Some theoretical characteristics of trapezoidal wings in supersonic flow and a comparison of several wing-flap combinations
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WINGS, TRAPEZOIDAL - CHARACTERISTICS, EFFECT OF CO↗
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Results for “WINGS - SWEEPBACK”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Effect of Finite Span on the Airload Distributions for Oscillating Wings I : Aerodynamic Theory of Oscillating Wings of Finite Span
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FLUTTER - WINGS↗
A WIND-TUNNEL INVESTIGATION AT A MACH NUMBER OF 2.01 OF THE SONIC-BOOM CHARACTERISTICS OF THREE WING-BODY COMBINATIONS DIFFERING IN WING LONGITUDINAL LOCATION
Wind tunnel tests on sonic boom with models of three wing-fuselage combinations
WIND TUNNEL↗
TIME-DEPENDENT AIR FORCES ON WINGS WITH SUPERSONIC LEADING AND TRAILING EDGES AND SUBSONIC SIDE EDGES WITH APPLICATION TO A WING DEFORMING HARMONICALLY ACCORDING TO A GENERAL POLYNOMIAL EQUATION
Time-dependent aerodynamic forces with application to a wing deforming harmonically according to a general polynomial equation
TIME DEPENDENCY↗
TRANSONIC AERODYNAMIC CHARACTERISTICS OF A LATERAL CONTROL EMPLOYING ROTATABLE AIRFOILS MOUNTED VERTICALLY AT THE WING TIPS OF A 45 DEG SWEPTBACK WING, FUSELAGE, AND TAIL COMBINATION
Aerodynamic characteristics of lateral control with rotatable airfoils and sweptback wing
SWEPTBACK WING↗
THE ORIGIN AND DISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGESTORE CONFIGURATIONS. 1.-SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE NACELLE . LIFT AND DRAG, MACH NUMBER, 1.61
Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61
EXTERNAL STORE↗
THE ORIGIN AND DISTRIBUTION OF SUPSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGESTORE CONFIGURATIONS. V - SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE NACELLE. MACH NUMBER 2.01
Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure
EXTERNAL STORE↗
THE ORIGIN AND DISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGESTORE CONFIGURATIONS. III - SWEPT-WING FIGHTER-BOMBER CONFIGURATION WITH LARGE AND SMALL STORES. MACH NUMBER, 1.61
Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores
EXTERNAL STORE↗
Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a V/STOL airplane configuration with a variable-sweep wing and with a skewed wing design
Static longitudinal and lateral aerodynamic characteristics of V/STOL aircraft with variable sweep wing
AERODYNAMIC CHARACTERISTICS↗
Aerodynamic-center considerations of wings and wing-body combinations
Aerodynamic center shifts of rigid wing-body combinations at increased Mach numbers
WING BODY↗
Aerodynamic data on large semispan tilting wing with 0.5-diameter chord, single-slotted flap, and single propeller 0.19 chord below wing
Wind tunnel tests to determine longitudinal aerodynamic characteristics of large scale semispan V/STOL tilt-wing configuration with single propeller
V/STOL AIRCRAFT↗
Aerodynamic data on large semispan tilting wing with 0.5-diameter chord, single-slotted flap, and single propeller 0.08 chord below wing
Longitudinal aerodynamic characteristics of large scale semispan V/STOL tilt-wing configuration having single propeller
AERODYNAMIC CHARACTERISTICS↗
Theoretical lift and damping in roll of thin sweptback tapered wings with raked-in and cross-stream wing tips at supersonic speeds.subsonic leading edges
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LIFT - WINGS, SWEPTBACK↗
Investigation of the Effects of a Nacelle on the Aerodynamic Characteristics of a Swept Wing and the Effects of Sweep on a Wing Alone
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WIND TUNNEL TESTS - NACA - HIGH-SPEED (16')↗
Damping-in-roll calculations for slender swept-back wings and slender wing-body combinations
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WINGS, SWEPTBACK↗
Transonic wind-tunnel investigation of the effect of control span and large wing-tip nacelles on effectiveness of spoiler-slot- deflector controls on an unswept-wing fighter-type airplane
Transonic wind tunnel study of control span and large wing-tip nacelles results on effectiveness of spoiler-slot-deflector controls on fighter aircraft
WIND TUNNEL↗
Aerodynamic data on large semispan tilting wing with 0.4-diameter chord, single-slotted flap, and single propeller 0.22 chord below wing
Aerodynamic characteristics of large semi-span V/STOL tilt-wing with single propeller tested for modes of propeller rotation
Fink, M. P.↗
Pressure Distribution of a Large Semispan Tilting Wing with 0.4-diameter-chord, Single- Slotted Flap, and a Single Propeller 0.22 Chord Below Wing
Aerodynamic pressure distribution on semispan tilting wing-propeller combination of V/STOL aircraft
Fink, M. P.↗