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$X-Ray Diffraction Study of the Internal Structure of Supercooled Water$

X-Ray Diffraction Study of the Internal Structure of Supercooled Water

X-ray instrumentation for density measurements in a supersonic flow field

X-ray instrumentation for density measurements in a supersonic flow field

XC-35 gust research project analysis of gust measurements

XC-35 gust research project analysis of gust measurements

XC-35 gust research project characteristics of vertical drafts and associated vertical gust velocities within convective type clouds

XC-35 gust research project characteristics of vertical drafts and associated vertical gust velocities within convective type clouds

XC-35 gust research project operation in cumulus congestus cloud on July 31, 1941 maximum gust intensities

XC-35 gust research project operation in cumulus congestus cloud on July 31, 1941 maximum gust intensities

XC-35 gust research project preliminary analysis of the lateral distribution of gust velocity along the span of an airplane

XC-35 gust research project preliminary analysis of the lateral distribution of gust velocity along the span of an airplane

Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

The zero-lift drag of a 60 degree delta-wing-body combination (AGARD model 2) obtained from free-flight tests between Mach numbers of 0.8 and 1.7

The zero-lift drag of a 60 degree delta-wing-body combination (AGARD model 2) obtained from free-flight tests between Mach numbers of 0.8 and 1.7

Zero-lift drag of a large fuselage cavity and a partially submerged store on a 52.5 degree sweptback-wing-body configuration as determined from free-flight tests at Mach numbers of 0.7 to 1.53

Zero-lift drag of a large fuselage cavity and a partially submerged store on a 52.5 degree sweptback-wing-body configuration as determined from free-flight tests at Mach numbers of 0.7 to 1.53

Zero-lift drag of a series of bomb shapes at Mach numbers from 0.60 to 1.10

Zero-lift drag of a series of bomb shapes at Mach numbers from 0.60 to 1.10

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

Zero-lift drag of several conical and blunt nose shapes obtained in free flight at Mach numbers of 0.7 to 1.3

Zero-lift drag of several conical and blunt nose shapes obtained in free flight at Mach numbers of 0.7 to 1.3

Zero-lift drag of the Chance Vought Regulus II missile at Mach numbers between 0.8 and 2.2 as determined from the flight tests of two 0.12-scale models : TED No. NACA AD 398

Zero-lift drag of the Chance Vought Regulus II missile at Mach numbers between 0.8 and 2.2 as determined from the flight tests of two 0.12-scale models : TED No. NACA AD 398

Zero-lift drag of the chance vought regulus it missile at mach numbers between 0.8 and 2.2 as determined from the flight tests of two o.12-scale models

Zero-lift drag of the chance vought regulus it missile at mach numbers between 0.8 and 2.2 as determined from the flight tests of two o.12-scale models

The zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio

The zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio

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