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Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes

Description: Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers t… more
Date: May 26, 1958
Creator: Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Item Type: Refine your search to only Report
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Induction system characteristics and engine surge occurrence for two fighter-type airplanes

Description: Report presenting an investigation to measure and to compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbo-jet engines, but with dissimilar inlets. Results regarding compressor-face total-pressure surveys and surges encountered are provided.
Date: May 26, 1958
Creator: Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Item Type: Refine your search to only Report
open access

Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 employing high-velocity blowing over the leading- and trailing-edge flaps

Description: Report presenting an investigation to determine the longitudinal characteristics of an airplane model with a thin, highly swept and tapered wing of low aspect ratio equipped with plain leading-edge flaps in conjunction with blowing-type boundary-layer control applied to flap radius. Several leading-edge configurations and boundary-layer control system variables were also investigated.
Date: May 26, 1958
Creator: Hickey, David H. & Aoyagi, Kiyoshi
Item Type: Refine your search to only Report
open access

Some Effects of Roughness on Stagnation-Point Heat Transfer at a Mach Number of 2, a Stagnation Temperature of 3,530 F, and a Reynolds Number of 2.5 X 10(Exp 6) Per Foot

Description: Report presenting an investigation to determine some effects of surface roughness on heat transfer at the stagnation point. Testing occurred in the ceramic-heated jet laboratory model at a Mach number of 2, a stagnation temperature of 3,530 degrees Fahrenheit, and a stream Reynolds number of 2.5 x 10(exp 6) per foot. Results regarding the variation of stagnation-point heat-transfer coefficient with surface roughness, heat transfer at the stagnation point of a hemisphere, and heat-transfer coeff… more
Date: May 26, 1958
Creator: Strass, H. Kurt & Tyner, Thomas W.
Item Type: Refine your search to only Report
open access

Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model

Description: Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.
Date: May 26, 1958
Creator: Matthews, Clarence W.
Item Type: Refine your search to only Report
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Theoretical analysis of the interference effects of several supersonic-tunnel walls capable of absorbing the shock caused by the nose of a model

Description: Report presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.
Date: May 26, 1958
Creator: Matthews, Clarence W.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at a Mach Number of 2.01 of Forebody Strakes for Improving Directional Stability of Supersonic Aircraft

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of forebody strakes on the aerodynamic characteristics in sideslip of a delta-wing airplane model at Mach number of 2.01. The presence of the strakes increased the directional-stability level for both vertical-tail arrangements. Results of pressure tunnels for a forebody show that the presence of the strakes provides a stabilizing influence on the forebody which is consistent with the … more
Date: May 26, 1958
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
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Light Diffusion Through High-Speed Turbulent Boundary Layers

Description: Memorandum presenting the optical transmission characteristics of turbulent boundary layers in air on a flat plate with negligible heat transfer measured photometrically for ranges of Mach number from 0.4 to 2.5. The results indicated that the scattering from a collimated beam of white light which penetrates a turbulent boundary layer depends mainly on the integral across the layer of the difference between the free-stream density and the local boundary-layer density.
Date: May 26, 1956
Creator: Stine, Howard A. & Winovich, Warren
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of various configurations of a model of a 45 degree swept-wing airplane at a Mach number of 2.01

Description: An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach nmber of 2.01 to determine the aerodynamic characteristics of several configurations of a model of a 45 deg swept-wing airplane. The basic configuratin had a wing with 45 deg sweepback at the quarter-chord line, aspect ration 3.2, taper ration 0.468, NACA 65A005.5 sections just outboard of the inlet and NACA 65A003.7 sections at the tip. The wing was mounted slightly above the body center line a… more
Date: May 26, 1955
Creator: Spearman, M. Leroy; Driver, Cornelius & Robinson, Ross B.
Item Type: Refine your search to only Report
open access

Experimental Investigation at High Subsonic Speeds of the Rolling Stability Derivatives of a Complete Model with an Aspect-Ratio-2.52 Wing Having an Unswept 72-Percent-Chord Line and a High Horizontal tail

Description: Memorandum presenting rolling stability derivatives for a complete model with a low-aspect-ratio wing and tail surfaces for a Mach number range of 0.70 to 0.94 and for an angle-of-attack range from 0 to 13 degrees for the lower Mach numbers. The model test results indicated regions of neutral or unstable damping in roll at Mach numbers of 0.85 and 0.90 in the higher angle-of-attack range for the basic model. Results regarding damping in roll, yawing moment and lateral force due to rolling, and … more
Date: May 26, 1955
Creator: Sleeman, William C., Jr. & Wiggins, James W.
Item Type: Refine your search to only Report
open access

Flight Determination of the Longitudinal Stability and Control Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Description: Memorandum presenting the Bell X-5 research airplane tested at 58.7 degrees sweepback during the program to determine the characteristics of a variable-sweep fighter airplane at transonic speeds. This paper includes the stability and control characteristics in the stable lift range up to Mach numbers near 1.0 at an altitude of 40,000 feet and to slightly lower Mach numbers at altitudes of 25,000 feet and 15,000 feet. Results regarding general comments, static stability and control characteristi… more
Date: May 26, 1955
Creator: Finch, Thomas W.
Item Type: Refine your search to only Report
open access

Lateral stability and control characteristics of the Convair XF-92A delta-wing airplane as measured in flight

Description: Report presenting the lateral stability and control characteristics were investigated on the Convair XF-92A delta-wing airplane during the flights of the NACA research program. The investigation included sideslips, aileron rolls, and rudder pulses at a range of altitudes and indicated speeds. The lateral handling characteristics appear satisfactory when viewed in terms of gradually increasing sideslips, lateral control effectiveness, and period, and damping.
Date: May 26, 1955
Creator: Sisk, Thomas R. & Muhleman, Duane O.
Item Type: Refine your search to only Report
open access

Static longitudinal and lateral stability and control characteristics of a model of a 35 degree swept-wing airplane at a Mach number of 1.41

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a model of a 35 degree swept-wing airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on aerodynamic characteristics were also investigated.
Date: May 26, 1955
Creator: Palazzo, Edward B. & Spearman, M. Leroy
Item Type: Refine your search to only Report
open access

The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced… more
Date: May 26, 1954
Creator: Sadoff, Melvin; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
open access

A Wind-Tunnel Investigation at High Subsonic Speeds of the Lateral Control Characteristics of Various Plain Spoiler Configurations on a 3-Percent-Thick 60 Degree Delta Wing

Description: Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of attack of -2 degrees to about 24 degrees to determine the lateral control characteristics of spoilers with various wing chord-wise and spanwise locations and spoiler spans and deflections on thin 60 degree delta wing of NACA 65a003 airfoil section parallel to free stream.
Date: May 26, 1954
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
open access

Fabrication and Properties of Hot-Pressed Molybdenum Disilicide

Description: Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.
Date: May 26, 1950
Creator: Long, Roger A.
Item Type: Refine your search to only Report
open access

Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89

Description: "Abrupt, rudder-fixed aileron rolls have been made with the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers between 0.6 and 0.89. Rolls were made at aileron deflections between one-eighth and one-half the maximum available deflection. The results obtained indicate that the aileron effectiveness is independent of Mach number and deflection within the range investigated" (p. 1).
Date: May 26, 1950
Creator: Thompson, Jim Rogers; Roden, William S. & Eggleston, John M.
Item Type: Refine your search to only Report
open access

Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models

Description: Report presenting data gathered on a lateral-trim change or wing dropping that involves a rapid change of lateral trim with Mach number, which has occurred on several rocket-powered models used in roll investigations at transonic speeds. The data in this report demonstrates that straight wings with airfoil sections 9 percent thick or greater are susceptible to wing dropping between Mach numbers of 0.9 and 1.0. Results for straight, sweptback, and delta wings are provided.
Date: May 26, 1950
Creator: Stone, David G.
Item Type: Refine your search to only Report
open access

Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 2: nacelle with long straight air inlet

Description: Report presenting aerodynamic and icing investigations conducted in the icing research tunnel on a model of a turbojet-engine nacelle with a long straight air inlet in order to provide basic design criteria for hot-gas blowback systems. The most uniform temperature distribution was obtained with a bleedback of 4.4 percent at a gas temperature of 1000 degrees Fahrenheit and resulted in an average dry-air-temperature rise of 46 degrees Fahrenheit.
Date: May 26, 1949
Creator: Callaghan, Edmund E. & Ruggeri, Robert S.
Item Type: Refine your search to only Report
open access

Investigation of several clamshell variable-area exhaust nozzles for turbojet engines

Description: Report presenting the results of several investigations of the performance of different types of clamshell variable-area exhaust nozzle far turbojet engines to determine the efficiency of that type of exhaust nozzle as compared with conventional fixed-area conical exhaust nozzles. The investigations were conducted at zero-ram sea level conditions on three different full-scale turbojet engines and using five different nozzles.
Date: May 26, 1949
Creator: Lundin, Bruce T.
Item Type: Refine your search to only Report
open access

Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen

Description: From Summary: "Theoretical performance data including nozzle-exit temperature, specific impulse, volume specific impulse and composition, temperature, and mean molecular weight of reaction products based on frozen equilibrium and isentropic expansion are presented for 13 propellant combinations at reaction pressure of 300 pounds per square inch absolute and expansion ratio of 20.4. On basis of maximum specific impulse alone, five fuels had the following order for any given oxidant: liquid hydro… more
Date: May 26, 1948
Creator: Miller, Riley O. & Ordin, Paul M.
Item Type: Refine your search to only Report
open access

Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Pitch of an NACA 64-Series 40 Degree Swept-Back Wing

Description: Report presenting wind-tunnel testing to determine the low-speed lift, drag, and pitching-moment characteristics of a 40 degree sweptback wing with high-lift and stall-control flaps and a fuselage with a fineness ratio of 10.2 to 1. Low, medium, and high-wing-fuselage combinations were tested at high Reynolds numbers. Results regarding the high-lift and stall-control flaps and wing-fuselage combinations are provided.
Date: May 26, 1947
Creator: Conner, D. William & Neely, Robert H.
Item Type: Refine your search to only Report
open access

Further investigation of NACA 4-(5)(08)-03 two-blade propeller at high forward speeds

Description: Report presenting tests of an NACA 4-(5)(08)-03 two-blade propeller in the 8-foot high-speed tunnel for blade angles of 45 and 60 degrees extending the Mach number range from that of previous tests of the propeller up to Mach number 0.913. When the forward speed was increased from a low value to a forward Mach number of 0.90, the loss in peak efficiency was found to be not more than 47 percent.
Date: May 26, 1947
Creator: Carmel, Melvin M. & Robinson, Harold L.
Item Type: Refine your search to only Report
open access

Spin and Recovery Characteristics of the Curtiss-Wright XP-87 Airplane

Description: "The spin and recovery characteristics of the Curtiss-Wright XP-87 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape, are presented in this report. The characteristics were estimated rather than determined by model tests because the XP-87 dimensional and mass characteristics were considered to be noncritical and because data were available from model tests of se… more
Date: May 26, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
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