Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Pressure Distribution and Force and Moment Measurements of an 80 Deg Swept Wing with Twist and Camber at a Mach Number of 2.98
Author: Pressure Distribution and Force and Moment Measurements on an 80 Swept Wing with Twist and Camber at a Mach Number of 2.98
Author: Walter A. VahlPressure Distributions at Mach Number 2.05 on a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber
Author: Harry W. CarlsonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Effects of Twist and Camber on the Low-speed Longitudinal Stability Characteristics of a 45© Swept-back Wing of Aspect Ratio 8 at Reynolds Numbers from 1.5 X 106 to 4.8 X 10 as Determined by Pressure Distributions, Force Tests, and Calculations
Author: George L. PrattPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110
Book Description
Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform
Author: Emma Jean LandrumPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
Book Description
The Effect of Camber and Twist on Wing Pressure Distributions for Mach Numbers from 2 to 7.6: Experimental data
Author: Frank Herman DurginPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 120
Book Description
Pressure Distribution at Mach Number 2.05 on a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber
Author: Harry W. CarlsonCalculation of Camber Using Slender Wing Theory at Mach Number 1.0
Author: William Bernard IgoePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 84
Book Description
Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Author: Harry W. Carlson