National Advisory Committee for Aeronautics (NACA) - 25 Matching Results

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Altitude Acceleration Investigation of the RA-14 Avon Turbojet Engine

Description: As a part of this investigation, the acceleration characteristics of the engine, using the standard engine fuel-control system, were obtained for conditions simulating flight at altitudes of 35,000 and 50,000 feet with a flight Mach number of 0.4. Rapid and wave-off type accelerations were made at each flight condition, and the transient performance of the engine was recorded with a multiple-channel oscillograph. The parameters are presented graphically in the form of time histories, augmented … more
Date: March 13, 1956
Creator: Russey, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of Tchebichef form of harmonic analysis to the calculation of zero-lift wave drag of wing-body-tail combinations

Description: Report presenting an improvement of the computing procedure of NACA RM A53H17 using a new procedure of harmonic analysis using Tchebichef polynominals. The two main improvements are the simplification of computing procedures and the provision for a comprehensive check solution which includes a direct check of how well the number of harmonics used represent the area-distribution curve.
Date: February 13, 1956
Creator: Holdaway, George H. & Mersman, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag at Model Trim Lift of a 1/15-Scale Convair B-58 Supersonic Bomber

Description: Report presenting an investigation using rocket-propelled model of the Convair B-58 supersonic bomber. Drag at trim lift was obtained for a range of Mach and Reynolds numbers and is compared to data from several other testing facilities.
Date: July 13, 1956
Creator: Hopko, Russell N. & Kinard, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag at Model Trim Lift of a 1/15-Scale Convair B-58 Supersonic Bomber

Description: Memorandum presenting an investigation utilizing a 1/15-scale rocket-propelled model of the Convair B-58 supersonic bomber. The drag at model trim lift was obtained at a range of Mach and Reynolds numbers. A comparison of the drag at transonic speeds and approximately the same Reynolds number showed excellent agreement.
Date: July 13, 1956
Creator: Hopko, Russell N. & Kinard, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Investigation of Release Characteristics of a Streamlined Internal Store From a Simulated Bomb Bay of the Republic F-105 Airplane at Mach Numbers of 0.8, 1.4, and 1.98, Coord. No. AF-222

Description: "An investigation has been conducted in the 27- by 27-inch preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., of the release characteristics of a dynamically scaled streamlined-type internally carried store from a simulated bomb bay at Mach numbers M(sub o) of 0.8, 1.4, and 1.98. A 1/17-scale model of the Republic F-105 half-fuselage and bomb-bay configuration was used with a streamlined store shape of a fineness ratio of 6.00. Simulated altitudes were 3,40… more
Date: June 13, 1956
Creator: Lee, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of the effect of boundary-layer transition on the average heat transfer to a yawed cylinder in supersonic flow

Description: Report presenting the average heat-transfer to the forward half of a circular cylinder measured in a blowdown jet at a stream Mach number of 4.15. Most of the tests was made at a wall-to-stagnation temperature ratio of about 0.8. Report presenting pressure distributions, heat transfer and recovery temperatures, and effect of yaw on transition are provided.
Date: July 13, 1956
Creator: Beckwith, Ivan E. & Gallagher, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Results From a Test in Rough Air at High Subsonic Speeds of a Tailless Rocket Model Having Cruciform Triangular Wings, and a Note on the Calculation of Mean Square Loads of Aircraft in Continuous Rough Air

Description: Report presenting results of testing of a rocket model with cruciform 60 degree triangular wings in continuous rough air at transonic speeds. The wing arrangement tested appears to be useful for improving the accuracy of the results. Results regarding the characteristics of the rough-air response, variation of acceleration with Mach number, and evaluation of the cruciform arrangement are provided.
Date: April 13, 1956
Creator: Vitale, A. James & Mitchell, Jesse L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exploratory Materials and Missile-Nose-Shape Tests in a 4,000 Degrees F Supersonic Air Jet

Description: Report presenting some exploratory materials and nose-shape tests in a small supersonic air jet with a stagnation temperature of approximately 4000 degrees Fahrenheit. Materials considered included graphite, copper, carbon steel, and stainless steel, and the nose shapes included 90 degree total-angle cones, hemispherical-face cylinders, and flat-face cylinders. The aerodynamic heat transfer to flat-face cylinders is appreciably less than to hemispherical-face cylinders.
Date: December 13, 1956
Creator: Purser, Paul E. & Hopko, Russell N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Effect of a Propulsive Jet Positioned According to the Transonic Area Rule on the Drag Coefficients of a Single-Engine Delta-Wing Configuration at Mach Numbers From 0.83 to 1.36

Description: Report discussing testing of a 60 degree delta-wing configuration with an engine located in a pod contiguous to the underside of the fuselage to determine the effects of the flow field and drag, lift, and longitudinal stability. Jet-on drag coefficients were found to be lower than jet-off drag coefficients at transonic speeds. The transonic-area-rule concept was also found to be viable for predicting jet effects on drag for this type of configuration.
Date: April 13, 1956
Creator: Judd, Joseph H. & Falanga, Ralph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force and Pressure-Distribution Measurements at a Mach Number of 3.12 of Slender Bodies Having Circular, Elliptical, and Triangular Cross Sections and the Same Longitudinal Distribution of Cross-Sectional Area

Description: Report presenting an investigation to determine the aerodynamic characteristics of bodies with elliptical and triangular cross sections and to compare the data with a body with circular cross sections. Force tests to determine lift, drag, and pitching-moment characteristics as well as pressure-distribution measurements were made for an angle of attack range.
Date: July 13, 1956
Creator: Lange, Roy H. & Wittliff, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Force, moment, and pressure-distribution characteristics of rectangular wings at high angles of attack and supersonic speeds

