Analysis Of Wind Tunnel Tests To A Mach Number Of 0 90 Of A Four Engine Propeller Driving Airplane Configuration Having A Wing With 40 Degrees Sweepback And An Aspect Ratio Of 10

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Analysis of Wind-tunnel Tests to a Mach Number of 0.90 of a Four-engine Propeller-driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10

George G. Edwards
Analysis of Wind tunnel Tests to a Mach Number of 0 90 of a Four engine Propeller driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 Book PDF

Author : George G. Edwards
Publisher : Unknown
Page : 658 pages
File Size : 48,9 Mb
Release : 1956
Category : Aerodynamics
ISBN : STANFORD:36105024832177

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Analysis of Wind-tunnel Tests to a Mach Number of 0.90 of a Four-engine Propeller-driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 by George G. Edwards Pdf

An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.

The Effects of Compressibility on the Upwash at the Propeller Planes of a Four-engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10

Armando E. Lopez,Jerald K. Dickson
The Effects of Compressibility on the Upwash at the Propeller Planes of a Four engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10 Book PDF

Author : Armando E. Lopez,Jerald K. Dickson
Publisher : Unknown
Page : 46 pages
File Size : 45,8 Mb
Release : 1953
Category : Aerodynamics
ISBN : UOM:39015086432765

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The Effects of Compressibility on the Upwash at the Propeller Planes of a Four-engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10 by Armando E. Lopez,Jerald K. Dickson Pdf

The results indicate that for Mach numbers up to 0.60 the upwash angles can be predicted accurately by the available theoretical methods. At Mach numbers above 0.60 the experimental values were less than those predicted by theory and this difference increased with increasing Mach number.

Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail

Paul T. Soderman,Thomas N. Aiken
Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail Book PDF

Author : Paul T. Soderman,Thomas N. Aiken
Publisher : Unknown
Page : 108 pages
File Size : 49,9 Mb
Release : 1971
Category : Airplanes
ISBN : UIUC:30112106692574

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Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail by Paul T. Soderman,Thomas N. Aiken Pdf

The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.

Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies

Thomas C. Kelly
Transonic Wind tunnel Investigation of Aerodynamic loading Characteristics of a 2 percent thick Trapezoidal Wing in Combination with Basic and Indented Bodies Book PDF

Author : Thomas C. Kelly
Publisher : Unknown
Page : 82 pages
File Size : 42,8 Mb
Release : 1957
Category : Aerodynamic load
ISBN : UOM:39015086507152

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Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies by Thomas C. Kelly Pdf

Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.

The Effects of Compressibility on the Upwash at the Propeller Planes of a Four-engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10

Armando E. Lopez,Jerald K. Dickson
The Effects of Compressibility on the Upwash at the Propeller Planes of a Four engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10 Book PDF

Author : Armando E. Lopez,Jerald K. Dickson
Publisher : Unknown
Page : 38 pages
File Size : 42,7 Mb
Release : 1956
Category : Aerodynamics
ISBN : OCLC:681759187

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The Effects of Compressibility on the Upwash at the Propeller Planes of a Four-engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10 by Armando E. Lopez,Jerald K. Dickson Pdf

The results indicate that for Mach numbers up to 0.60 the upwash angles can be predicted accurately by the available theoretical methods. At Mach numbers above 0.60 the experimental values were less than those predicted by theory and this difference increased with increasing Mach number.

Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6

Robert J. Platt
Transonic Wind tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing body Combination of Aspect Ratio 4 and Taper Ratio 0 6 Book PDF

Author : Robert J. Platt
Publisher : Unknown
Page : 50 pages
File Size : 40,7 Mb
Release : 1955
Category : Aerodynamic load
ISBN : UOM:39015095100858

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Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6 by Robert J. Platt Pdf

A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.

Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives

James W. Wiggins
Wind tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 and at High Subsonic Mach Numbers Including a Semiempirical Method of Estimating the Rolling Derivatives Book PDF

Author : James W. Wiggins
Publisher : Unknown
Page : 54 pages
File Size : 48,5 Mb
Release : 1954
Category : Airplanes
ISBN : UOM:39015086490375

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Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives by James W. Wiggins Pdf

An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.

Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4

Paul G. Fournier
Wind tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing fuselage Combination Having a Triangular Wing of Aspect Ratio 4 Book PDF

Author : Paul G. Fournier
Publisher : Unknown
Page : 34 pages
File Size : 53,8 Mb
Release : 1953
Category : Airplanes
ISBN : UOM:39015086490300

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Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4 by Paul G. Fournier Pdf

The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.

