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Theoretical Performance of Liquid Hydrogen and Liquid Fluorine as a Rocket Propellant

Description: Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal con… more
Date: February 6, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Lark Pilotless-Aircraft Configuration

Description: Report presenting flight tests to determine the longitudinal stability and control characteristics of models of the Lark pilotless aircraft. Testing included the standard configuration with the horizontal wing flaps deflected 0 degrees, 15 degrees, and 60 degrees, and a test with the tail surfaces in line with the wings with the wing flaps not deflected. Results regarding time-history records, drag, longitudinal stability, and control effectiveness are provided.
Date: February 6, 1948
Creator: Stone, David G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Temperature survey of the wake of two closely located parallel jets

Description: Report presenting a temperature survey made in the wake of two closely located parallel jets emerging into the atmosphere from two types of twin convergent nozzles. Results regarding the twin unshrouded nozzles and twin nozzles with twin geometry-simulated shrouds are provided.
Date: February 6, 1950
Creator: Sloop, John L. & Morrell, Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations

Description: Report discussing an investigation of the longitudinal trim and drag characteristics of two airplane configurations through the transonic speed range. One configuration had a thin straight wing and tail and one had a thicker 35 degree sweptback wing and a 46 degree sweptback tail on the same fuselage-fin arrangement. Information about the control effectiveness and stability and application to a full-scale airplane is also provided.
Date: February 6, 1950
Creator: Parks, James H. & Mitchell, Jesse L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of ref… more
Date: February 6, 1951
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal stability and dynamic characteristics at high angles of attack and at low Reynolds numbers of a model of the X-3 supersonic research airplane

Description: Report presenting an investigation in the 20-foot free-spinning tunnel to determine the motions and trim conditions from 0 to 90 degrees angle of attack for the X-3 airplane, which is a supersonic airplane with an extremely long nose and s mall wing. Testing was conducted on several scales of models and component parts. Results from dynamic and static tests are provided.
Date: February 6, 1951
Creator: Burk, Sanger M., Jr. & Hultz, Burton E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance and operational characteristics of a python turbine-propeller engine at simulated altitude conditions

Description: "The performance and operational characteristics of a Python turbine-propeller engine were investigated at simulated altitude conditions in the NACA Lewis altitude wind tunnel. In the performance phase, data were obtained over a range of engine speeds and exhaust nozzle areas at altitudes from 10,000 to 40,000 feet at a single cowl-inlet ram pressure ratio; independent control of engine speed and fuel flow was used to obtain a range of powers at each engine speed. Engine performance data obtain… more
Date: February 6, 1952
Creator: Meyer, Carl L. & Johnson, LaVern A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine 3: combustion and operational performance of three flame holders with a center pilot burner

Description: Report presenting a direct-connect altitude test chamber investigation of the combustion performance of a 28-inch-diameter ramjet engine with a can-type center pilot burner. Combustion-chamber configurations with three different flame holders were investigated at a simulated flight Mach number of 2.0 and several different altitudes.
Date: February 6, 1951
Creator: Shillito, Thomas B.; Younger, George G. & Henzel, James G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant

Description: Theoretical values of performance parameters for liquid hydrogen and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ration of nozzle-exit area to throat area, spe… more
Date: February 6, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wind-Tunnel Investigation of an Unswept-Wing-Body Combination at Angles of Attack Up to 24 Degrees

Description: Report presenting testing of a wing with 0 degree sweepback of the 0.25-chord line in combination with a body of revolution at Mach numbers from 0.60 to 1.11 for angles of attack up to 24 degrees. Results regarding lift characteristics, pitching moment, drag characteristics, and lift-drag ratio are provided.
Date: February 6, 1953
Creator: Estabrooks, Bruce B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378

Description: From Summary: "Additional tests of a 1/7-size model of the Grumman XJR2F-1 amphibian were made in Langley tank no. 1 to compare the behavior during take-off of the model equipped with split- and slotted-type flaps. The slotted flag had a large effect on locating the forward center-of-gravity limits for stable take-offs. Stable take-offs within the normal operating range of positions of the center of gravity could be made with the split flaps deflected 45 degrees or with the slotted flaps deflec… more
Date: February 6, 1947
Creator: Land, Norman S. & Zeck, Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the NACA 4-(4)(06)-057-45a and NACA 4-(4)(06)-57-45b Two-Blade Swept Propellers at Forward Mach Numbers to 0.925

Description: Report presenting an investigation of the NACA 4-(4)(06)-057-45A and NACA 4-(4)(06)-057-45B two-blade swept propellers in the high-speed tunnel at blade angles of 25 degrees, 55 degrees, 60 degrees, 65 degrees, and 70 degrees. The swept propellers were compared with straight propellers and were found to be 10 percent more efficient at a forward Mach number of 0.85 for the design blade angle of 60 degrees. Results regarding the effect of forward Mach number, blade sweep, advance ratio, and const… more
Date: February 6, 1950
Creator: Delano, James B. & Harrison, Daniel E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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