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Flying qualities of a high-performance personal-owner airplane

Description: Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.
Date: November 8, 1951
Creator: Adams, James J. & Whitten, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane

Description: Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies… more
Date: March 19, 1951
Creator: Aiken, William S., Jr. & See, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics: transonic bump method

Description: Report presenting the results of an experimental investigation of the downwash and longitudinal stability characteristics of a semispan, triangular-wing airplane model with a horizontal tail. Lift, drag, and pitching-moment data re presented for the wing-fuselage combination. Results indicated that the model with the tail on or below the wing-chord plane possessed satisfactory stability characteristics throughout the test range of lift coefficient.
Date: August 17, 1951
Creator: Allen, Edwin C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of flow over inclined bodies of revolution

Description: From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly ac… more
Date: March 5, 1951
Creator: Allen, H. Julian & Perkins, Edward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements in Flight of the Longitudinal Characteristics of Two Jet Aircraft, One With a Diving Tendency and the Other With a Climbing Tendency at High Mach Numbers

Description: Memorandum presenting flight tests conducted on two straight-wing jet airplanes of generally similar configuration, one exhibiting a diving tendency and the other a climbing tendency, in order to investigate the cause for the particular type of behavior of each airplane at high Mach numbers. The results showed that the diving tendency experienced by the one airplane was due to the predominant effect of an increased angle of attack of the horizontal tail.
Date: October 5, 1951
Creator: Anderson, Seth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight measurements of the wing-dropping tendency of a straight-wing jet airplane at high subsonic Mach numbers

Description: From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sens… more
Date: April 24, 1951
Creator: Anderson, Seth B.; Ernst, Edward A. & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system

Description: The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Date: October 23, 1951
Creator: Armstrong, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

Description: Effects of air-cooling turbine rotor blades on performance of a turbojet engine were calculated for a range of altitudes from sea level to 40,000 feet and a range of coolant flows up to 3 percent of compressor air flow, for two conditions of coolant bleed from the compressor. Bleeding at required coolant pressure resulted in a sea-level thrust reduction approximately twice the percentage coolant flow and in an increase in specific fuel consumption approximately equal to percentage coolant flow.… more
Date: August 13, 1951
Creator: Arne, Vernon L. & Nachtigall, Alfred J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter

Description: Report presenting an investigation of the effects of many of the parameters significant to wing flutter on several untwisted rotating models to determine their significance with respect to stall flutter of propeller blades. The parameters included torsional stiffness, section thickness ratio, sweepback, length-chord ratio, section center-of-gravity location, blade taper, Mach number, and fluid density. Results regarding the considerations on method of presentation, experimental data and discuss… more
Date: January 31, 1951
Creator: Baker, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Fuel Volatility on Performance of Tail-Pipe Burner

Description: Fuels having Reid vapor pressures of 6.3 and 1.0 pounds per square inch were investigated in a tail-pipe burner on an axial-flow-type turbojet engine at a simulated flight Mach number of 0.6 and altitudes from 20,000 to 45,000 feet. With the burner configuration used in this investigation, having a mixing length of only 8 inches between the fuel manifold and the flame holder, the low-vapor-pressure fuel gave lower combustion efficiency at a given tail-pipe fuel-air ratio. Because the exhaust-no… more
Date: April 30, 1951
Creator: Barson, Zelmar & Sargent, Arthur F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques

Description: Report discussing the results of an investigation to determine the stability and control characteristics of a flying model of an unswept-wing vertically rising airplane. Information about stabilization, maneuverability, rolling motions, and landings is provided.
Date: November 6, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight

Description: Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.
Date: February 23, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Water Landing Investigation of a Hydro-Ski Model at Beam Loadings of 18.9 and 4.4

Description: Report presenting an investigation of water landings in the impact basin with a model with a flat rectangular planing surface, a pulled-up bow, and a simulated landing wheel. Runs were made at several wave conditions, trim ranges, flight-path angles, and beam loadings. The results were found to be applicable in predicting loads and motions exhibited by a flat rectangular ski during impact with a water surface.
Date: September 12, 1951
Creator: Batterson, Sidney A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Centrifugal Compressor Performance With Water Injection

