Author: Victor M. GanzerPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
Book Description
An Experimental Investigation of the Effect of Wind Tunnel Walls on the Aerodynamic Performance of a Helicopter Rotor
Author: Victor M. GanzerPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
Book Description
An Experimental Investigation of the Effect of Wind Tunnel Walls on the Aerodynamic Performance of a Helicopter Rotor
Author: Victor M. GanzerPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
Book Description
NASA Technical Note
Author: The Effect of Wind-tunnel Wall Interference on the Performance of a Fan-in-wing VTOL Model
Author: Harry H. HeysonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 236
Book Description
Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade With Slotted Airfoils at the Tip
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 134
Book Description
Data for rotors using unconventional airfoils are of interest to permit an evaluation of this technology's capability to meet the U.S. Army's need for increased helicopter mission effectiveness and improved safety and survivability. Thus, an experimental investigation was conducted in the Langley Transonic Dynamics Tunnel (TDT) to evaluate the effect of using slotted airfoils in the rotor blade tip region (85 to 100 percent radius) on rotor aerodynamic performance and loads. Four rotor configurations were tested in forward flight at advance ratios from 0.15 to 0.45 and in hover in-ground effect. The hover tip Mach number was 0.627, which is representative of a design point of 4000-ft geometric altitude and a temperature of 95 degrees F. The baseline rotor configuration had a conventional single element airfoil in the tip region. A second rotor configuration had a forward-slotted airfoil with a -6 degrees slat, a third configuration had a forward-slotted airfoil with a -10 degrees slat, and a fourth configuration had an aft-slotted airfoil with a 3 degrees flap (trailing edge down). The results of this investigation indicate that the -6 degrees slat configuration offers some performance and loads benefits over the other three configurations.
NASA Technical Report
Author: An Experimental Investigation of Wind Tunnel Constraint Effects on the Performance of Helicopter Rotors
Author: A. S. HallidayNASA Technical Memorandum
Author: Scientific and Technical Aerospace Reports
Author: A Wind-tunnel Investigation of Helicopter Directional Control in Rearward Flight in Ground Effect
Author: Robert J. HustonPublisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 44
Book Description
An investigation was conducted in the Langley full-scale tunnel to study the aerodynamics that produce directional-control problems for a helicopter with a tail rotor in low-speed rearward flight in ground effect. A helicopter model mounted close to the tunnel floor was tested in tail winds from 0 to 25 knots.