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Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight

Description: Report presenting the results of an investigation of the dynamic stability and controllability of a proposed supersonic-cruise, vertical-take-off-and-landing airplane configuration with a tilting wing and engines. The configuration tested was found to have satisfactory take-off, landing, and hovering characteristics. Information about transition flight, including stability and control characteristics, is provided.
Date: August 26, 1958
Creator: Kirby, Robert H. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
open access

Operational problems of manned orbital vehicles

Description: Report presenting an exploration of some of the problems of manned orbital vehicles, which introduce many problems in the fields of escape, piloting, orbit selection, flight termination, and range requirements. The effects of some of these problems, including some effects of configuration, are discussed.
Date: July 21, 1958
Creator: Drake, Hubert M.; Bellman, Donald R. & Walker, Joseph A.
Item Type: Refine your search to only Report
open access

Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet

Description: Report presenting the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in order to determine the performance penalties associated with spike-tip and cowl-lip blunting. The data can be used as a design guide for blunt inlet components applicable to cooling techniques. Results regarding the effect of tip rounding, drag coefficients, flow distortion, lip blunting, and Schileren photographs are provided.
Date: September 23, 1958
Creator: Cubbison, R. W. & Samanich, N. E.
Item Type: Refine your search to only Report
open access

Some experiments at high supersonic speeds on the aerodynamic and boundary-layer transition characteristics of high-drag bodies of revolution

Description: Report presenting measurements made at Mach numbers of 4.0 and 8.3 of the drag, static stability, damping in pitch, and boundary-layer transition characteristics of several high-drag bodies of revolution that might be used for high-speed entry into the earth's atmosphere. The static stability was found to be high with centers of pressure as far aft as 91 percent of the length from the nose. Results regarding the force and moment data, boundary-layer transition, a comparison of roughness height … more
Date: January 14, 1957
Creator: Seiff, Alvin; Sommer, Simon C. & Canning, Thomas N.
Item Type: Refine your search to only Report
open access

Investigation at high subsonic speeds of the effects of various underwing external-store arrangements on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II Research Airplane

Description: Report presenting an investigation at high subsonic speeds of various arrangements of underwing external stores on a model of the Douglas D-558-II research airplane. Three sizes of a short-cylinder shape and two sizes of a long-cylinder shape were investigated with three thicknesses of pylon support on one store configuration. Results regarding drag characteristics and lift and pitch characteristics are provided.
Date: July 18, 1955
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Effects of Wing-Mounted Tank-Type Stores on the Low Lift Buffeting and Drag of a Swept-Wing Airplane Configuration Between Mach Numbers of 0.8 and 1.3

Description: Memorandum presenting tests of two rocket-powered models of a 45 degree swept-wing airplane configuration with different underwing fuel-tank installations located at approximately half the wing semispan. Results of the tests were compared with previously reported data from a similar configuration with no tanks and with isolated tank data. These results include trim, buffeting, drag, and static longitudinal stability are provided.
Date: October 6, 1955
Creator: Mason, Homer P.
Item Type: Refine your search to only Report
open access

Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: "The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements" (p. 1).
Date: December 17, 1951
Creator: Friedman, Morris D.
Item Type: Refine your search to only Report
open access

The Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the Ames supersonic free-flight wind tunnel, which is a new piece of equipment for aerodynamic research at high supersonic Mach numbers. It has a wide Mach number range extending from low supersonic speeds to Mach numbers in excess of 10. The air stream in the tunnel is imperfect, mainly due to a symmetrical pair of oblique shock waves which reflect down the test section.
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Item Type: Refine your search to only Report
open access

Effects of variations in combustion-chamber configuration on ignition delay in a 50-pound-thrust rocket

Description: Ignition delays of a diallylaniline-triethylamine mixture and of triethyl trithioposphite with red fuming nitric acid were measured as a function of combustor dimensions, initial propellant temperature, and initial ambient pressure. Ignition delay increased with exhaust-nozzle diameter. Ignition delay also increased as propellant temperature decreased, but did not vary with initial ambient pressure except with the largest nozzle diameter. A correlation among ignition delay, combustor dimensions… more
Date: October 5, 1956
Creator: Ladanyi, Dezso J.
Item Type: Refine your search to only Report
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
open access

Heat Transfer and Pressure Distribution at a Mach Number of 6.8 on Bodies With Conical Flares and Extensive Flow Separation

Description: Report presenting an investigation of heat transfer and pressure distribution on flared bodies under laminar, transitional, and turbulent boundary-layer conditions at Mach number 6.8. Information about flow characteristics, flare drag, and the relationship between flare drag and flare heating is provided.
Date: July 20, 1956
Creator: Becker, John V. & Korycinski, Peter F.
Item Type: Refine your search to only Report
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
open access

A free-flight investigation of the effects of a sonic jet on the total-drag and base-pressure coefficients of a boattail body of revolution from Mach number 0.83 to 1.70

Description: Report presenting flight testing of two 7.5 degree boattail bodies of revolution with constant base annuli and varying jet static-pressure ratios and simulated turbojet exhaust rocket motors in order to determine the jet interference effects on total-drag and base-pressure coefficients over a range of Mach numbers. Results regarding the total drag and base-pressure and base-drag coefficients are provided.
Date: March 8, 1956
Creator: Falanga, Ralph A.
Item Type: Refine your search to only Report
open access

Pressure distributions and aerodynamic characteristics of several spoiler-type controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results of the tests indicated that the incremental pressure distributions due to spoiler were in agreement with previous results as long as the spoiler was not too close to a break in the wing surface or the wing tip.
Date: July 26, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
open access

The Effects of the Addition of Small Fuselage-Mounted Fins on the Static Directional Stability Characteristics of a Model of a 45 Degree Swept-Wing Airplane at Angles of Attack up to 15.3 degrees at a Mach Number of 2.01

Description: Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 to determine the effects of the addition of four small fuselage-mounted cruciform fins on the directional characteristics of a 45 deg swept-wing airplane model at angles of attack up to 15.3 deg and angles of sideslip up to about 16 deg. The results showed that the addition of the four cruciform fins to the model increased the directional stability substantially at the highest angle of attack an… more
Date: October 12, 1956
Creator: Spearman, M. Leroy; Robinson, Ross B. & Driver, Cornelius
Item Type: Refine your search to only Report
open access

Comparison of the Minimum Drag of Two Versions of a Modified Delta-Wing Fighter as Obtained From Flight Tests of Rocket-Boosted Models and Equivalent Bodies Between Mach Numbers of 0.80 and 1.64

Description: Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
Date: September 24, 1956
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Item Type: Refine your search to only Report
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
open access

Experimental Investigation of Diffuser Pressure-Ratio Control With Shock-Positioning Limit on 28-Inch Ram-Jet Engine

Description: The performance of a control system designed for variable thrust applications was determined in an altitude free-jet facility at various Mach numbers, altitudes and angles of attack for a wide range of engine operation. The results are presented as transient response characteristics for step disturbances in fuel flow and stability characteristics as a function of control constants and engine operating conditions. The results indicate that the control is capable of successful operation over the … more
Date: January 15, 1957
Creator: Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
Item Type: Refine your search to only Report
open access

Static-thrust characteristics of the NACA 8.75-(5)(05)-037 dual-rotation propeller

Description: Report presenting the static-thrust characteristics of the NACA 8.75-(5)(05)-037 dual-rotation propeller with six and eight blades as obtained on the static test stand in the course of an investigation set up primarily for studying blade vibratory stresses. Force data were obtained for a blade-angle range measured at the 0.75 radial station on the front propeller. Results regarding the effect of tip Mach number, effect of number of blades, and effect of blade angle are provided.
Date: July 10, 1956
Creator: Norton, Harry T., Jr.
Item Type: Refine your search to only Report
open access

Investigation of an Underslung Normal-Wedge Inlet at Free-Stream Mach Numbers From 1.50 to 1.99

Description: Two normal -wedge-inlet configurations (straight and sweptback splitter plates) were investigated in the Lewis 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.50 to 1.99. Negligible differences occurred in the performances of the two normal-wedge inlets. In comparison with a previously tested scoop inlet, the normal-wedge configuration showed superior thrust-minus-drag characteristics at Mach 1.99. However the scoop inlet was better at Mach numbers of 1.80 and 1.50.
Date: March 19, 1957
Creator: Vargo, Donald J. & Weinstein, Maynard I.
Item Type: Refine your search to only Report
open access

Free-Flight Aerodynamic-Heating Data to Mach Number 10.4 for a Modified Von Karman Nose Shape

Description: Report presenting aerodynamic-heating data obtained on a modified-fineness-ratio-5.0 Von Karman nose shape at free-stream Mach numbers up to 10.4 with a rocket-propelled model. Transient skin temperatures were measured on the nose, and a maximum temperature of 1,663 degrees R was measured after maximum Mach number was obtained.
Date: July 10, 1956
Creator: Bland, William M., Jr. & Collie, Katherine A.
Item Type: Refine your search to only Report
open access

Zero-Lift Drag of a Series of Bomb Shapes at Mach Numbers From 0.60 to 1.10

Description: Report presenting zero-lift drag data obtained on a series of six bomb shapes. Five configurations had the same body shape with different body-surface conditions and profile and plan form of fins, and the sixth had a different and longer body shape. Results regarding the effect of blunt trailing edge, blunt leading edge, fin thickness, and body surface are provided.
Date: July 26, 1956
Creator: Stoney, William E., Jr. & Royall, John F.
Item Type: Refine your search to only Report
open access

Some Effects of Wing Fences on the Lateral Stability Derivatives of a 60 Degree Delta Wing Oscillating Continuously in Yaw

Description: Report presenting an investigation at low speed to determine some of the effects of wing fences on the lateral stability derivatives of a flat-plate 60 degree delta-wing model oscillating continuously in yaw. Results regarding the variation with angle of attack, effect of frequency, effect of amplitude, number of fences, and some effects of fence geometric characteristics are provided.
Date: July 11, 1956
Creator: Riley, Donald R.
Item Type: Refine your search to only Report
open access

Lateral-Stability Flight Test of a 0.125-Scale Rocket-Propelled Model of the Mcdonnell F-101A Airplane at Mach Numbers from 1.0 to 1.9

Description: "A rocket-propelled model of the McDonnell F-101A airplane was tested in free flight for its lateral stability characteristics. The 0.125-scale model was equipped with six pulse rockets to produce the lateral disturbances. The center of gravity was located at 17.3 percent of the mean aerodynamic chord. The method of analysis was based on lateral-force and moment vector diagrams which trigonometrically solved for the resultants" (p. 1).
Date: April 17, 1956
Creator: Hollinger, James A. & Coltrane, Lucille C.
Item Type: Refine your search to only Report
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