You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1948
 Collection: National Advisory Committee for Aeronautics Collection
Accuracy of airspeed measurements and flight calibration procedures

Accuracy of airspeed measurements and flight calibration procedures

Date: 1948
Creator: Huston, Wilber B
Description: The sources of error that may enter into the measurement of airspeed by pitot-static methods are reviewed in detail together with methods of flight calibration of airspeed installations. Special attention is given to the problem of accurate measurements of airspeed under conditions of high speed and maneuverability required of military airplanes. (author).
Contributing Partner: UNT Libraries Government Documents Department
Additional abstracts pertaining to seaplanes

Additional abstracts pertaining to seaplanes

Date: March 9, 1948
Creator: Bidwell, J. M. & King, D. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds

Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds

Date: November 24, 1948
Creator: Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional results in a free-flight investigation of control effectiveness of full-span, 0.2-chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, aspect ratio, taper, and section thickne

Additional results in a free-flight investigation of control effectiveness of full-span, 0.2-chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, aspect ratio, taper, and section thickne

Date: April 23, 1948
Creator: Sandahl, Carl A & Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: October 1, 1948
Creator: Solomon, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Date: October 26, 1948
Creator: Johnson, Peter J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord

Date: November 19, 1948
Creator: Berggren, Robert E & Summers, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 II : maximum thickness at midchord

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 II : maximum thickness at midchord

Date: December 3, 1948
Creator: Walker, Harold J & Berggren, Robert E
Description: The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit the irregular variations with Mach number at high subsonic and low supersonic Mach numbers that are characteristic of unswept wings. The lift-curve slope increased steadily with Mach number below unity and declined slowly beyond the Mach number of 1.13. A substantial rise in the minimum drag coefficient occurred between Mach numbers of 0.95 and 1.20 with an associated reduction in the maximum lift-drag ratio. The aerodynamic center shifted rearward toward the centroid of area of the wing with increasing Mach number below 0.975; whereas above 1.09 it coincided with the centroid.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections

Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections

Date: June 1, 1948
Creator: Loftin, Laurence K , Jr & Cohen, Kenneth S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller

Date: September 2, 1948
Creator: Evans, Albert J & Salters, Leland B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Date: August 30, 1948
Creator: Allis, A E & Gray, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Date: November 10, 1948
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Aerodynamic characteristics of several NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Date: May 27, 1948
Creator: Loftin, Laurence K , Jr & Poteat, M Irene
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Date: October 28, 1948
Creator: Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

Date: April 23, 1948
Creator: Boddy, Lee E & Morrill, Charles P , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic properties of slender wing-body combinations at subsonic, transonic, and supersonic speeds

Aerodynamic properties of slender wing-body combinations at subsonic, transonic, and supersonic speeds

Date: July 1, 1948
Creator: Spreiter, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Date: October 11, 1948
Creator: Reynolds, Robert M & Smith, Donald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Date: September 1, 1948
Creator: Lindsey, W F; Stevenson, D B & Daley, Bernard N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Date: October 29, 1948
Creator: Davidson, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine I - Operational Characteristics and Altitude Limits

Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine I - Operational Characteristics and Altitude Limits

Date: July 6, 1948
Creator: unknown
Description: An altitude-test-chamber investigation was conducted to determine the operational characteristics and altitude blow-out limits of a Solar afterburner in a 24C engine. At rated engine speed and maximum permissible turbine-discharge temperature, the altitude limit as determined by combustion blow-out occurred as a band of unstable operation of about 8000 feet altitude in width with maximum altitude limits from 32,000 feet at a Mach number of 0.3 to about 42,000 feet at a Mach number of 1.0. The maximum fuel-air ratio of the afterburner, as limited by maximum permissible turbine-discharge gas temperatures at rated engine speed, varied between 0.0295 and 0.0380 over a range of flight Mach numbers from 0.25 to 1.0 and at altitudes of 20,000 and 30,000 feet. Over this range of operating conditions, the fuel-air ratio at which lean blow-out occurred was from 10 to 19 percent below these maximum fuel-air ratios. Combustion was very smooth and uniform during operation; however, ignition of the burner was very difficult throughout the investigation. A failure of the flame holder after 12 hours and 15 minutes of afterburner operation resulted in termination of the investigation.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Analysis of Combustion-Chamber Performance

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Analysis of Combustion-Chamber Performance

Date: August 23, 1948
Creator: Campbell, Carl E.
Description: Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 4, Operational Characteristics

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 4, Operational Characteristics

Date: August 23, 1948
Creator: Hawkins, W. Kent & Meyer, Carl L.
Description: An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures were evaluated.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 6, Analysis of Effects of Inlet Pressure Losses

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 6, Analysis of Effects of Inlet Pressure Losses

Date: January 1, 1948
Creator: Sanders, Newell D. & Palasics, John
Description: The losses in the inlet air ducts, the diffusers, and the de-icing equipment associated with turbojet engine installations cause a reduction in the total pressure at the inlet of the engine and result in reduced thrust and increased specific fuel consumption. An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of a 3000-pound-thrust axial flow turbojet engine with a two-stage turbine is presented. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel. The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 7, Pressure and Temperature Distributions

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 7, Pressure and Temperature Distributions

Date: December 10, 1948
Creator: Saari, Martin J. & Prince, William R.
Description: Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST