Technical Report Archive & Image Library (TRAIL) - 5,157 Matching Results

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Investigation of an NACA Submerged Inlet at Mach Numbers from 1.17 to 1.99

Description: Memorandum presenting an investigation conducted with an NACA submerged inlet at Mach numbers from 1.17 to 1.99. Total-pressure ratio, mass-flow ratio, and static pressure distribution along the ramp and main body were obtained at angles of attack of 0 and 6 degrees for a side inlet location. The results showed that the maximum total-pressure ratio attainable with the submerged inlet decreased from 0.83 at a Mach number of 1.17 to 0.52 at a Mach number of 1.99.
Date: September 15, 1952
Creator: Anderson, Warren E. & Frazer, Alson C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a Flow Deflector and an Auxiliary Scoop for Improving Off-Design Performance of Nose Inlets

Description: Memorandum presenting an investigation of flow deflectors which extend forward of an open-nose inlet for improving positive angle-of-attack performance and auxiliary scoops for use at off-design engine air-flow conditions at low angles of attack to determine their effect on net inlet performance. The results show that a deflector inlet and a basic open-nose inlet have about the same net performance at low angles of attack although the flow steadiness characteristics of the deflector inlet are t… more
Date: July 20, 1954
Creator: Anderson, Warren E. & Scherrer, Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal stability characteristics of the Convair YF-102 airplane determined from flight tests

Description: Report presenting an analysis of the longitudinal stability characteristics of the cambered-wing version of the Convair YF-102 airplane at a range of Mach numbers and altitudes. Results regarding longitudinal trim, stall maneuvers, dynamic longitudinal stability, maneuvering stability, stability and control effectiveness parameters, and artificial-feel system are provided.
Date: December 13, 1956
Creator: Andrews, William H.; Sisk, Thomas R. & Darville, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Initial Flight Test of the NACA FR-1-A, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting testing on the first of a series of flutter rockets, designated the NACA FR-1-A, which was tested with two identical swept wings. Results regarding the launching, flight, and wing failure are provided.
Date: June 29, 1948
Creator: Angle, Ellwyn E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of Longitudinal Stability of the Bell X-1 Airplane From Transient Responses at Mach Numbers Up to 1.12 at Lift Coefficients of 0.3 and 0.6

Description: Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.
Date: November 7, 1950
Creator: Angle, Ellwyn E. & Holleman, Euclid C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Frequency-Response Characteristics of the Douglas D-558-I Airplane as Determined From Experimental Transient-Response Histories to Mach Number of 0.90

Description: Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.
Date: February 11, 1952
Creator: Angle, Ellwyn E. & Holleman, Euclid C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight and Wind-Tunnel Investigation to Determine the Aileron-Vibration Characteristics of 1/4-Scale Wing Panels of the Douglas D-558-2 Research Airplane

Description: Report presenting a flight and wind-tunnel investigation to determine the aerodynamic vibration characteristics of ailerons for the Douglas D-558-2 airplane. Testing was conducted to investigate the possibilities of a single-degree-of-freedom flutter known as aileron "buzz" or aileron compressibility flutter. Results regarding the three types of aileron vibration observed and vibration amplitudes are provided.
Date: November 30, 1948
Creator: Angle, Ellwyn E. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of Longitudinal Stability in Supersonic Accelerated Maneuvers for the Douglas D-558-II Research Airplane

Description: Report discussing testing of a Douglas D-558-II to investigate its longitudinal stability characteristics in accelerated flight at supersonic speeds. Information about the normal-force coefficients and their relation to stability and pitch-up of the aircraft is included.
Date: February 17, 1954
Creator: Ankenbruck, Herman O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Measurements of Flying Qualities of a Douglas D-558-II Research Airplane During Flights to Supersonic Speeds

Description: Report presenting some measurements of the dynamic lateral stability and lateral and longitudinal trim of a Douglas D-558-II in flights up to a Mach number of 1.87 and an altitude of about 67,000 feet. Testing indicated that the airplane flying in low density air at supersonic speeds had poor dynamic lateral stability, which worsened as the Mach number was increased to 1.85.
Date: March 10, 1953
Creator: Ankenbruck, Herman O. & Dahlen, Theodore E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Motions Encountered with the Douglas D-558-II All-Rocket Research Airplane During Exploratory Flights to a Mach Number of 2.0

Description: Memorandum presenting flight tests performed with the Douglas D-558-II research airplane in order to determine the lateral handling characteristics in straight flight at supersonic speeds. It primarily describes the lateral motions obtained at moderate and low angles of attack during a preliminary survey in pushovers and straight flight at supersonic Mach numbers up to about 2.0 at altitudes between 50,000 and 70,000 feet.
Date: December 17, 1954
Creator: Ankenbruck, Herman O. & Wolowicz, Chester H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds

Description: Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.
Date: January 17, 1956
Creator: Arabian, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Directional Behavior of a Swept Planing-Tail Hull

Description: "A qualitative investigation of the low-speed directional behavior of a swept planing-tail hull was made in the Langley tank no. 2 in still water and still air with the use of a free self-propelled model. The configuration was directionally unstable over a range of low speed. It was, however, directionally controllable at all speeds by use of the rudder and elevator. Several modifications that were investigated did not improve the controllability" (p. 1).
Date: January 10, 1952
Creator: Arabian, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at transonic speeds of loading over a 30 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body

Description: Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.
Date: September 26, 1957
Creator: Arabian, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Stability and Control Measurements of a 0.0858-Scale Model of the Lockheed XF-104 Airplane at Transonic Speeds

Description: An investigation of the lateral stability and control effectiveness of a 0.0858-scale model of the Lockheed XF-104 airplane has been conducted in the Langley 16-foot transonic tunnel. The model has a low aspect ratio, 3.4-percent-thick wing with negative dihedral. The horizontal tail is located on top of the vertical tail. The investigation was made through a Mach number range of 0.80 to 1.06 at sideslip angles of -5 deg. to 5 deg. and angles of attack from 0 deg. to 16 deg. The control effecti… more
Date: June 8, 1955
Creator: Arabian, Donald D. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail

Description: Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.
Date: June 12, 1956
Creator: Arabian, Donald D. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.
Date: August 28, 1956
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: "Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).
Date: February 11, 1955
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing of the Northrop MX-775A Missile With Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.
Date: February 11, 1955
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Longitudinal-Stability Investigation Including Some Effects of Wing Elasticity From Mach Numbers of 0.85 to 1.34 of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 5.5

Description: Report presenting a free-flight longitudinal-stability investigation between Mach numbers of 0.85 and 1.34 to obtain the aerodynamic characteristics of a long-range, jet-propelled, ground-to-ground missile with a wing of aspect ratio 5.5, 45 degrees of sweepback, and taper ratio 0.4 on a body with a vertical tail. Two models with two different wing materials were flown. Results regarding trimmed flight, pitching flight, and aeroelastic calculations are provided.
Date: August 10, 1953
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of rocket-model tests at zero lift of an arrow-wing missile configuration from Mach numbers of 0.9 to 1.8

Description: Report presenting flight tests conducted between Mach numbers of 0.9 to 1.8 over a range of Reynolds numbers to determine the zero-lift drag and some rolling-effectiveness characteristics of a proposed long-range, supersonic, ground-to-ground missile. Results regarding the longitudinal trim, drag, rolling effectiveness, and instability due to roll are provided.
Date: January 14, 1954
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of Rocket-Model Tests at Zero Lift of the Northrop MX-775B Missile Configuration from Mach Numbers of 0.9 to 1.8

Description: Flight tests were conducted between Mach numbers of 0.9 and 1.8 over a Reynolds number range of 9(exp 6) to 30(exp 6) to determine the zero-lift drag and some rolling-effectiveness characteristics of the Northrop MX -775B missile with small and large body. The MX-775B is a proposed long range, supersonic, ground-to-ground missile having an arrow wing with 67.5 degree leading-edge sweep, 15 deg trailing-edge sweep, and a modified NACA 0004 airfoil section. The configuration has no horizontal tai… more
Date: October 1, 1953
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some approximate methods for estimating the effects of aeroelastic bending of rocket-propelled model-booster combinations

Description: Report presenting methods for estimating the aeroelastic effects and structural requirements of rocket-propelled model-booster combinations that are nearly symmetrical. The methods differ principally in the manner in which booster stiffness, reference axis, and inertia loading are considered. Special conditions and accuracy for each of the three models are provided.
Date: March 27, 1953
Creator: Arbic, Richard G.; White, George & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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