behavior of military airplanes as affected by ditching aids
Report presenting an investigation of planing devices like hydroflaps and hydrofoils on several dynamically scaled models of military airplanes and their effectiveness in improving ditching characteristics. The ditching aids were generally found to be of value. Results regarding the hydroflap test in the impact basin, dynamic model tests at the outdoor catapult, and effect of ditching aids on ditching performance and rough water are provided.
Date:
January 1945
Creator:
Steiner, Margaret F.
System:
The UNT Digital Library
Flight Investigation to Improve the Dynamic Longitudinal Stability and Control-Feel Characteristics of the P-63A-1 Airplane (AAF No. 42-68889) with Closely Balanced Experimental Elevators
Results of flight tests of a control-feel aid presented. This device consisted of a spring and dashpot connected in series between the control stick and airplane structure. The device was tested in combination with an experimental elevator and bobweight which had given unsatisfactory dynamic stability and control-feel characteristics in previous tests. The control-feel aid effected marked improvement in both the control-feel characteristics and the control-feel dynamic longitudinal stability of the airplane.
Date:
July 1946
Creator:
Johnson, Harold I.
System:
The UNT Digital Library
Tests of Bell XP-63 Low-Drag Wing Model With Split Flap
Report presenting tests on the Bell XP-63 wing root section fitted with an 0.18c split flap hinged at approximately 0.805c on the lower surface. The tests were conducted to determine the effect of a 10 degree deflection of the split flap on the drag characteristics of the model at low lift coefficients.
Date:
September 1941
Creator:
Underwood, W. J.
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
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
Tests of two models representing intermediate inboard and outboard wing sections of the XB-36 airplane
Report presenting testing in the two-dimensional low-turbulence pressure tunnel and the two-dimensional low-turbulence tunnel of two models made by the Consolidated Aircraft Corporation, one of the outboard section and one of the inboard section.
Date:
January 1943
Creator:
Bogdonoff, Seymour M.
System:
The UNT Digital Library
Lift and Drag Tests of Three Airfoil Models With Fowler Flaps Submitted by Consolidated Aircraft Corporation
Report presenting lift and drag tests made in the two-dimensional tunnel of three airfoil models. The models represented intermediate sections on alternative wings of the XB-32 airplane and were equipped with 0.30 Fowler flaps. Results regarding the Davis model, the C.A.C. model, and low-drag model are provided.
Date:
December 1941
Creator:
Abbott, Ira H. & Turner, Harold R., Jr.
System:
The UNT Digital Library
Effect of Mach and Reynolds Numbers on the Maximum Lift Coefficient Obtainable in Gradual and Abrupt Stalls of a Pursuit Airplane Equipped With a Low-Drag Wing
Report discussing flight tests on a low-drag wing pursuit airplane to determine the effects of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls. The obtainable maximum lift coefficient was found to be greatly affected by the Mach and Reynolds numbers in gradual stall. In abrupt stalls, the maximum lift coefficient was affected by the Mach number, but not the Reynolds number.
Date:
July 6, 1945
Creator:
Spreiter, John R.; Galster, George M. & Blair, William K.
System:
The UNT Digital Library
Lift Tests of a 0.1536c Thick Douglas Airfoil Section of NACA 7-Series Type Equipped With a Lateral-Control Device for Use With a Full-Span Double-Slotted Flap on the C-74 Airplane
Report discussing lift tests on a two-dimensional airfoil model similar to a Douglas C-74 with a double-slotted flap and lateral-control device. Information about the maximum lift coefficient, aileron and flip effectiveness, and flap stall is provided.
Date:
March 1945
Creator:
Nuber, Robert J. & Rice, Fred J., Jr.
System:
The UNT Digital Library
Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts
Report presenting measurements of a Consolidated B-24D airplane of accelerations at various points on the wing during landing impacts. landings were made with the wheels initially stationary but free to rotate, with the brakes set before contact, and with the main wheels rotating prior to contact.
Date:
August 1944
Creator:
Westfall, John R.
System:
The UNT Digital Library
Accelerations and bottom pressures measured on a B-24D airplane in a ditching test
From Introduction: "This report presents only that portion of the data from the first ditching which was to be used roughly establish the accelerations experienced by the pilot and the amount of water pressure to which the fuselage structure was subjected during the ditching."
Date:
November 1944
Creator:
Steiner, Margaret F.
System:
The UNT Digital Library