7,003 Matching Results

Search Results

Results: 1 - 24 next
open access

Full-scale wind-tunnel tests of the longitudinal stability and control characteristics of the XV-1 convertiplane in the autorotating flight range

Description: Force and moments were measured for the XV-1 convertiplane at 75 to 150 knots. Rotor on and off and propeller powered and off configurations were investigated. The characteristics of the V-tab horizontal tail and its downwash field were studied. Lift interference between fixed wing and rotor and possible means of drag reduction were considered.
Date: May 17, 1956
Creator: Hickey, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (Including Canopy Shape Effects)

Description: Memorandum presenting component interference studies that have been made in an attempt to explain the unexpected large loss in damping in roll which occurred in wind-tunnel tests at zero angle of attack for the Bell X-1A research airplane near a Mach number of 2.22. The studies include theoretical calculations of the effect of the body flow field on the wing damping in roll and measurements at several Mach numbers on the contribution of the individual components to the damping in roll.
Date: October 15, 1956
Creator: McDearmon, Russell W. & Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
Date: May 23, 1956
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the damping in roll of the Bell X-1E research airplane and its components at supersonic speeds

Description: Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.
Date: April 26, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the damping in roll of the Bell X-1A research airplane and its components at supersonic speeds

Description: Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.
Date: January 10, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09

Description: Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.
Date: March 23, 1956
Creator: Carmel, Melvin M. & Gregory, Donald T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wind-Tunnel Investigation of a Seaplane Configuration having a 40 Deg Sweptback Wing, TED No. NACA DE 387

Description: From Summary: "During the course of an aerodynamic loads investigation of a model of the Martin XP6M-1 flying boat in the Langley 16-foot transonic tunnel, longitudinal-aerodynamic-performance information was obtained. Data were obtained at speeds up to and exceeding those anticipated for the seaplane in level flight and included the Mach number range from 0.84. to 1.09. The angle of attack was varied from -2deg to 6deg and the average Reynolds number, based on wing mean aerodynamic chord, was … more
Date: April 6, 1956
Creator: Hieser, Gerald; Kudlacik, Louis & Gray, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Minimum drag of the Chance Vought XF8U-1 airplane as determined from the flight test of a 0.11-scale rocket-boosted model at Mach numbers between 0.73 and 1.71: TED No. NACA DE 392

Description: Report presenting drag data obtained from the flight of a 0.11-scale rocket-boosted model of the Chance Vought XF8U-1 airplane over a range of Mach numbers. Results regarding the duct performance, trim normal-force coefficient, total drag, internal and base drag, and external drag are provided.
Date: March 15, 1956
Creator: Hastings, Earl C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal and lateral stability characteristics including effects of transonic area rule and wing modification of a 0.10-scale model of the Douglas A4D-1 airplane at transonic speeds: TED No. NACA AD 3114

Description: Report presenting force tests of a 0.10-scale model of the Douglas A4D-1 airplane in the 8-foot transonic pressure tunnel to investigate the static longitudinal characteristics of wing and fuselage modifications and the static lateral characteristics of the basic model. Tests were conducted over a range of Mach numbers and angles of attack.
Date: August 17, 1956
Creator: Wornom, Dewey E. & Bollech, Thomas V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, Drag, Static Stability, and Buffet Boundaries of a Model of the McDonnell F3H-1N Airplane at Mach Numbers from 0.40 to 1.27, TED No. NACA DE 351

Description: "The National Advisory Committee for Aeronautics has conducted a flight test of a model approximating the McDonnell F3H-1N airplane configuration to determine its pitch-up and buffet boundaries, as well as the usual longitudinal stability derivatives obtainable from the pulsed- tail technique. The test was conducted by the freely flying rocket-boosted model technique developed at the Langley Laboratory; results were obtained at Mach numbers from 0.40 to 1.27 at corresponding Reynolds numbers of… more
Date: January 31, 1956
Creator: Crabill, Norman L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static Longitudinal and Lateral Stability Characteristics Including Effects of Transonic Area Rule and Wing Modification of a 0.10- Scale Model of the Douglas A4D-1 Airplane at Transonic Speeds

Description: Report discussing testing of a model of the Douglas A4D-1 to investigate the static longitudinal characteristics of wing and fuselage modifications and the static lateral characteristics of the basic model.
Date: July 6, 1956
Creator: Bollech, Thomas V. & Wornom, Dewey E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Concluding Report on Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

Description: "An investigation has been completed in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a re… more
Date: August 14, 1956
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine 1: Nonafterburning Configurations

Description: "Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in a representative nonafterburning position. Jet-thrust and air-handling data were obtained in quiescent air for 11 selected ejector configurations over a wide range of operation. Additional data, at specific operating conditions, were obtained which indicate the ejector diameter ratio for peak jet-thrust performance. The experimental ejector data are presented in both graphical and tab… more
Date: August 30, 1956
Creator: Greathouse, William K. & Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static lateral and directional stability and control characteristics of a 1/15-scale model of the Grumman F11F-1 airplane at Mach numbers of 1.41, 1.61, and 2.01: TED No. NACA DE 390

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static lateral and directional stability and control characteristics of a scale model of the Grumman F11F-1 airplane at Mach numbers of 1.41, 1.61, and 2.01. The complete model and various combinations of component parts were tested as well as various configuration changes including modified bodies and vertical tails. Results regarding the static lateral and directional stability, lateral and dire… more
Date: November 29, 1956
Creator: Robinson, Ross B. & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

TEMPERATURE DISTRIBUTION AND THERMAL STRESS IN REACTOR CORE APPR-1

Description: The feasibility of the Liquid Metal Fuel Reactor (LMFR) proposed by Brookhaven National Laboratory as a source of electric power was thoroughly investigated. The reference design is based on an LMFR using U dissolved in Bi as the fuel and a thorium bismuthide in Bi slurry as the blanket. Detailed estimates of power costs are presented for electrical power stations from 226 to 904 Mw net electrical capability. (C.W.H.)
Date: February 15, 1956
Creator: Berggren, W. P. & Kroeger, H. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53

Description: Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coe… more
Date: November 30, 1956
Creator: Turner, Kenneth L. & Fournier, Roger H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen