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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.
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Tests of Wickwire-Spencer Propeller

Description: 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
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Longitudinal Stability at High Speeds of a 1/5-Scale Model of a Tailless Pursuit Airplane

Description: "Tests of a tailless pursuit airplane model at the Ames Aeronautical Laboratory have shown that in conditions corresponding to level flight at a Mach number less than 0.7 and at an altitude under 35,000 feet, no serious compressibility effects occurred and that no sudden adverse diving moments were encountered up to a Mach number of 0.74, the maximum speed of the tests. However, there were indications that the elevons might lose their effectiveness for longitudinal control during a pull-out fro… more
Date: March 1943
Creator: Laitone, Edmund V.
Partner: UNT Libraries Government Documents Department
open access

Effect in Flight of the Propeller Cuffs and Spinner on Pressure Recovery in Front of a Double-Row Radial Aircraft Engine in a Twin-Engine Airplane

Description: Report presenting an investigation conducted with the propeller cuffs and spinner removed to determine their effect in flight on the pressure recovery of the cooling-air flow. Curves are presented to compare the pressure and temperature distribution over the front row of cylinders for flights with and without cuffs and spinner.
Date: March 1944
Creator: Ellisman, Carl
Partner: UNT Libraries Government Documents Department
open access

Loss of xylidines in overwater storage of xylidine-blended fuel

Description: Tests were undertaken to determine the relationships for estimating the maximum amount of a water-soluble gasoline additive that will diffuse from the gasoline to the water when fuel is stored over the water and to determine from the relationships the amount of xylidines that will diffuse from the gasoline to the water in an overwater-storage system.
Date: March 1944
Creator: Tischler, Adelbert O. & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department
open access

Measurements of flying qualities of a Curtiss SB2C-1 airplane (number 00014)

Description: Report presenting an investigation of the flying qualities of a Curtiss SB2C-1 airplane. Tests were made to determine the effect of a bobweight in the elevator system and the effect of seals in the aileron gaps. Results regarding longitudinal stability and control, requirements for lateral stability and control, and stalling characteristics are provided.
Date: March 1944
Creator: Phillips, W. H.; Williams, W. C. & Hoover, H. H.
Partner: UNT Libraries Government Documents Department
open access

Force Test of a 1/5-Scale Model of the Type GB-5 Controllable Glide Bomb

Description: Report presenting information regarding the development of a type GB-5 controllable glide bomb equipped with a target-seeking device. The model was tested on the six-component balance in order to measure the stability and control characteristics of the bomb in its original condition and with various modifications. Results regarding the effect of end plates on dihedral parameter, effect of vertical-tail arrangement on directional stability, aileron tests, and glide-path control are provided.
Date: March 27, 1944
Creator: Pitkin, Marvin
Partner: UNT Libraries Government Documents Department
open access

Characteristics of Several Single- and Dual-Rotating Propellers in Negative Thrust

Description: Report discusses the thrust and power characteristics of several single- and dual-rotating propellers with differing blade width and number of blades for negative-thrust operation from -45 degrees to 145 degrees blade angle. From Summary: "The tests indicate that it is possible to predict for a given propeller design characteristics in the negative-thrust range from known characteristics at a different activity factor. Adequate negative thrusts were indicated for extremely high positive as well… more
Date: March 1945
Creator: Gray, W. H. & Gilman, Jean, Jr.
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of a Rudder With a Spring Tab on an F6F-3 Airplane (BuAer No.04776)

Description: Report discussing testing on an F6F-3 with a spring-tab rudder to determine the directional stability and control characteristics. Using the spring-tab rudder was found to result in lower trim-force change with speed and lower pedal forces in sideslips than the original rudder. Pilots were found to prefer the maneuverability of this configuration.
Date: March 1945
Creator: Williams, Walter C.
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of the Sikorsky HNS-1 (Army YR-4B) Helicopter 1: Experimental Data on Level-Flight Performance With Original Rotor Blades

Description: "Results of performance measurements made in level fight with the HNS-1 (Army YR-4B) helicopter are presented. These data include torquemeter measurements of shaft power for both the main rotor and the tail rotor. The power data, in conjunction with full-scale-tunnel date on the lift and drag of the fuselage, are used to calculate the drag-lift ratio for the main rotor" (p. 1).
Date: March 1945
Creator: Gustafson, F. B.
Partner: UNT Libraries Government Documents Department
open access

High-Speed Photographs of a YR-4B Production Rotor Blade for Simulated Flight Conditions in the Langley Full-Scale Tunnel

Description: Report discussing tests of a Sikorsky YR-4B helicopter, including photography of a rotor blade in forward-flight conditions at several azimuth angles for several tip-speed ratios. Fabric deformation in the form of sagging and bulging was noted. A reversal in the bending curve near the blade tip was also noted, which was hypothesized to come from losses of lift and high centrifugal force.
Date: March 1945
Creator: Dingeldein, Richard C. & Schaefer, Raymond F.
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Slipstream Effects on a Wing-Inlet Oil-Cooler Ducting System of a Twin-Engine Airplane in the Ames 40- by 80-Foot Wind Tunnel

Description: Report discussing an investigation of wing-inlet oil-cooler ducts on a twin-engine airplane to determine internal and external-flow characteristics of the ducting installation. Testing was also performed on revised inlets to attempt to develop a ducting system with low overall losses throughout the operating range.
Date: March 10, 1945
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Modified Baffles and Auxiliary-Cooling Ducts on the Cooling of a Double-Row Radial Engine

Description: Report discussing testing to determine the cooling effect of modified baffles and auxiliary-cooling ducts on the rear-row cylinders of a double-row radial engine. The modified baffles were found to reduce the temperatures of the exhaust-valve seats, but did not have an effect on the valve-guide temperatures. The auxiliary-cooling ducts reduced temperatures of the exhaust-valve seats and rear spark plug gaskets.
Date: March 20, 1945
Creator: Gendler, Stanley L. & Geisenheyner, Robert M.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade

Description: From Summary: "A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of symmetry, the measured aerodynamic characteristics cor… more
Date: March 29, 1945
Creator: Kemp, William B., Jr.
Partner: UNT Libraries Government Documents Department
open access

Operating Stresses in Aircraft-Engine Crankshafts and Connecting Rods 1: Slip-Ring and Bush Combinations for Dynamic-Strain Measurements

Description: "Tests were conducted to develop a slip-ring and brush system that will perform satisfactorily in aircraft-engine, dynamic-strain-measuring applications where resistance-wire strain gages are the means of measuring the strain and to correlate the data obtained from tests in order to provide a basis for predicting the performance of similar slip-ring and brush systems operating under conditions similar to those imposed by these tests." 24 combinations of materials were tested dry and 8 were test… more
Date: March 30, 1945
Creator: Dutee, Francis J.; Phillips, Franklyn W. & Kemp, Richard H.
Partner: UNT Libraries Government Documents Department
open access

An Evaluation of the Knock-Limited Performance of Triptane

Description: Report discussing an investigation of the knock-limited performance of triptane in F-3 and F-4 rating engines, two full-scale air-cooled aircraft cylinders, and flight tests on a full-scale multicylinder engine. Information about the lead susceptibility and effect of engine operating conditions is also provided.
Date: March 1946
Creator: Barnett, Henry C.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Ice Formation in the Induction System of an Aircraft Engine 1: Ground Tests

Description: "Ground tests were conducted on a twin-engine fighter airplane to study icing of an induction system incorporating an exhaust-driven turbosupercharger. The ground tests were made to determine the disposition of free water in the induction system of the airplane, to determine the charge-air heat rise available from the turbosupercharger, and to correlate actual airplane-test results with those of laboratory tests" (p. 1).
Date: March 1946
Creator: Essex, Henry A.; Zlotowski, Edward D. & Ellisman, Carl
Partner: UNT Libraries Government Documents Department
open access

Test-Stand Investigation of Cooling Characteristics and Factors Affecting Temperature Distribution of a Double-Row Aircraft Engine

Description: Report presenting testing of a double-row radial air-cooled engine to investigate overall cooling characteristics and to analyze what variations in temperature distribution were caused by variations in cooling-air pressure drop, power, and fuel-air ratio. Testing occurred over a range of engine powers.
Date: March 1946
Creator: Sipko, Michael A.; Hickel, Robert O. & Jones, Robert J.
Partner: UNT Libraries Government Documents Department
open access

Tests of a 1/7-Scale Powered Model of the Kaiser Tailless Airplane in the Langley Full-Scale Tunnel

Description: Report discussing testing of a model of the Kaiser tailless airplane in order to determine its general aerodynamic characteristics and the probable stability and control characteristics. Only the results of the tests are presented in this report; the estimated flying qualities are in a separate report. Information about the lift, stall, drag, elevator effectiveness and hinge moments, rudder effectiveness and hinge moments, aileron effectiveness and hinge moments, and characteristics in yaw is i… more
Date: March 1946
Creator: Brewer, C. W. & Rickey, E. A.
Partner: UNT Libraries Government Documents Department
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