An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47© Sweepback, Aspect Ratio 3.5, and Taper Ratio 0.2 in the Slotted Test Section of the Langley 8-foot High-speed Tunnel

Ralph P. Bielat
An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47 Sweepback Aspect Ratio 3 5 and Taper Ratio 0 2 in the Slotted Test Section of the Langley 8 foot High speed Tunnel Book PDF

Author : Ralph P. Bielat
Publisher : Unknown
Page : 44 pages
File Size : 48,9 Mb
Release : 1951
Category : Aerodynamics, Transonic
ISBN : UOM:39015086506873

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An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47© Sweepback, Aspect Ratio 3.5, and Taper Ratio 0.2 in the Slotted Test Section of the Langley 8-foot High-speed Tunnel by Ralph P. Bielat Pdf

Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.

Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing

Arvid L. Keith
Low speed Wind tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing Book PDF

Author : Arvid L. Keith
Publisher : Unknown
Page : 76 pages
File Size : 55,6 Mb
Release : 1950
Category : Air ducts
ISBN : UOM:39015086464701

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Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing by Arvid L. Keith Pdf

A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.

Blockage Study of a 1/16-scale B-1 Inlet Model in the 1-ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility

C. F. Anderson,F. M. Jackson
Blockage Study of a 1 16 scale B 1 Inlet Model in the 1 ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility Book PDF

Author : C. F. Anderson,F. M. Jackson
Publisher : Unknown
Page : 170 pages
File Size : 44,6 Mb
Release : 1972
Category : Airplanes
ISBN : UOM:39015104952414

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Blockage Study of a 1/16-scale B-1 Inlet Model in the 1-ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility by C. F. Anderson,F. M. Jackson Pdf

Tests were conducted in the 1-ft Aerodynamic Wind Tunnels (1T and 1S) of the Propulsion Wind Tunnel Facility to obtain estimates of the performance available for the full-scale B-1 inlet/engine tests in the 16-ft Propulsion Wind Tunnels (16T and 16S). Data were obtained with two nacelle configurations and four wing configurations. The maximum test section blockage was 17 percent. Data were obtained at Mach numbers from 0.55 to 1.30 and from 1.71 to 2.30. The tunnel performance for each configuration was evaluated relative to the others and with regard to the capabilities of the 16-ft tunnels. The results of these tests indicate that the available tunnel performance is significantly compromised with the nacelle configuration which has been selected for the full-scale test. The maximum Mach number estimated to be available for the full-scale test in Tunnel 16T is 1.0. To obtain a full range of engine operating points, however, testing should be restricted to M

Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches

Charles F. Whitcomb
Transonic Investigation of Aerodynamic Characteristics of a Swept wing Fighter airplane Model with Leading edge Droop in Combination with Outboard Chord extensions and Notches Book PDF

Author : Charles F. Whitcomb
Publisher : Unknown
Page : 34 pages
File Size : 50,8 Mb
Release : 1956
Category : Aerodynamics, Transonic
ISBN : UOM:39015095100957

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Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by Charles F. Whitcomb Pdf

An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.

Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-speed Wind Tunnel as Affected by the Tunnel Walls

Robert E. Dannenberg
Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low speed Wind Tunnel as Affected by the Tunnel Walls Book PDF

Author : Robert E. Dannenberg
Publisher : Unknown
Page : 678 pages
File Size : 54,6 Mb
Release : 1950
Category : Aerodynamic load
ISBN : STANFORD:36105024796083

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Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-speed Wind Tunnel as Affected by the Tunnel Walls by Robert E. Dannenberg Pdf

Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.

Investigation of the Aerodynamic Characteristics of a Model Wing-propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90°

John W. Draper
Investigation of the Aerodynamic Characteristics of a Model Wing propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90 Book PDF

Author : John W. Draper
Publisher : Unknown
Page : 82 pages
File Size : 54,7 Mb
Release : 1954
Category : Aerodynamics
ISBN : UOM:39015086496323

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Investigation of the Aerodynamic Characteristics of a Model Wing-propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90° by John W. Draper Pdf

This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.

Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections

Jack F. Runckel
Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3 a Taper Ratio of 0 2 and NACA 65A004 Airfoil Sections Book PDF

Author : Jack F. Runckel
Publisher : Unknown
Page : 104 pages
File Size : 49,7 Mb
Release : 1956
Category : Aerodynamic load
ISBN : UOM:39015095100999

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Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections by Jack F. Runckel Pdf

An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.