Locheed SR-71A "Blackbird"

MACH 3.32

2 Pratt & Whitney J58 Afterburning Turbojet engines which on "dry" meaning they weren't on afterburner they produced 25,000 Pounds of Force or 110 Kilo-newtons each meaning one of these engines produced that much and together they would make 50,000 Pounds of Force of or 222.41 Kilo-Newtons and that's not on afterburners. On Afterburners these engines would make 32,500 Pounds of Force or 145 Kilo-newtons each. Meaning with the two together they make 65,000 Pounds of Force or 289.13 Kilo-newtons.

82,000ft

11,820 Feet Per Minute

3,250 Miles

Is the percentage of the pressure caused by aircraft's supersonic flight foward that gets translated into usable pressure inside the diffuser for the engine. This ratio is a high 90% for SR-71 when it is flying at MACH 3.2.

The role of the SR-71A is for Strategic Reconnaissance meaning it would do Reconnaissance on Strategic targets such as Enemy Military Bases which could be Airfields, Nuke Silos, Shipyards, Docks, Submarine Pens, Ships, Parked Aircraft, and E.T.C

United States of America

The SR-71A doesn't actually have an "official" name as it is often called "Blackbird" and "Hubu," but it doesn't have an official one. The SR-71A does not bear any consciousness. It is just an aircraft, that is all.

55.6 Feet

107.4 Feet

18.5 Feet

172,000 Pounds

Introduced as a bomber variant of the A-12, it would later become the A-12's Sucessor and being introduced in the December of 1964 and would become the famous Strategic Reconnaissance aircraft, the SR-71A. Where it would be used by the United States Airforce from January 1966 to then be retired by January 26, 1990.

The Locheed A-12 was a high altitude, MACH 3+ Reconnaissance aircraft. It was first made in 1962 and would be the first aircraft with a Reduced Cross Section, making it have a smaller Radar Cross Section that would reduce the likelihood of detection. The A-12 was retired in 1968 in favor of the SR-71A and YF-12.

It had 2 tandem cockpits with there being a crew of 2. The Pilot and a Reconnaissance Systems Officer. The pilot would be in the foward cockpit and the Reconnaissance Systems Officer in the back cockpit.

The SR-71 had Optical Cameras such as the Itek Operational Objectives Cameras, Itek Optical Bar Camera, HYCON Technical Objective Camera(TEOC for short). The SR-71 also has Side-Looking Airborne Radar or SLAR for short, Electronic Intelligence gathering systems, Radar Jammers for Missile and Fighter Defense.

Locheed Martin

Radar Cross Section in basic principle, if it's huge, it can easily be detected, and if it's tiny like 0.0001m² it's almost undetectable, aka STUPIDLY HARD TO DETECT. The SR-71A Blackbird had a Radar Cross Section of 0.01m² about the same as a bird, and yes, the SR-71 was an attempt at improving radar stealth after its predecessor, the A-12.

Lift is generated by an Airfoil(The Wing of an given aircraft) by generating low pressure under the curvature of the wing, and high pressure over the wing. The magnitude of the force acting over a small section of an object immersed in a fluid equals the pressure p times the area A of the section. A quick units check shows that:

p * A = (force/area) * area = force

As discussed on the fluid pressure slide, pressure is a scalar quantity related to the momentum of the molecules of a fluid. Since a force is a vector quantity, having both magnitude and direction, we must determine the direction of the pressure force. Pressure acts perpendicular (or normal) to the solid surface of an object. So, the direction of the force on the small section of the object is along the normal to the surface. We denote this direction by the letter n.

The normal direction changes from the front of the airfoil to the rear and from the top to the bottom. We indicate this variation on the figure by several small arrows pointing perpendicular to the surface and labeled with an n. To obtain the net mechanical force over the entire solid object, we must sum the contributions from all the small sections. Mathematically, the summation is indicated by the Greek letter sigma ( ) The net aerodynamic force F is equal to the sum of the product of the pressure p times the incremental area delta A in the normal direction n.

