This paper presents a statistical methodology whereby the probability limits associated with CFD grid resolution of inlet flow analysis can be determined which provide quantitative information on the distribution of that error over the specified operability range. The objectives of this investigation is to quantify the effects of both random (accuracy) and systemic (biasing) errors associated with grid resolution in the analysis of the Lockheed Martin Company (LMCO) N+2 Low Boom external compression supersonic inlet. The study covers the entire operability space as defined previously by the High Speed Civil Transport (HSCT) High Speed Research (HSR) program goals. The probability limits in terms of a 95.0% confidence interval on the analysi...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
A high-quality model validation experiment was performed in the NASA Langley Research Center Unitary...
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol.
In 2016, NASA's Aeronautics Research Mission Directorate announced the New Aviation Horizons Initiat...
Reynolds Averaged Navier-Stokes (RANS) simulations were performed on a Lockheed Martin Quiet SuperSo...
A computational study was performed to explore the aerodynamic performance of a streamline-traced, e...
Concepts are investigated for obtaining both low cowl drag and good inlet performance at high angles...
Two inlet performance tests and one inlet/airframe drag test were conducted in 1969 at the NASA-Ames...
Computational simulations of the flow within a streamline-traced, external-compression supersonic in...
Accurate spillage drag and pressure data are presented for a realistic supersonic inlet configuratio...
Tabular data derived from inlet flow distortion tests of high Mach number transonic fan stages - Vol...
This presentation provides a high level overview of the Large-Scale Low-Boom Inlet Test and was pres...
An axisymmetric panel code was used to evaluate a series of ducted propeller inlets. The inlets were...
The effects of high-angle-of-attack flight on aircraft inlet aerodynamic characteristics were invest...
Inlet pressure fluctuation in XB-70 aircraft during takeoff and prior to compressor stall at Mach 2.
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
A high-quality model validation experiment was performed in the NASA Langley Research Center Unitary...
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol.
In 2016, NASA's Aeronautics Research Mission Directorate announced the New Aviation Horizons Initiat...
Reynolds Averaged Navier-Stokes (RANS) simulations were performed on a Lockheed Martin Quiet SuperSo...
A computational study was performed to explore the aerodynamic performance of a streamline-traced, e...
Concepts are investigated for obtaining both low cowl drag and good inlet performance at high angles...
Two inlet performance tests and one inlet/airframe drag test were conducted in 1969 at the NASA-Ames...
Computational simulations of the flow within a streamline-traced, external-compression supersonic in...
Accurate spillage drag and pressure data are presented for a realistic supersonic inlet configuratio...
Tabular data derived from inlet flow distortion tests of high Mach number transonic fan stages - Vol...
This presentation provides a high level overview of the Large-Scale Low-Boom Inlet Test and was pres...
An axisymmetric panel code was used to evaluate a series of ducted propeller inlets. The inlets were...
The effects of high-angle-of-attack flight on aircraft inlet aerodynamic characteristics were invest...
Inlet pressure fluctuation in XB-70 aircraft during takeoff and prior to compressor stall at Mach 2.
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
A high-quality model validation experiment was performed in the NASA Langley Research Center Unitary...
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol.