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Analytical and experimental investigation of the effects of compressor interstage air bleed on performance characteristics of a 13-stage axial-flow compressor

Description: Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at l… more
Date: February 8, 1957
Creator: Lucas, James G.; Geye, Richard P. & Calvert, Howard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Chemical igniters for starting jet fuel - nitric acid rockets

Description: Report presenting experiments in a 200-pound-thrust jet fuel-nitric acid rocket with an axial-flow igniter employing the hypergolic alkyl thiosphosphite-nitric acid system. No combustion instability was observed in the igniter, but many of the main-stage runs exhibited low-frequency oscillations.
Date: October 8, 1957
Creator: Morrell, Gerald & Ladanyi, Dezso J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental study of the effects of scale on the absolute values of zero-lift drag of aircraft configurations at transonic speeds

Description: Report presenting an investigation at a range of Mach numbers from 0.7 to 1.4 to determine the effect of scale on the zero-lift drag of a fin-stabilized body of revolution and a fighter-type airplane configuration. Results obtained at low values of Reynolds number were compared with larger scale data obtained on geometrically similar models in free flight. Results regarding fin-stabilized body and airplane model are provided.
Date: February 8, 1957
Creator: Howell, Robert R. & Braslow, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory Investigation of the Effect of Wing Slots and Leading-Edge Slats on the Longitudinal Stability Characteristics of a 45 Degree Sweptback Wing-Fuselage Configuration

Description: Report presenting an exploratory investigation to determine the effects of wing slots on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage combination. Results regarding pitching-moment characteristics and lift and drag characteristics are provided.
Date: February 8, 1957
Creator: Critzos, Chris C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Experience of the Lateral Stability Characteristics at Low Lift of a 45 Degree Swept-Wing Rocket-Propelled Model Equipped With a Nonlinear Yaw-Rate Damper System at Mach Numbers From 0.76 to 1.73

Description: Report discussing a low-lift lateral stability investigation with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system at a range of Mach numbers. Results indicated that the system was nonlinear due to a large dead spot in the system. The primary effect of the system was to increase the damping of lateral oscillations.
Date: February 8, 1957
Creator: D'Aiutolo, Charles T.; Willoughby, William W. & Coltrane, Lucille C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Physical and Chemical Properties of HEF-2 (NACA Fuel 56Z4)

Description: Memorandum presenting a study of the chemical and physical properties of the high-energy fuel HEF-2. The properties measured included elemental analysis, heat of combustion, density, freezing point, self-ignition temperature, flash point, viscosity, molecular weight, vapor pressure, refractive index, and the water and oxygen stability.
Date: February 8, 1957
Creator: Spakowski, A. E.; O'Donnell, P. & Buddie, M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane

Description: Memorandum presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. Of specific concern were characteristic modes, period and damping, airplane response to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem. Results regarding stability-boundary plots, characteristic roots, roll-to-sideslip ratio, and time histories are provided.
Date: February 8, 1957
Creator: Moul, Martin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane

Description: Report presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. The characteristic modes, period and damping, airplane responses to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem are the primary focus.
Date: February 8, 1957
Creator: Moul, Martin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90

Description: Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90: TED No. NACA AD 3115

Description: From Summary: "A flight test was conducted with a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane configuration at transonic and supersonic speeds. The external drag coefficient varied from a value of 0.044 at a Mach number of 1.17 to 0.045 at a Mach number of 1.40 and then decreased to 0.041 at a Mach number of 1.90. The limited oscillatory data available indicate the existence of a coupled longitudinal-lateral motion in the Mach number range from 0.20 to 1.17."
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Structural Design and Engine Evaluation of an Air-Cooled Turbine Blade Composed of Corrugation and a Semistrut for Operation at a Tip Speed of 1200 Feet Per Second

Description: Report presenting an investigation of an air-cooled turbine rotor blade consisting of an internal part-span structural strut, corrugated cooling surfaces, and a thin outer shell. The effects on stresses and blade lift of varying strut length, shell thickness, and corrugation dimensions are provided. Testing occurred with the X-40 strut - A-286 shell combination and the S-816 strut - L-605 combination.
Date: October 8, 1957
Creator: Kemp, Richard H.; Meyer, André J., Jr. & Morgan, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Description: Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.
Date: October 8, 1957
Creator: Lucas, D. & Lipschitz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Description: "A series of experiments involving the reaction of water with decaborane and HEF-3, a borane fuel consisting mainly of ethyldecaborane, was performed. The results show that the presence of one alkyl group on the decaborane nucleus inhibits the hydrolysis reaction significantly and that the hydrolysis rate can be increased by using an acidic hydrolysis mixture. Two diiododecaborane isomers were prepared for use as intermediates in proposed dimethyldecaborane syntheses, and their melting points, … more
Date: October 8, 1957
Creator: Lucas, D. & Lipschitz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01

Description: "An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for t… more
Date: November 8, 1957
Creator: Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A theoretical and experimental study of boric oxide deposition on a surface immersed in an exhaust gas stream from a jet-engine combustor, including a method of calculating deposition rates on surfaces

Description: Report presenting the deposition rate of boric oxide from a stream containing submicron particles, which was found experimentally to fit a molecular diffusion equation. Results regarding boundary-layer studies, deposition studies, deposition tests, and turbojet engine performance are provided.
Date: October 8, 1957
Creator: Setze, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Republic F-105 Inlet with Various Modifications at Mach Numbers 1.41, 1.81, and 2.01

Description: "A 1/13-scale Republic F-105 wing-root inlet configuration in which inlet components were varied was tested in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1,41, 1.81, and 2,01 corresponding to Reynolds numbers per foot of 4,19 X 10(exp 6) , 3.74 X 10(exp 6) , and 3.46 x 10(exp 6) respectively. Angles of attack ranged from -4 deg to 15 deg and a few configurations were tested in a sideslip range from -8 deg to 4 deg. Inlet performance and engine-face flow distortions a… more
Date: January 8, 1957
Creator: Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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