24 Matching Results

Search Results

Advanced search parameters have been applied.
in subjects: "nacelles"  
Results: 1 - 24
open access

Some Lift and Drag Measurements of a Representative Bomber Nacelle on a Low-Drag Wing 2

Description: "Tests of a second representative bomber nacelle on a low-drag wing at a large value of the Reynolds number were made in the NACA two-dimensional low-turbulence pressure tunnel. Results show the drag and interference of the nacelle on the low-drag wing to be small" (p. 1).
Date: September 1942
Creator: Ellis, Macon C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of a Typical Nacelle on the Characteristics of a Thick Low-Drag Airfoil Critically Affected by Leading-Edge Roughness

Description: Report presenting testing to study the effects of a typical nacelle on the characteristics of a thick low-drag airfoil that was shown to be subject to separation difficulties due to leading edge roughness. This testing confirmed the results of previous tests which indicated that the airfoil was unconservative with respect to separation difficulties. Results regarding the internal-flow measurements and corresponding drag increments, external drag, leading-edge roughness and nacelle combination, … more
Date: April 1943
Creator: Ellis, Macon C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-speed tests of radial-engine nacelles on a thick low-drag wing

Description: Report presenting testing in the high-speed wind tunnel to determine the drag characteristics of several types of radial-engine nacelle on a low-drag airfoil. The drag coefficients of nacelles incorporating cowling-nose shapes shown by previous tests to be efficient and afterbodies of adequate length were about the same magnitude as commonly obtained for comparable installations on conventional wings. Results regarding the reduction of data, effect of nacelles on lift, and pressures at wing-nac… more
Date: May 1942
Creator: Becker, John V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Description: Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date: March 11, 1947
Creator: Bartlett, Walter A., Jr. & Goral, Edwin B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Chordwise Positions at the Wing Tip of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the chordwise position of a nacelle at the wing tip of a 45 degree sweptback wing and body combination as determined through transonic flight tests at zero lift. The drag of the configuration with nacelles in the rear chordwise positions was equal to or less than the drag of the configuration without nacelles over most of the speed range.
Date: September 17, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds

Description: Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a wing-nacelle combination at high subsonic speeds. Lift, drag, pitching-moment, and ram-recovery data re presented for a range of Mach and Reynolds numbers.
Date: October 24, 1950
Creator: Boltz, Frederick W. & Buell, Donald A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Tips on a 45 Degree Sweptback Wing and Body Combination

Description: Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.
Date: January 11, 1952
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Tests to Compare the Zero-Lift Drags of 45 Degree Sweptback Wings of Aspect Ratio 3.55 and 6.0 With and Without Nacelles at the Wing Tips

Description: Report presenting tests of rocket-propelled models at transonic speeds to compare the zero-lift drags of 45 degree sweptback wings with and without solid nacelles at the wing tips. The wing drag coefficient was lowered at high subsonic and supersonic speeds when the aspect ratio was reduced from 6.0 to 3.55. Results regarding the favorability of the wing-tip nacelles and the force-break Mach number of the varying configurations are also provided.
Date: March 6, 1952
Creator: Hoffman, Sherwood & Mapp, Richard C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Spanwise Positions on a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.
Date: May 23, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Zero-Lift Drag Determined by Flight Tests at Transonic Speeds of Pylon, Underslung, and Symmetrically Mounted Nacelles at 40 Percent Semispan of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.
Date: June 25, 1951
Creator: Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A small-scale investigation of the effect of spanwise and chordwise positioning of an ogive-cylinder underwing nacelle on the high-speed aerodynamic characteristics of a 45 degree sweptback tapered-in-thickness wing of aspect ratio 6

Description: Report presenting an investigation of a nacelle in three chordwise locations at each of four spanwise locations in an underwing position on a small-size semi-span model of a wing sweptback 45 degrees and tapered in thickness from 9 percent at the root to 3 percent at the tip. Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitching moment characteristics, and lateral center of pressure are provided.
Date: December 18, 1952
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Root on a 45 Degree Sweptback Wing and Body Configuration

Description: Report presenting the zero-lift drag of a sweptback wing and body configuration with nacelles as determined by flight tests of rocket-propelled models at Mach numbers 0.8 to 1.3. Results regarding pressure recovery are also provided.
Date: September 29, 1953
Creator: Hoffman, Sherwood & Wolff, Austin L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Ram-Jet Missile Model Having a Wing and Canard Surfaces of Delta Plan Form With 70 Degree Swept Leading Edges: Force and Moment Characteristics of Various Combinations of Components at a Mach Number of 1.6

Description: Report presenting testing of a ram-jet canard missile model with a wing and horizontal and vertical canard surfaces of delta plan form with 70 degree swept leading edges in the supersonic pressure tunnel. Two ram-jet nacelles were mounted in the vertical plane near the rear of the body and various combinations of components were tested. Results regarding the longitudinal and lateral characteristics, comparison with theory, and effect of nacelles on the model are presented.
Date: March 9, 1953
Creator: Hamilton, Clyde V.; Driver, Cornelius & Sevier, John R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effect of Spanwise Positioning of a Vertically Symmetric Ogive-Cylinder Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness Wing of Aspect Ratio 6 With and Without a Fuselage

Description: Report presenting an investigation of an ogive-cylinder nacelle in various spanwise locations in a vertically symmetric position on a small-size 45 degree sweptback wing of aspect ratio 6 with and without a fuselage. Results regarding the drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.
Date: October 7, 1953
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Transonic Drag of Models of Several Isolated External Stores and Nacelles

Description: Report presenting drag measurements on models of 20 isolated external stores and nacelles flown from the helium gun at a range of Mach numbers. Results regarding fineness-ratio and shape effects, drag correlation, and friction drag are provided. Generally, the shape variations among the various types of stores and nacelles had the expected effects on isolated body drag.
Date: March 11, 1955
Creator: Stevens, Joseph E. & Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Factors Affecting the Carburetor Ram and Nacelle Drag of an A-26B Airplane

Description: "Flight tests of an A-26B airplane have been conducted to determine the changes in maximum speed, as affected by changes in carburetor ram and aerodynamic refinement of the nacelles, resulting from the addition of sealed spinners and modification of the charge air system, cowling, and nacelle afterbodies. The changes in nacelle drag resulting from these modifications were measured independently by means of a revolving wake survey rake behind the nacelle and boundary layer rakes on the cowling, … more
Date: July 1946
Creator: Johnston, J. Ford; Klawans, Bernard B. & Danforth, Edward C. B., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Wing and Nacelle Modifications on Drag and Wake Characteristics of a Bomber-Type Airplane Model

Description: Report presenting an investigation of a model of a large four-engine bomber to determine the effects of several wing and nacelle modifications on drag characteristics and airflow characteristics at the tail. Leading-edge gloves, trailing-edge extensions, and modified nacelle afterbodies were all tested. Results regarding flow characteristics at the wing during flight and at the landing condition, flow characteristics at the tail, and longitudinal stability characteristics are provided.
Date: December 1945
Creator: Neely, Robert H.; Fairbanks, Richard W. & Conner, D. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Description: "An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of several scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and havin… more
Date: September 1939
Creator: McHugh, James G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing-Nacelle-Propeller Tests - Comparative Tests of Liquid-Cooled and Air-Cooled Engine Nacelles

Description: "This report gives the results of measurements of the lift, drag, and propeller characteristics of several wing and nacelle combinations with a tractor propeller" (p. 1). The liquid-cooled engines appeared to have an advantage over the air-cooled engines.
Date: January 1934
Creator: Wood, Donald H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effect of Chordwise Positioning and Shape of an Underwing Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness-Ratio Wing of Aspect Ratio 6

Description: Report presenting an investigation of three different nacelles in an underwing position at the 0.46 semispan station of a 45 degree sweptback wing at three chordwise positions for a range of Mach numbers. The nacelle profiles were an ogive cylinder, an NACA 65A-series airfoil, and an NACA 0-series airfoil (reversed). Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.
Date: January 22, 1953
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Five Full-Scale Propellers in the Presence of a Radial and a Liquid-Cooled Engine Nacelle, Including Tests of Two Spinners

Description: "Wind-tunnel tests are reported of five 3-blade 10-foot propellers operating in front of a radial and a liquid-cooled engine nacelle. The range of blade angles investigated extended from 15 degrees to 45 degrees. Two spinners were tested in conjunction with the liquid-cooled engine nacelle. Comparisons are made between propellers having different blade-shank shapes, blades of different thickness, and different airfoil sections" (p. 589).
Date: 1938
Creator: Biermann, David & Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen