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in subjects: "aircraft design, testing and performance"

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Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59

Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.

Date: May 20, 1957

Creator: Lee, John B.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Range Performance of Bombers Powered by Turbine-Propeller Power Plants

"Calculations have been made to find ranges attainable by bombers of gross weights from l40,000 to 300,000 pounds powered by turbine-propeller power plants. Only conventional configurations were considered and emphasis was placed upon using data for structural and aerodynamic characteristics which are typical of modern military airplanes. An effort was made to limit the various parameters invoked in the airplane configuration to practical values" (p. 1).

Date: June 20, 1950

Creator: Cline, Charles W.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Flight Measurements of the Directional Stability and Control of a P-51D Airplane with a Horn-Balanced Rudder as Compared with Previously Tested Vertical-Tail Configurations

"At the request of the Air Materiel Command, Army Air Forces, flight tests were conducted on a P-5lD-20-NA (AAF No. 44-63826) airplane equipped with a horn-balanced rudder. This rudder was fitted with an unbalancing tab as was the original product fan rudder. Tests were made both with the unbalancing tab in operation and with the unbalancing tab locked. The modification to the original vertical tail consisted of removing the cap from the top of the fin and adding 1.91 square feet of area to the… more

Date: December 3, 1946

Creator: Mungall, Robert G.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Wind-Tunnel Tests to Determine Aileron Characteristics of the McDonnell XFD-1 Airplane, TED No. NACA 23102

"Tests were performed on a partial span of the wing of a McDonnell XFD-1 airplane to determine a combination of sealed internal balance and spring-tab stiffness for the aileron that would give satisfactory stick-force characteristics for the airplane. Two sealed internal balances were tested in combination with spring tabs of various stiffnesses. One of the combinations was tested at several speeds to determine the variation of stick force with speed" (p. 1).

Date: September 26, 1946

Creator: Yates, Campbell C. & Schneiter, Leslie E.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Results of Flight Test of an Automatically Stabilized Model C (Swept Back) Four-Wing Tiamat

"The results of the first flight test of a swept-back four-wing version of Tiamat (MX-570 model C) which was launched at the NACA Pilotless Aircraft Research Station at W4110PB Island, Va. are presented. In general, the flight behavior was close to that predicted by calculations based an stability theory and oscillating table tests of the autopilot. The flight test thus indicates that the techniques employed to predict automatic stability are valid and practical from an operational viewpoint" (… more

Date: June 11, 1947

Creator: Seacord, Charles L., Jr. & Teitelbaum, J. M.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

"A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The … more

Date: April 11, 1947

Creator: Adams, Richard E. & Silsby, Norman S.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Flight Measurements of Average Skin-Friction Coefficients on a Parabolic Body of Revolution (NACA RM-10) at Mach Numbers from 1.0 to 3.7

"Measurement of average skin-friction coefficients have been made on six rocket-powered free-flight models by using the boundary-layer rake technique. The model configuration was the NACA RM-10, a 12.2-fineness-ratio parabolic body of revolution with a flat base. Measurements were made over a Mach number range from 1 to 3.7, a Reynolds number range 40 x 10(exp 6) to 170 x 10(exp 6) based on length to the measurement station, and with aerodynamic heating conditions varying from strong skin heati… more

Date: August 25, 1954

Creator: Loposer, J. Dan & Rumsey, Charles B.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane

"An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model" (p. 1).

Date: February 11, 1953

Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

High Speed Stability and Control Characteristics of a 0.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No. NACA DE 318)

"High-speed wind-tunnel tests were conducted of two versions of a 0.17-scale model of the McDonnell XF2H-1 airplane to ascertain the high-speed stability and control characteristics and to study means for raising the high-speed buffet limit of the airplane, The results for the revised model, employing a thinner wing and tail than the original model, revealed a mild diving tendency from 0.75 to 0.80 Mach number, followed by a marked climbing tendency from 0.80 to 0.875 Mach number. The high-spee… more

Date: March 31, 1949

Creator: Axelson, John A. & Emerson, Horace F.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Vibration of a Wing of Finite Span in a Supersonic Flow

An investigate ion was made of the disturbed motion of a gas for the harmonic vibrations of a thin slightly cambered wing of finite span moving forward with supersonic velocity. This problem was considered by E. A. Krasilshchikova who applied the method of Fourier series and obtained a solution of the space problem for the condition that the Mach cones drawn through the leading edge of the wing intersect the wing or are tangent to it. In this paper, a different method of solution is given, whic… more

Date: April 1950

Creator: Haskind, M. D. & Falkovich, S. V.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

A Low-Speed Investigation of a Fuselage-Side Air Inlet for use at Transonic Flight Speeds

"A low-speed investigation in the Langley propeller-research tunnel of annular air inlets designed to avoid compression shocks and attendant boundary-layer separation on the fuselage ahead of the inlets at transonic flight speeds by maintaining substream flow velocities on the fuselage nose was reported in NACA RM No. L6J04. In the present investigation, one of the original annular inlets was converted by the installation of a canopy and a nose-wheel fairing into a twin side inlet in order to s… more

Date: April 9, 1947

Creator: Nichols, Mark R. & Goral, Edwin B.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

"Two theoretical procedures are developed for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One procedure is applicable at Mach numbers less than approximately 3. This approach yields, without iteration, a nozzle for which the calculated exit flow is uniform at two Mach numbers and, with proper design, is nearly uniform at Mach numbers between, slightly above, and slightly below these two" (p. 1).

