2 edition of Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds found in the catalog.
Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds
Robert L Stallings
by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||Robert L. Stallings, and Milton Lamb|
|Series||NASA technical paper -- 1889|
|Contributions||Lamb, Milton, Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch|
|The Physical Object|
|Pagination||187 p. :|
|Number of Pages||187|
The presence of shock waves, along with the compressibility effects of high-velocity fluids, is the central difference between supersonic and subsonic aerodynamic flow. The figure below shows a supersonic airfoil with angle of attack (θ), as the angle of attack increases the lift generated increases, up until the stall point (separation point. The F subsequently exhibited very high levels of trim drag at supersonic speeds during its operational lifetime. In March , the initial supersonic tests of the F in the Langley Unitary Plan Wind Tunnel by David S. Shaw confirmed the Langley expectations of high trim drag at supersonic speeds.
Airplanes generally use high angles of attack at lower speeds where the Bernoulli effect is less powerful, and switch to the the Bernoulli effect at higher speeds because having the wing flatter. The aerodynamics of aircraft at high angles of attack is a subject which is being pursued diligently, because the modern agile fighter aircraft and many of the current generation of missiles must perform well at very high incidence, near and beyond stall. However, a comprehensive presentation of.
The present volume discusses tactical missile aerodynamic drag, drag-prediction methods for axisymmetric missile bodies, an aerodynamic heating analysis for supersonic missiles, a component buildup method for engineering analysis of missiles at low-to-high angles of attack, experimental and analytical methods for missiles with noncircular fuselages, and a vortex-cloud model for body vortex. of different theories all of which are applicable only to small angles of attack. To fulfill the high angle of attack requirements, a method for determining the aerodynamic characteristics of low aspect-ratio configurations at zero roll angles operating at angles of attack up to degrees has been developed.
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Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. (a) The aerodynamic characteristics Cℓ and C m linearly depend on the coefficients w ˜ i j * of the downwash w of the thin rectangular wing component, as given in formulas () and (), and, consequently, their dependence on the angle of attack α is also linear, as in (a,b).The coefficients C ℓ 0 (ν), C 1 (ν), C m 0 (ν) and C 2 (ν), entering in formulas (a,b), depend.
At high supersonic speeds the shock cone from the leading edge root angles further back to lie along the wing surface behind the leading edge. It is no longer possible for the sideways flow to occur and the aerodynamic characteristics change considerably.
. The Flow Over Elongated Slender Bodies -- Aircraft Type Configurations -- Vortex Breakdown -- Nonsteady Aerodynamics at High Angles of Attack on Slender Configurations -- Effect of Separation at High Angles of Attack in Hypersonic Flows -- References -- 3 The Topology of Separating and Reattaching Vortical Flows -- At hypersonic speeds, wind tunnel results of viscous interaction effects at high angles of attack are discussed.
In the supersonic region, critical stability and control parameters and wind tunnel results are described. At subsonic speeds, comparisons are shown between predicted aerodynamic characteristics and data from the approach and landing.
Research in supersonic aerodynamics began in the period of II World War i.e. the 's. This research was howerver limited to conventional wings. Maneuverability at supersonic speeds is restricted.
--To avoid deep stall at high angle of attack. A Method for Calculating the Aerodynamic Loading on Wing body Combinations at Small Angles of Attack in Supersonic Flow Book Summary: This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration.
In order to provide a basis for evaluation of the method, experimental measurements of surface. A final way to reinforce what has been shown is to plot the aerodynamic efficiency against angle of attack: The slow speed CH is most efficient at high angles of attack (slow speeds), the C is able to operate efficiently through a large range of cruise speeds and angles of attack, and the F is most efficient at low angles of attack.
The aerodynamic characteristics Cℓ and C m are linearly depending on the coefficients w ˜ i j * of the downwash w of the thin delta wing component, as given in formulas () and (), and, consequently, their dependence on the angle of attack α is also linear, i.e.
supersonic speeds. Special drag prediction problems peculiar to short take- off and landing (STOL) designs, such as jet flap thrust recovery, and energy to-lift at small angle of attack and supersonic wave drag for smooth slender book.
Drag The resultant aerodynamic force caused by a flight vehicle's motion with. aerodynamic characteristics at high angles of attack. are studied at supersonic speeds. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation.
The work has produced methods for calculating the aerodynamic characteristics of: low aspect ratio fins, in the Mach number range ; slender missile bodies at angles of attack to 90° at.
Wing-Alone Data Base. A wing-alone data base, required by the equivalent angle of attack method, is composed of normal-force coefficient data for 0° ≤ c ≤ 90° and ≤ M ∞≤ The AR and range for this data base are the same as those for the fin stability data base described above.
The wing-alone curves were generated from. W.H. Mason Supersonic Aerodynamics 7/31/16 The best paper to read on the B is by Erickson.1 The airplane had a poor safety record. In part this was because the tires were very small to allow the gear to fit in the fuselage.
The takeoff and landing speeds were high, and the tires sometimes blew up. It was also very difficult to maintain. Aerodynamic loads decreased to fairly low levels as the shuttle accelerated past about Mach 5 and the atmospheric density decreased with altitude, thus the aerodynamic testing for the ascent configuration was focused on the subsonic through high supersonic regimes.
Other aspects of the shuttle design further complicated the task for engineers. An experimental and analytical aerodynamic program to develop predesign guides for irregular planform wings is reported.
The benefits are linearization of subsonic lift curve slope to high angles of attack and avoidance of subsonic pitch instabilities at high lift by proper tailoring of the planform fillet wing combination while providing the desired hypersonic trim angle and stability.
Compressibility Effects Importance of the Speed of Sound Realms of Flight Supersonic Flow Patterns V. High Speed Aerodynamics High Speed Airfoils Critical Mac. COMBINATIONS AT HIGH ANGLES OF ATTACK AND SUPERSONIC SPEEDS By Jack N. Nielsen, J. Richard Spahr, and Frank Centolanzi SUMMARY Results are presented on the aerodynamic behavior of bodies, wings, and wing-body combinations at high angles of attack and supersonic speeds.
Maximum lift coefficients for rectangular and triangular wings are pre. Supersonic aerodynamics of delta wings Through the empirical correlation of experimental data and theoretical analysis, a set of graphs has been developed which summarize the inviscid aerodynamics of delta wings at supersonic speeds.
The various graphs which detail the aerodynamic performance of delta wings at both zero-lift and lifting conditions were then employed to. Force at 40,': This animation reveals how pressure to the aircraft exterior changes over a range of Mach, speed applies a significant 1,psf of pressure to the exterior.
Reduced Drag = Greater Efficiency. In the case of aircraft design, the goal is to have the highest lift to drag ratio or L/D ratio (pronounced “L over D ratio”) to improve efficiencies.
"Most useful in working with wing sections and methods for using section data to predict wing characteristics much detailed geometric and aerodynamic data." — Mechanical EngineeringThe first edition of this work has been corrected and republished in answer to the continuing demand for a concise compilation of the subsonic aerodynamics characteristics of modern NASA .The Concorde had a famously high angle of attack (and pitch angle) when led to its famous droop nose.
The Concorde's Russia counterpart, the Tupolev Tu, had the same issue. These are the only two supersonic airliners to have been built, so there is, admittedly, a. Fully supersonic flow. Fully developed waves at bow and tail. FORCE DIVERGENCE • At a speed above M-Crit, airflow will begin to separate from the wing similarly to during a stall.
• This separation will happen even at zero angles of attack. When this separation begins, the aerodynamic drag on the airfoil will begin to increase rapidly.