F =   p * n * delta A

In the limit of infinitely small sections, this gives the integral of the pressure times the area around the closed surface. Using the symbol S dA for integration, we have:

F = S (p * n) dA

where the integral is taken all around the body. On the figure, that is why the integral sign has a circle through it.

If the pressure on a closed surface is a constant, there is no net force produced because the summation of the directions of the normal adds up to zero.

F =   p * n * delta A

In the limit of infinitely small sections, this gives the integral of the pressure times the area around the closed surface. Using the symbol S dA for integration, we have:

F = S (p * n) dA

where the integral is taken all around the body. On the figure, that is why the integral sign has a circle through it.

If the pressure on a closed surface is a constant, there is no net force produced because the summation of the directions of the normal adds up to zero. For every small section there is another small section whose normal points in exactly the opposite direction.

F = S (p * n) dA = p * S n dA = 0

For a fluid in motion, the velocity has different values at different locations around the body. The local pressure is related to the local velocity, so the pressure also varies around the closed surface and a net force is produced. On the figure, at the lower right, we show the variation of the pressure around the airfoil as obtained by a solution of the Euler equations. The blue line shows the variation from front to back on the lower surface, while the red line shows the variation from front to back on the upper surface, The black line gives the reference free stream pressure. Summing the pressure perpendicular to the surface times the area around the body produces a net force.

F = S (p * n) dA

Definitions of Lift and Drag

Since the fluid is in motion, we can define a flow direction along the motion. The component of the net force perpendicular (or normal) to the flow direction is called the lift; the component of the net force along the flow direction is called the drag. These are definitions. In reality, there is a single, net, integrated force caused by the pressure variations along a body. This aerodynamic force acts through the average location of the pressure variation which is called the center of pressure.

Velocity Distribution

For an ideal fluid with no boundary layers, the surface of an object is a streamline. If the velocity

This is the part of the Aircraft's body where the engine, intake, and convergent devergent ejector(Aka Afterburner) is. At speeds under Mach 2 or 2 time the speed of the sound the aircraft acts like any other afterburning turbojet engine. Where air flows into the Nacelle Inlet where the air is diffused behind the supersonic shock waves before moving into the Pratt & Whitney J58's Multi-Axial Compressor where the air is compressed and go through to the burners of the J58 which the fuel is added to create combustion which then. The now super heated exhaust turns a turbine which gives the engines foward thrust and turns the Compressor to keep the engine cycle going, and just after the Pratt & Whitney J58 Engine is the afterburner where more fuel is added in order to get as much oxygen and use as much oxygen as possible for more combustion.

When the aircraft is moving at speeds faster than Mach 2.2, The middle of the inlet is the symmerical spike or intake cone and behind the spike is the diffuser where the compressed air spreads out before entering the engine, The Pratt & Whitney J58 Afterburning Turbojet engine has 6 bypass tubes which only work when the aircraft is going greater than the speeds of Mach 2.2. These bypass tubes move cool air from the Compressor stage to the afterburner where it now acts as a Ram jet thus giving more fuel efficiency to the jet and more power. Now back to the Intake Cone, at supersonics speeds of MACH 1. The intake cone takes the pressure of the leading supersonic shockwave off the engine so that the engines get the best airflow. Inside the Inlet a second shockwave is formed called the normal, where air coming into the nacelle transitions from low-pressure supersonic shockwaves to high-pressure subsonic shockwaves. Where the normal forms inside the intake depends on the speed at which the aircraft is and shape of the intake cone this is all at Mach 1. When the aircraft goes at MACH 1.6, the normal ends up in the best place inside the Intake for pressure recovery. So to get the normal optimal for pressure recovery, the symmerical spike retracts every 1.6 Inches for each .1 increase in Mach number.

When the SR-71A is on the ground, it drips out fuel as the material of the SR-71's body being of a Titanium Composite expands as the SR-71A approaches MACH 3 due to the heat and friction caused by those speeds. The SR-71A's nose could reach nearly 800°F in temperature when it is traveling at MACH 3.