Author: Robert J. McGhee
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92
Book Description
Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.
Low-speed Aerodynamic Characteristics of a 17-percent-thick Medium Speed Airfoil Designed for General Aviation Applications
Author: Robert J. McGhee
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92
Book Description
Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92
Book Description
Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.
Low-speed Aerodynamic Characteristics of a 13 Percent Thick Medium Speed Airfoil Designed for General Aviation Applications
Scientific and Technical Information Output of the Langley Research Center for Calendar Year ...
Scientific and Technical Information Output of the Langley Research Center for Calendar Year 1980
NASA Technical Memorandum
Scientific and Technical Aerospace Reports
NASA Scientific and Technical Publications
NASA Supercritical Airfoils
Author: Charles D. Harris
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 80
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 80
Book Description
NASA Technical Paper
Airplane Design: Preliminary configuration design and integration of the propulsion system
Author: Jan Roskam
Publisher: DARcorporation
ISBN: 9781884885433
Category : Technology & Engineering
Languages : en
Pages : 326
Book Description
Publisher: DARcorporation
ISBN: 9781884885433
Category : Technology & Engineering
Languages : en
Pages : 326
Book Description