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Results for “Angle of attack”

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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At least 739 records · Page 41

All sources NASA NTRS DOE OSTI

NASA NTRS1960

Pressure Distribution of a 0.0667-Scale Model of the X-15 Airplane for an Angle-Of-Attack Range of 0 deg To 28 deg at Mach Numbers of 2.30, 2.88, and 4.65

Pressure distribution on x-15 aircraft model

PRESSURE DISTRIBUTION↗

NASA NTRS1960

AN INVESTIGATION AT SUBSONIC SPEEDS OF AERODYNAMIC CHARACTERISTICS AT ANGLES OF ATTACK FROM -4 DEG TO 100 DEG OF A DELTA-WING REENTRY CONFIGURATION HAVING FOLDING WINGTIP PANELS

Subsonic aerodynamic characteristics of delta- wing reentry vehicle with folding wingtip panels

DELTA WING↗

NASA NTRS1963

STATIC AERODYNAMIC CHARACTERISTICS OF A THREE-STAGE ROCKET VEHICLE HAVING VARIOUS FIN CONFIGURATIONS AT LOW SUBSONIC MACH NUMBERS AND ANGLES OF ATTACK UP TO 28 DEG

Static aerodynamic characteristics of three-stage trailblazer ii rocket vehicle determined in low turbulence pressure wind tunnel

TRAILBLAZER II REENTRY VEHICLE↗

NASA NTRS1963

CENTER-LINE PRESSURE DISTRIBUTIONS ON TWO-DIMENSIONAL BODIES WITH LEADING-EDGE ANGLES GREATER THAN THAT FOR SHOCK DETACHMENT AT MACH NUMBER 6 AND ANGLES OF ATTACK UP TO 25 DEG

Center-line pressure distribution on two- dimensional bodies

PRESSURE DISTRIBUTION↗

NASA NTRS1963

TRANSONIC INVESTIGATION OF THE STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF LOW-ASPECT-RATIONWING-BODY CONFIGURATIONS AT ANGLES OF ATTACK AROM 0 DEG TO 90 DEG

Transonic wind tunnel tests for aerodynamic characteristics of wing-body configurations

TRANSONIC SPEED↗

NASA NTRS1963

WAKE OF A CHARGED PROLATE SPHERIOD AT ANGLE OF ATTACK IN RAREFIED PLASMA

Rarefied gas dynamics - wake of conducting prolate spheroid in magnet-free rarefied plasma

RAREFIED GAS DYNAMICS↗

NASA NTRS1964

Flight measurements of stability and control derivatives of the x-15 research airplane to a mach number of 6.02 and an angle of attack of 25 deg

Flight test data on longitudinal, lateral, and directional stability and control derivatives of X-15 aircraft

X-15 AIRCRAFT↗

NASA NTRS1958

Performance of a 28-inch ramjet utilizing gaseous hydrogen at a mach number of 3.6, angles of attack up to 12 deg, and pressure altitudes up to 110,000 feet

Combustion efficiency of gaseous hydrogen fuel for ramjets at very high altitudes and high distortion

HYDROGEN FUEL↗

NASA NTRS1965

A direct method for computation of nonequilibrium flows with detached shock waves. i - two-dimensional flows. ii - axisymmetric blunt-body at an angle of attack.

Nonequilibrium inviscid flow about arbitrarily shaped body with detached shock waves, using method with time derivative and bypassing boundary conditions

SHOCK WAVE↗

NASA NTRS1965