Description: The effects of water injection on a compressor are presented. To determine the effects of varying water-air ratio, the compressor was operated at a constant equivalent impeller speed over a range of water-air ratios and weight flows. Operation over a range of weight flows at one water-air ratio and two inlet air temperatures was carried out to obtain an indication of the effects of varying inlet air temperature. Beyond a water-air ratio of 0.03 there was no increase in maximum air-weight flow, … more
Date: July 18, 1951
Creator: Beede, William L.; Hamrick, Joseph T. & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Effects of Wing Vortex Generators of the Aerodynamic Characteristics of the Douglas D-558-I Airplane

Description: Report presenting testing using a Douglas D-558-I airplane to determine the effect of wing vortex generators on some of the undesirable handling characteristics of aircraft flying at hypercritical speeds. The effects on buffeting, lateral unsteadiness, change in trim, and loss of control effectiveness were the primary objectives.
Date: August 14, 1951
Creator: Beeler, De E.; Bellman, Donald R. & Griffith, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Variation of the pressure limits of flame propagation with tube diameter for propane-air mixtures

Description: An investigation was made of the variation of the pressure limits of flame propagation with tube diameter for quiescent propane with tube diameter for quiescent propane-air mixtures. Pressure limits were measured in glass tubes of six different inside diameters, with a precise apparatus. Critical diameters for flame propagation were calculated and the effect of pressure was determined. The critical diameters depended on the pressure to the -0.97 power for stoichiometric mixtures. The pressure d… more
Date: December 5, 1951
Creator: Belles, Frank E. & Simon, Dorothy M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting free-floating fuel tanks attached to the wing tips

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting, free-floating fuel tanks attached to the wing tips. The results showed that the flight behavior of the configuration could be made satisfactory when sufficient restoring moment was supplied. Results regarding the flight behavior, rolling motions, motions of the bomber and attached tanks, and flight records f… more
Date: August 7, 1951
Creator: Bennett, Charles V. & Cadman, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a tip-to-tip bomber-fighter coupled airplane configuration

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a coupled airplane configuration with simplified fighter models attached to the wing tips of a simplified bomber model. The configuration is meant to represent fighter airplanes carried on the wing tips of a bomber airplane to provide fighter protection for the bomber or for in-flight fueling. Results regarding the fighters attached with freedom in roll, with fr… more
Date: April 4, 1951
Creator: Bennett, Charles V. & Cadman, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supplementary Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane in the Swept-Wing Configuration with Slats Extended

Description: "A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/30 -scale model of the Grumman XF10F-1 airplane to determine what effect full-span slats would have on the spin-recovery characteristics of the swept-wing version of the XF10F-1 airplane, which had previously been indicated as possessing undesirable spin-recovery characteristics without slats. The effects of extended nose-wheel doors and of fairing the air-duct inlets were also determined" (p. 1… more
Date: July 24, 1951
Creator: Berman, Theodore & Klinar, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Fuselage Interference, Wing Interference, and Sweepback on the Damping in Roll of Untapered Wings as Determined by Techniques Employing Rocket-Propelled Vehicles

Description: Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.
Date: October 8, 1951
Creator: Bland, William M., Jr. & Dietz, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Estimation of Neutron Energy for First Resonance From Absorption Cross Section for Thermal Neutrons

Description: Examination of published data for some 52 isotopes indicates that the neutron energy for which the first resonance occurs is related to the magnitude of the thermal absorption cross section. The empirical relation obtained is in qualitative agreement with the results of a simplified version of the resonance theory of the nucleus of Breit-Wigner.
Date: September 17, 1951
Creator: Bogart, Donald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A comparison of the experimental and theoretical loading over triangular wings in sideslip at supersonic speeds

Description: The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 3… more
Date: May 18, 1951
Creator: Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A comparison of the experimental and theoretical loading over triangular wings at supersonic speeds

Description: Report presenting the results of an experimental investigation of the pressure distribution over two triangular wings at supersonic speeds. The two wings which were tested had identical plan forms, 45 degrees of sweepback of the leading edge, and an aspect ratio of 4.0, but different airfoil sections. Results regarding the pressure distribution at zero lift, flow characteristics and pressure distribution at angles of attack, normal-force coefficients, and application of results to other triangu… more
Date: January 3, 1951
Creator: Boyd, John W. & Phelps, E. Ray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: June 25, 1951
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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