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Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane

Description: Memorandum presenting rudder pulse maneuvers obtained with the Convair XF-92A delta-wing research airplane at an altitude of about 30,000 feet over a Mach number range of 0.52 to 0.92. Tests were made with and without a wing fence. By analyzing the maneuvers, the characteristics of the airplane transient, airplane stability derivatives, and frequency-response characteristics were measured.
Date: August 5, 1955
Creator: Holleman, Euclid C.
Partner: UNT Libraries Government Documents Department
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Flight Determination of the Longitudinal Stability and Control Characteristics of a 0.125-Scale Rocket-Boosted Model of the Mcdonnell F-101 Airplane at Mach Numbers from 0.82 to 1.84

Description: From Summary: "A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.125-scale model of the McDonnell F-101A airplane for the Mach number range between 0.82 and 1.84. The variation of lift-curve slope with Mach number was gradual with a maximum value of 0.107 occurring at a Mach number of 0.95. The minimum drag coefficient (including base and internal drag) has a value of 0.020 at a Mach number of 0.87. The drag rise begins at a Mach number … more
Date: July 5, 1955
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department
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Investigation of the Effect of Balancing Tabs on the Hinge-Moment Characteristics of a Trailing-Edge Flap-Type Control on a Trapezoidal Wing at a Mach Number of 1.61

Description: Report presenting an investigation at Mach number 1.61 to determine the effect of 10-percent control are attached tabs on the hinge-moment characteristics of a trailing-edge flap-type control on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Results regarding hinge-moment coefficients, tab parameters, and control effectiveness are provided.
Date: August 5, 1954
Creator: Lord, Douglas R. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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Comparison Between Theoretical and Experimental Rates of Roll of Two Models with Flexible Rectangular Wings at Supersonic Speeds

Description: "A comparison is presented between the experimentally measured and theoretically calculated (by the method of NACA TN 3067) rates of roll of two rocket-propelled models with flexible rectangular wings. The comparisons show that although there are large aeroelastic losses in rolling rate, the theory predicts the actual rate of roll accurately" (p. 1).
Date: August 5, 1954
Creator: Hedgepeth, John M. & Kell, Robert J.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats

Description: Memorandum presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback in order to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Close to theoretical flap effectiveness was obtained with blowing flaps deflected 45, 55, and 65 degrees at low angles of attack. Results regarding the wind tunnel, take-off performance, landing performance, and comparison… more
Date: July 5, 1957
Creator: James, Harry A. & Maki, Ralph L.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile

Description: "Flutter models of the upper and lower vertical tails of an air-to-ground missile have been tested in the Mach number range from 0.5 to 3.0. It was found that the upper surface exhibited more or less conventional flutter behavior throughout the Mach number range, whereas the lower surface experienced a sudden change in flutter mode at a Mach number of about 1.18. This change in flutter mode was accompanied by a decrease of about 50 percent in the density required for flutter to occur" (p. 1).
Date: June 5, 1957
Creator: Hanson, Perry W. & Rainey, A. Gerald
Partner: UNT Libraries Government Documents Department
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Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine

Description: Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.
Date: March 5, 1951
Creator: Cook, William P. & Butze, Helmut F.
Partner: UNT Libraries Government Documents Department
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Aircraft configurations developing high lift-drag ratios at high supersonic speeds

Description: From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."
Date: March 5, 1956
Creator: Eggers, A. J., Jr. & Syvertson, Clarence A.
Partner: UNT Libraries Government Documents Department
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Icing Characteristics and Anti-Icing Heat Requirements for Hollow and Ternally Modified Gas-Heated Inlet Guide Vanes

Description: "A two-dimensional inlet-guide-vane cascade was investigated to determine the effects of ice formations on the pressure losses across the guide vanes and to evaluate the heated gas flow and temperature required to prevent Icing at various conditions. A gas flow of approximately 0.4 percent of the inlet-air flow was necessary for anti-icing a hollow guide-vane stage at an inlet-gas temperature of 500 F under the following icing conditions: air velocity, 280 miles per hour; water content, 0.9 gra… more
Date: December 5, 1950
Creator: Gray, Vernon H. & Bowden, Dean T.
Partner: UNT Libraries Government Documents Department
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Effects of Surface Roughness and Extreme Cooling on Boundary-Layer Transition for 15 Degrees Cone-Cylinder in Free Flight at Mach Numbers to 7.6

Description: Report presenting an investigation of three cone-cylinder bodies to obtain boundary-layer-transition data at very low ratios of wall to local stream temperature. Surface finishes at several levels of roughness height were tested. Results regarding the smooth body and rough bodies are provided.
Date: March 5, 1958
Creator: Rabb, Leonard & Krasnican, Milan J.
Partner: UNT Libraries Government Documents Department
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Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance

Description: Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date: August 5, 1954
Creator: Weber, Richard J. & Luidens, Roger W.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of Missiles Employing Wings of Very Low Aspect Ratio

Description: Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.
Date: March 5, 1956
Creator: Katzen, Elliott D. & Jorgensen, Leland H.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Free-Flight Measurements of the Zero-Lift Drag Rise of Six Airplane Configurations and Their Equivalent Bodies of Revolution at Transonic Speeds

Description: "Free-flight drag measurements are presented which show the practicability of duplicating the zero-lift drag rise of many airplane configurations by simple bodies of revolution. The results confirm the transonic area rule for straight wings, and for delta and modified-delta wings with and without nacelles. The results showed that the area rule did not apply to one swept-wing configuration and an explanation is advanced to explain why it does not apply" (p. 1).
Date: January 5, 1954
Creator: Hall, James Rudyard
Partner: UNT Libraries Government Documents Department
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Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method

Description: Report presenting measurements using the NACA wing-flow method of the lift, pitching-moment, and hinge-moment characteristics of a 35 degree sweptback NACA 65-009 airfoil of aspect ratio 3.04 with a full-span 1/4-chord unsealed plain flap. The tests were carried out at a range of Mach numbers, Reynolds numbers, angles of attack, and flap deflections. Variations of lift and pitching moment with angle of attack or flap deflection were approximately rectilinear at all Mach numbers for moderate ang… more
Date: August 5, 1947
Creator: Johnson, Harold I.
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of NACA submerged air inlets on a 1/5-scale model of a fighter airplane

Description: From Summary: "The results of an experimental investigation of an NACA submerged-air-inlet system on a 1/5-scale model of a fighter airplane are presented. Preliminary development tests were conducted to select the optimum entrance configuration. Duct-system total-pressure losses and pressure distributions over the lip and ramp of this air intake were obtained."
Date: December 5, 1947
Creator: Gault, Donald E.
Partner: UNT Libraries Government Documents Department
open access

Full-Scale Investigation of Boundary-Layer Control by Suction Through Leading-Edge Slots on a Wing-Fuselage Configuration Having 47.5 Degree Leading-Edge Sweep With and Without Flaps

Description: Report discussing the effects of suction through slots at the .5 percent chord and 2.5 percent chord stations on the longitudinal aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage configuration with and without flaps. Information about the Reynolds number effects, characteristics of the plain wing, wing with split flaps, extensible leading-edge flaps, the effect of power failure, and the drag coefficients is provided.
Date: April 5, 1950
Creator: Pasamanick, Jerome & Sellers, Thomas B.
Partner: UNT Libraries Government Documents Department
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Measurement of Uniform Flame Movement in Carbon Monoxide - Air Mixtures Containing Either Added D2O or H2O

Description: Relative velocities of the flame in a carbon monoxide - air mixture containing either added heavy water or light water were measured in a glass tube. Throughout the range of carbon monoxide - air composition, the flame containing added light water had a faster speed than the flame containing heavy water.
Date: July 5, 1950
Creator: McDonald, Glen E.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet

Description: Report presenting an investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles through a range of Mach numbers by use of a transonic bump. Results regarding the ram-recovery ratio, pressure distributions, and tuft studies are provided.
Date: June 5, 1950
Creator: Axelson, John A. & Taylor, Robert A.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Supersonic Flow With Detached Shock Waves for Mach Numbers Between 1.8 and 2.9

Description: Memorandum presenting results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves, which are compared with predictions of theory. The location of the detached shock wave was determined from schileren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. Results regarding schileren photographs, shock-location parameter, effect of b/T on shock form, effect of body form… more
Date: July 5, 1950
Creator: Moeckel, W. E.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections

Description: Report discussing testing to determine the aerodynamic characteristics of two semispan delta-wing configurations. Information about the lift characteristics, drag characteristics, pitching-moment characteristics, and comparison with other results is provided.
Date: May 5, 1950
Creator: Hall, Albert W. & Morris, Garland J.
Partner: UNT Libraries Government Documents Department
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Flight determination of the effects of rudder-pedal-force characteristics on the aiming error in azimuth of a conventional fighter airplane

Description: Report presenting flight tests to study the effect on aiming error in azimuth of a change in the rudder-pedal-force characteristics of a conventional fighter airplane equipped with an illuminated fixed gunsight. The effect of the modification on the mean azimuth tracking errors was insignificant, but pilots noted that the modified rudder made it tiring to fly the airplane for any length of time.
Date: July 5, 1950
Creator: Winograd, Lee & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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Flight investigation of the heat requirements for ice prevention on aircraft windshields

Description: Report presenting a flight investigation conducted to establish the heat requirements for ice prevention on aircraft windshields mounted on the forebody of an airplane at several angles. Electrically heated windshields were used in order to provide accurate measuring of heat input to the windshield. Results regarding the quantity of heat provided, amount of water collection, ideal windshield angle, ranges in airplane velocity, and icing conditions are provided.
Date: September 5, 1947
Creator: Kleinknecht, Kenneth S.
Partner: UNT Libraries Government Documents Department
open access

Precautions for Flight Testing Near the Speed of Sound

Description: From experience gained by NACA test pilots in flying at high subsonic Mach numbers and from interpretation of the data obtained, some general precautionary rules for test flying near sonic Mach numbers have been formulated. The reasons for these rules are discussed and observations are made with respect to the hazards arising from undesirable stability and control characteristics which have been noted in test flights of various airplanes. This paper, although written primarily for the attention… more
Date: November 5, 1947
Creator: Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department
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