Date: April 11, 1951

Creator: Syvertson, Clarence A. & Savin, Raymond C.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Component Performance Investigation of J71 Experimental Turbine 3 - Effect of Third-Stage Shrouding on Over-All Performance

"A negligible effect on turbine efficiency and only a small decrease in turbine weight flow were observed when the J71 experimental turbine with 97-percent-design stator areas was modified to include shrouding of the third-stage rotor" (p. 1).

Date: April 17, 1956

Creator: Petrash, Donald A.; Schum, Harold J. & Davison, Elmer H.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Interim Report on Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-1N Airplane, TED No. NACA AD 3100

"An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/23-scale model of the McDonnell F3H-1N airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Spin-recovery parachute tests were also performed. The results indicated that erect spins obtained on the airplane for the take-off or combat loadings should be satisfactorily terminated if full rudder rev… more

Date: December 31, 1954

Creator: Lee, Henry A. & Wilkes, L. Faye

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Component Performance Investigation of J71 Experimental Turbine 2 - Internal-Flow Conditions with 97-Percent-Design Stator Areas

"An experimental investigation of the internal-flow conditions of a J71 experimental turbine equipped with 97-percent-design stator areas was conducted at equivalent design speed and near equivalent design work. The results of the investigation indicate that the stage work distribution closely approximates design, the actual distribution being 44.1, 33.4, and 22.5 percent for the first, second, and third stages, respectively. The first-, second-, and third-stage efficiencies were 0.894, 0.858, … more

Date: April 11, 1956

Creator: Rebeske, John J., Jr. & Petrash, Donald A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Calculation of Centrally Loaded Thin-Walled Columns Above the Buckling Limit

"When thin-walled columns formed from flanged sheet, such as used in airplane construction, are subjected to axial load, their behavior at failure varies according to the slenderness ratio. On long columns the axis deflects laterally while the cross section form is maintained; buckling results. The respective breaking load in the elastic range is computed by Euler's formula and for the plastic range by the Engesser- Karman formula. Its magnitude is essentially dependent upon the length" (p. 1).

Date: April 1945

Creator: Reinitzhuber, F.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Pressure-Distribution Measurements on the Tail Surfaces of a Rotating Model of the Design BFW - M31

In order to obtain insight into the flow conditions on tail surfaces on airplanes during spins, pressure-distribution measurements were performed on a rotating model of the design BFW-M31. For the time being, the tests were made for only one angle of attack (alpha = 60 degrees) and various angles of yaw and rudder angles. The results of these measurements are given; the construction of the model, and the test arrangement used are described. Measurements to be performed later and alterations pla… more

Date: December 1949

Creator: Kohler, M. & Mautz, W.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Strength Investigations in Aircraft Construction Under Repeated Application of the Load

"In the calculation of the dimensions of modern machines and building constructions, account is taken of the frequency of the occurrence of the anticipated loads. It is generally assumed that these loads will be repeated an infinite number, or at any rate some millions, of times during the total working life of the construction. When calculating the dimensions of the structural parts of aircraft, on the contrary, a consideration only of those frequencies in the appearance of the loads which act… more

Date: August 1946

Creator: Gassner, E.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Transonic-Wind-Tunnel Tests of the Aerodynamic Characteristics of a 0.15-Scale Model of the North American Aviation 255-Inch Fin-Stabilized External Store, Coord No. AF-AM-4

"An investigation has been made in the Langley 8-foot transonic tunnels on the aerodynamic characteristics of a 0.15-scale model of the North American Aviation 255-inch fin-stabilized external store over a maximum Mach number range of 0.60 to 1.2 and on the effects of mounting lugs, of fin orientation, of fin aspect ratio, and of fixed-transition. The Reynolds number (based on a body length of 37.50 inches) varied from 9.8 x 10(exp 6) to 13.1 x 10(exp 6). The results indicate that the static ma… more

Date: February 9, 1958

Creator: Fischetti, Thomas L.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 3 - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages

The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.

Date: February 15, 1952

Creator: Medeiros, Arthur A. & Hatch, James E.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Effects of Horizontal-Tail Location and Wing Modifications on the High-Speed Stability and Control Characteristics of a 01.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No, NACA DE336)

"An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved… more

Date: October 14, 1949

Creator: Emerson, Horace F. & Axelson, John A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance

"Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers… more

Date: April 25, 1947

Creator: Dietz, Robert O. & Kuenzig, John K.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Effect of an Operating Propeller on the Aerodynamic Characteristics of a 1/10-Scale Model of the Lockheed XFV-1 Airplane at High Subsonic Speeds (TED No. NACA DE-377)

"An investigation was conducted in the Ames 12-foot pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a 1/19-scale model of the Lockheed XFV-1 airplane. Several full-scale power conditions were simulated at Mach numbers from 0.50 to 0.92; the.Reynolds number was constant at 1.7 million. Lift, longitudinal force, pitch, roll, and yaw characteristics, determined with and without power, are presented for the complete model and for various … more

Date: May 6, 1952

Creator: Sutton, Fred B. & Buell, Donald A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Full-Scale Hydrodynamic Evaluation of a Modified Navy J4F-2 Amphibian with a 0.425-Scale XP5M-1 Hull Bottom: TED No. NACA DE325

"An investigation was made to evaluate the hydrodynamic qualities of a 0.425-scale model of the Navy XP5M-1 hull, which was installed on a modified Navy J4F-2 amphibian. Longitudinal and directional stability during take-off and landing, low-speed maneuverability, spray characteristics, and take-off performance were investigated. The behavior of the airplane in moderately rough water was also observed. The opinions of three pilots have been correlated with the data" (p. 1).

Date: December 7, 1949

Creator: Land, Norman S.; Elliott, John M. & Christopher, Kenneth W.

Item Type: Report

Partner: UNT Libraries Government Documents Department