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 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
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Total Pages : 166
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ISBN-10 : NASA:31769000459704
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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 Related Books

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
Language: en
Pages: 166

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

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Type: BOOK - Published: 1960 - Publisher:

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Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections
Language: en
Pages: 48

Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections

Authors: E. O. Pearson
Categories: Aerodynamic load
Type: BOOK - Published: 1945 - Publisher:

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Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high
In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle
Language: en
Pages: 68

In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle

Authors: Mark C. Davis
Categories: Aerodynamic load
Type: BOOK - Published: 2000 - Publisher:

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Pressure distributions on the wings of the F/A-18A High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mount
Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-chord Flap
Language: en
Pages: 94

Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-chord Flap

Authors: W. F. Lindsey
Categories: Aerodynamic load
Type: BOOK - Published: 1946 - Publisher:

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An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a m
Pressure Distributions on a Flat-plate Delta Wing Swept 65 Deg at a Mach Number of 5.97 at Angles of Attack from 65 Deg to 115 Deg and Angles of Roll from 0 Deg to 25 Deg at a 90 Deg Angle of Attack
Language: en
Pages: 32

Pressure Distributions on a Flat-plate Delta Wing Swept 65 Deg at a Mach Number of 5.97 at Angles of Attack from 65 Deg to 115 Deg and Angles of Roll from 0 Deg to 25 Deg at a 90 Deg Angle of Attack

Authors:
Categories:
Type: BOOK - Published: 1962 - Publisher:

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