Author: Richard J. RePublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 116
Book Description
An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0
Author: Richard J. RePublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 116
Book Description
An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29
Author: Richard J. RePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 148
Book Description
Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers
Author: L. Stewart RollsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
Book Description
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal
Author: Earl C. WatsonPublisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 34
Book Description
Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet
Author: John A. AxelsonPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 44
Book Description
A preliminary investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles was conducted through a Mach number range from 0.70 to 1.15 by the use of a transonic bump. Ram recovery and pressure distribution were measured for mass-flow ratios up to 0.67. For approximately constant mass-flow ratio, the ram-recovery ratio decreased about 0.05 in the Mach number from 0.85 to 1.1, but generally improved above a Mach number of 1.0 to 1.1. The ram-recovery ratio decreased about 0.05 when the angle between the inlet center plane and the free stream was increased from 0 to 4 degrees, but increased about 0.02 from this reduced value when the angle was increased from 4 to 8 degrees. Increasing the mass flow into the inlet increased the ram recovery, but the improvement became progressively less at the higher mass flows and higher Mach numbers. Static-pressure and total-pressure surveys inside the inlet indicated that the losses in ram recovery were caused principally by the entrance of low-energy air from the surrounding boundary layer which passed over the sharp edges of the ramp walls and mixed with the higher-energy air entering the inlet.
An Experimental Investigation of NACA Submerged Inlets at High Subsonic Speeds
Author: Charles F. HallPublisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 64
Book Description
The data show that variations in the mass of air entering the inlet had a large effect on the ram-recovery ratio. Representative values of ram-recovery ratio were 0.50 with zero flow, 0.90 with 0.6 mass-flow coefficient, and 0.95 with 1.00 mass-flow coefficient. Variations in Mach number and angle of attack, in general, caused less than a 0.03 variation in the ram-recovery ratio.
Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79
Author: Owen H. DavisPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description
Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0
Author: Richard I. SearsPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 22
Book Description
An Experimental Investigation of NACA Submerged Air Inlets on a 1/5-scale Model of a Fighter Airplane
Author: Donald E. GaultPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 40
Book Description
Development of NACA Submerged Inlets and a Comparison with Wing Leading-edge Inlets for a 1/4-scale Model of a Fighter Airplane
Author: Emmet A. MossmanPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 50
Book Description