Description: Report presenting experimental force and moment data for rectangular wings of aspect ratios 1, 2, and 3 at a range of angles of attack and Mach numbers. Shock-expansion theory was found to adequately predict the span load distribution in the two-dimensional flow region below the shock-detachment angle. Results regarding basic physical data, the attached regime, and the detached regime are provided.
Date: February 13, 1956
Creator: Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-flight investigation at transonic speeds of drag coefficients of a boattail body of revolution with a simulated turbojet exhaust issuing at the base from conical short-length ejectors

Description: Report presenting tests of four 7.5 degree boattail bodies of revolution with secondary air scoops in free flight to find the change in drag coefficient when a simulated turbojet exhaust issued from conical short-length ejectors. Results indicated that the jet-on total drag coefficients were lower throughout the test Mach number range than corresponding jet-off values of the forebody drag coefficient. Results regarding drag and ejector-shroud characteristics are provided.
Date: December 13, 1956
Creator: Falanga, Ralph A. & Leiss, Abraham
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Limited Investigation of Effects of Differential Horizontal-Tail Deflection on Lateral Control Characteristics of Two Swept-Wing Airplane Models at Mach Numbers From 1.4 to 2.0

Description: Memorandum presenting a limited investigation in the supersonic pressure tunnel to determine the effectiveness of differential horizontal-tail deflection for producing lateral control for two swept-wing airplane models in the Mach number range from 1.4 to 2.0. The tests were limited to small tail deflections but included combined angles of attack and sideslip up to about 20 degrees. The tests showed the rolling-moment effectiveness to be essentially constant with sideslip angle but to decrease … more
Date: December 13, 1956
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
open access

Low-speed measurements of static stability, damping in yaw, and damping in roll of a delta, a swept, and an unswept wing for angles of attack from 0 degrees to 90 degrees

Description: Report presenting a low-speed investigation to determine the static and damping derivatives of a 60 degree delta wing, a 45 degree swept wing, and an unswept wing from 0 to 90 degrees angle of attack. Results regarding the static longitudinal stability characteristics, static lateral stability characteristics, damping characteristics.
Date: April 13, 1956
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5: Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number 2.01

Description: Report presenting an investigation of store interference in the supersonic pressure tunnel at Mach number 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The interference effects measured at that Mach number were similar to those reported previously at Mach number 1.61. Results regarding store drag, store lift, store side force, store pitching moment and yawing moment, wing-fuselage drag, wing-fuselage lift, total drag, total lift, and wing-fuselage… more
Date: February 13, 1956
Creator: Carson, Harry W. & Geier, Douglas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5 - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number, 2.01

Description: Memorandum presenting a supersonic wind-tunnel investigation of store interference performed in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with a large external store.
Date: February 13, 1956
Creator: Carlson, Harry W. & Geier, Douglas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Reduction of wave drag of wing-body combinations at supersonic speeds through body distortions

Description: Report presenting some methods providing sizable reductions in drag for aspect ratios of current interest. The drag savings are maintained over a wide Mach number range, particularly for low-aspect-ratio wings. A significant part of the drag reduction is found to be due to the nonaxisymmetric distortion.
Date: April 13, 1956
Creator: Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of a symmetrical, circular, internal, compression inlet

Description: From Summary: "A preliminary experimental study of symmetrical, circular, internal compression inlets has shown that they attain pressure recovery equal to that measured by conical nose inlets at Mach numbers up to about 2.3. This pressure recovery was obtained with configurations having essentially zero pressure drag of the external surfaces."
Date: February 13, 1956
Creator: Mossman, Emmet A. & Pfyl, Frank A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tables and charts for thermodynamic calculations involving air and fuels containing boron, carbon, hydrogen, and oxygen

Description: Report presenting tables and charts of gas properties for use in thermodynamic calculations for engine cycles involving the combustion of air and any fuel or combustion of fuels containing carbon, boron, hydrogen, and oxygen. Dissociation and phase changes may be accounted for with the method presented, which does not require the presentation of separate data for each fuel-air ratio.
Date: July 13, 1956
Creator: Hall, Eldon W. & Weber, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal Decomposition of Ethylpentaborane in Gas Phase

Description: The thermal decomposition of ethylpentaborane at temperatures of 185 degrees to 244 degrees C is approximately a 1.5-order reaction. The products of the decomposition were hydrogen, methane, a nonvolatile boron hydride, and traces of decaborane. Measurements of the rate of decomposition of pentaborane showed that ethylpentaborane has a greater rate of decomposition than pentaborane.
Date: July 13, 1956
Creator: McDonald, Glen E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Investigation of the Effectiveness and Loading Characteristics of a Flap-Type Aileron With and Without Paddle Balances of an Unswept-Wing-Fuselage Model

Description: Report presenting an investigation of the effectiveness and loading characteristics of an aileron mounted on an unswept-wing-body configuration. A flap-type outboard aileron was tested with and without paddle balances at a range of Mach numbers and angles of attack. The aileron effectiveness, hinge-moment parameter, and effect of the paddle balances are presented.
Date: April 13, 1956
Creator: Hieser, Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic-Wind-Tunnel Investigation of the Effects of Lip Bluntness and Shape on the Drag and Pressure Recovery of a Normal-Shock Nose Inlet in a Body of Revolution

Description: Memorandum presenting an investigation made to determine the effects of lip bluntness, camber, and leading-edge roundness on the drag and pressure recovery of a normal-shock nose inlet in a body of revolution. Surface pressure distributions over the inlet lip and forebody were also obtained. Results regarding surface-pressure distributions, external drag, and pressure recovery are provided.
Date: July 13, 1956
Creator: Olstad, Walter B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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