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Problems of High Speed and Altitude Robert Stengel, Aircraft Flight Dynamics MAE 331, 2018
12/14/18 Problems of High Speed and Altitude Robert Stengel, Aircraft Flight Dynamics MAE 331, 2018 Learning Objectives • Effects of air compressibility on flight stability • Variable sweep-angle wings • Aero-mechanical stability augmentation • Altitude/airspeed instability Flight Dynamics 470-480 Airplane Stability and Control Chapter 11 Copyright 2018 by Robert Stengel. All rights reserved. For educational use only. http://www.princeton.edu/~stengel/MAE331.html 1 http://www.princeton.edu/~stengel/FlightDynamics.html Outrunning Your Own Bullets • On Sep 21, 1956, Grumman test pilot Tom Attridge shot himself down, moments after this picture was taken • Test firing 20mm cannons of F11F Tiger at M = 1 • The combination of events – Decay in projectile velocity and trajectory drop – 0.5-G descent of the F11F, due in part to its nose pitching down from firing low-mounted guns – Flight paths of aircraft and bullets in the same vertical plane – 11 sec after firing, Attridge flew through the bullet cluster, with 3 hits, 1 in engine • Aircraft crashed 1 mile short of runway; Attridge survived 2 1 12/14/18 Effects of Air Compressibility on Flight Stability 3 Implications of Air Compressibility for Stability and Control • Early difficulties with compressibility – Encountered in high-speed dives from high altitude, e.g., Lockheed P-38 Lightning • Thick wing center section – Developed compressibility burble, reducing lift-curve slope and downwash • Reduced downwash – Increased horizontal stabilizer effectiveness – Increased static stability – Introduced -
7. Transonic Aerodynamics of Airfoils and Wings
W.H. Mason 7. Transonic Aerodynamics of Airfoils and Wings 7.1 Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = 0.6 or 0.7 to 1.2). Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds. This complicates both computations and wind tunnel testing. It also means that there is very little analytic theory available for guidance in designing for transonic flow conditions. Importantly, not only is the outer inviscid portion of the flow governed by nonlinear flow equations, but the nonlinear flow features typically require that viscous effects be included immediately in the flowfield analysis for accurate design and analysis work. Note also that hypersonic vehicles with bow shocks necessarily have a region of subsonic flow behind the shock, so there is an element of transonic flow on those vehicles too. In the days of propeller airplanes the transonic flow limitations on the propeller mostly kept airplanes from flying fast enough to encounter transonic flow over the rest of the airplane. Here the propeller was moving much faster than the airplane, and adverse transonic aerodynamic problems appeared on the prop first, limiting the speed and thus transonic flow problems over the rest of the aircraft. However, WWII fighters could reach transonic speeds in a dive, and major problems often arose. One notable example was the Lockheed P-38 Lightning. Transonic effects prevented the airplane from readily recovering from dives, and during one flight test, Lockheed test pilot Ralph Virden had a fatal accident. -
Ac 61-107B Chg 1
U.S. Department Advisory of Transportation Federal Aviation Administration Circular Subject: Aircraft Operations at Altitudes Date: 9/9/15 AC No: 61-107B Above 25,000 Feet Mean Sea Level Initiated by: AFS-800 Change: 1 or Mach Numbers Greater Than .75 1. PURPOSE. This advisory circular (AC) alerts pilots transitioning from aircraft with less performance capability to complex, high-performance aircraft that are capable of operating at high altitudes and high airspeeds. In particular, this AC stresses special physiological, equipment, and aerodynamic considerations involved in these kinds of operations. It also provides information to aid pilots in becoming familiar with the basic phenomena associated with high-altitude and high-speed flight. 2. PRINCIPAL CHANGES. Individual variability in hypoxia tolerance was the basis of discussions between the National Transportation Safety Board (NTSB) Chief Medical Officer and the Federal Aviation Administration (FAA) about whether to continue to include information in this AC relating to time of useful consciousness (TUC) (a measure of hypoxia tolerance) with increasing operational altitudes. TUCs are based on data that represent average values and reflect wide variation among pilots in terms of time to incapacitation. There was concern that this table was misleading because of the considerable ranges in TUCs given. Rather than delete the table from the AC, we agreed to augment it with more specific information on why hypoxia tolerances vary among individuals. This is in the form of a CAUTION statement presented underneath the original table. This change also incorporates editorial corrections throughout the document. PAGE CONTROL CHART Remove Pages Dated Insert Pages Dated Page ii 3/29/13 Page ii 9/9/15 Pages 1 thru 3 3/29/13 Pages 1 thru 3 9/9/15 Page 8 3/29/13 Page 8 9/9/15 Page 10 3/29/13 Page 10 9/9/15 Page 24 3/29/13 Page 24 9/9/15 Page 31 3/29/13 Page 31 9/9/15 Page 34 3/29/13 Page 34 9/9/15 Pages 40 thru 45 3/29/13 Pages 40 thru 45 9/9/15 John S. -
Operations Circular 3 of 2011
GOVERNMENT OF INDIA CIVIL AVIATION DEPARTMENT OFFICE OF DIRECTOR GENERAL OF CIVIL AVIATION NEW DELHI OPERATIONS CIRCULAR 3 OF 2011 AV. 22024/8/2010-FSD 21st April 2011 Subject: OPERATIONS OF AIRCRAFT AT ALTITUDES ABOVE 25,000 FEET MSL AND/OR MACH NUMBERS (MMO) GREATER THAN .75 1. PURPOSE. This circular is issued to guide pilots, particularly those who are transitioning from aircraft of lower performance capability to complex, high-performance aircraft that are capable of operating at high altitudes and high airspeeds. It is essential to have knowledge of the special physiological, engine and aerodynamic considerations involved in these operations. 2. BACKGROUND. A series of safety recommendations have required that, among other things, a minimum training curriculum be established for use at pilot schools covering pilots initial transition onto general aviation turbojet airplanes. Aerodynamics and physiological aspects of high-performance aircraft operating at high altitudes were among the subjects recommended for inclusion in this training curriculum. These recommendations were the result of a review of a series of fatal accidents which were believed to involve a lack of flightcrew knowledge and proficiency in general aviation turbojet airplanes capable of operating in a high-altitude environment. Although the near total destruction of physical evidence and the absence of installed flight recorders had prevented authorities to accurately determine the circumstances which led to these accidents, the concern that a lack of flightcrew knowledge and proficiency in the subject matter of this circular was involved in either the initial loss of control or the inability to regain control of the aircraft, or both. -
Ac 61-107A - Operations of Aircraft at Altitudes Above 25,000 Feet Msl And/Or Mach Numbers (Mmo) Greater Than .75
AC 61-107A - OPERATIONS OF AIRCRAFT AT ALTITUDES ABOVE 25,000 FEET MSL AND/OR MACH NUMBERS (MMO) GREATER THAN .75 {New-2003-09} Department of Transportation Federal Aviation Administration 1/2/03 Initiated by: AFS-820 1. PURPOSE. This advisory circular (AC) is issued to alert pilots who are transitioning from aircraft with less performance capability to complex, high-performance aircraft that are capable of operating at high altitudes and high airspeeds, of the need to be knowledgeable about the special physiological and aerodynamic considerations involved in these kinds of operations. 2. CANCELLATION. AC 61-107, Operations of Aircraft at Altitudes Above 25,000 Feet MSL and/or Mach Numbers (Mmo) Greater Than .75, dated January 23, 1991, is cancelled. 3. DEFINITIONS. a. Aspect Ratio is the relationship between the wing chord and the wingspan. A short wingspan and wide wing chord equal a low aspect ratio. b. Aileron buzz is a very rapid oscillation of an aileron, at certain critical air speeds of some aircraft, which does not usually reach large magnitudes nor become dangerous. It is often caused by shock- induced separation of the boundary layer. c. Drag Divergence is a phenomenon that occurs when an airfoil's drag increases sharply and requires substantial increases in power (thrust) to produce further increases in speed. This is not to be confused with MACH crit. The drag increase is due to the unstable formation of shock waves that transform a large amount of energy into heat and into pressure pulses that act to consume a major portion of the available propulsive energy. -
Ntsb/Aar-82-04
.. PB82-910404 AIRCRAFT ACCIDENT REPORT .SKY TRAIN AIR, INC. GATES LEARJET 24, N44CJ FELT, OKLAHOMA OCTOBER 1, 1981 2' 1 NTSB-AAR-82-4 0, I UNITED STATES GOVERNMENT TECHNICAL REPORT DOCUMENTATION PAGE . Report No. 2.Government Accession No. 3.Recipient's Catalog No. NTSB-AAR-82-4 PB82-910404 . Tit le and Subtitle Aviation Accident Report--Sky 5.Report Date Train Air, Inc., Gates Learjet 24, N44CJ, Felt, May 18,1982 Oklahoma, October 1, 1981. 6.Performing- Organization- Code , . Author(s) 8.Performing Organization ~ Report No. 88 National Transportation Safety Board 3435A Bureau of Accident Investigation 11.Contract or Grant No. Washington, D.C. 20594 13.Type of Report and Period Covered 2.Sponsoring Agency Name and Address Aircraft Accident Report October, 1, 1981 NATIONAL TRANSPORTATION SAFETY BOARD - Washington, 0. C. 20594 14.Sponsoring Agency Code 5.Supplcmentrry Notes l6.AbstractAbout 1502 c.d.t., on October 1, 1981, a Sky Train Air, Inc., Learjet 24, N44CJ, crashed 2.5 miles southwest of Felt, Oklahoma. The flightcrew and one passenger, the only occupants on board, were killed. At 1449:39, while in cruise flight at Flight Level 450, en route to McAllen, Texas, from Casper, Wyoming, the flightcrew made initial contact with the Albuquerque Air Route Traffic Control Center. About 1 minute later, the flightcrew failed to respond to a frequency change instruction and the aircraft's transponder beacon code was lost. The controller made several attempts to contact the aircraft but to no avail. Witnesses at Felt heard an aircraft overhead at a very high speed; one witness who saw the aircraft momentarily, stated it was in I a descent angle of about 45'before it struck the ground. -
Airplane Flying Handbook (FAA-H-8083-3B) Chapter 15
Chapter 15 Transition to Jet-Powered Airplanes Introduction This chapter contains an overview of jet powered airplane operations. The information contained in this chapter is meant to be a useful preparation for, and a supplement to, formal and structured jet airplane qualification training. The intent of this chapter is to provide information on the major differences a pilot will encounter when transitioning to jet powered airplanes. In order to achieve this in a logical manner, the major differences between jet powered airplanes and piston powered airplanes have been approached by addressing two distinct areas: differences in technology, or how the airplane itself differs; and differences in pilot technique, or how the pilot addresses the technological differences through the application of different techniques. For airplane-specific information, a pilot should refer to the FAA-approved Airplane Flight Manual for that airplane. 15-1 Jet Engine Basics Although the propeller-driven airplane is not nearly as efficient as the jet, particularly at the higher altitudes and cruising A jet engine is a gas turbine engine. A jet engine develops speeds required in modern aviation, one of the few advantages thrust by accelerating a relatively small mass of air to very the propeller-driven airplane has over the jet is that maximum high velocity, as opposed to a propeller, which develops thrust is available almost at the start of the takeoff roll. Initial thrust by accelerating a much larger mass of air to a much thrust output of the jet engine on takeoff is relatively lower slower velocity. and does not reach peak efficiency until the higher speeds. -
Compressible Flow Related Terms
COMPRESSIBLE FLOW RELATED TERMS Based on Information in Wikipedia, the free encyclopedia Prepared by Patrick H. Oosthuizen Department of Mechanical and Materials Engineering Queen’s University Kingston, Ontario, Canada August, 2009 CONTENTS 1. Area Rule 2. Atmospheric Reentry 3. Ballistic Reentry 4. Blast Wave 5. Choked Flow 6. Compressible Flow 7. Compressibility 8. Compressibility Factor 9. Critical Mach Number 10. DeLaval Nozzle 11. Drag Divergence Mach Number 12. Hypersonic 13. Interferometer 14. Jet Engine 15. Mach Wave 16. Moving Shock Wave 17. Oblique Shock Wave 18. Prandtl-Meyer Function 19. Prandtl-Meyer Wave 20. Real Gas 21. Rocket Engine Nozzle 22. Schlieren Photography 23. Shadowgraph 24. Shock Tube 25. Shock Wave 26. Sonic Boom 27. Sound Barrier 28. Speed of Sound 29. Subsonic and Transonic Wind-tunnels 30. Supercritical Airfoil 31. Supersonic 32. Supersonic Transport Aircraft 33. Supersonic Wind-tunnel 34. Transonic 35. Wave Drag Area rule From Wikipedia, the free encyclopedia The Whitcomb area rule, also called the transonic area rule, is a design technique used to reduce an aircraft's drag at transonic and supersonic speeds, particularly between Mach 0.8 and 1.2. This is the operating speed range of the majority of commercial and military fixed-wing aircraft today. Description The Sears-Haack body shape At high-subsonic flight speeds, supersonic airflow can develop in areas where the flow accelerates around the aircraft body and wings. The speed at which this occurs varies from aircraft to aircraft, and is known as the critical Mach number. The resulting shock waves formed at these points of supersonic flow can bleed away a considerable amount of power, which is experienced by the aircraft as a sudden and very powerful form of drag, called wave drag. -
Some Transonic Aerodynamics
Some Transonic Aerodynamics W.H. Mason Configuration Aerodynamics Class Transonic Aerodynamics History • Pre WWII Prop speeds limited airplane speed – Props did encounter transonic losses • WWII Fighters started to encounter transonic effects – Dive speeds revealed loss of control/Mach “tuck” • Invention of the jet engine revolutionized airplane design • Now, supersonic flow occurred over the wing at cruise • Aerodynamics couldn’t be predicted, so was mysterious! – Wind tunnels didn’t produce good data – Flow was inherently nonlinear, and there were no theoretical methods The Sound Barrier! The P-38, and X-1 reveal transonic control problems/solutions Airfoil Example: Transonic Characteristics • From classical 6 series results Subsonic design pressures Lift From NACA TN 1396, by Donald Graham, Aug. 1947 Drag From NACA TN 1396, by Donald Graham, Aug. 1947 Pitching Moment: a major problem! From NACA TN 1396, by Donald Graham, Aug. 1947 Whats going on? The flow development illustration From Aerodynamics for Naval Aviators by Hurt Addressing the Testing Problem • The tunnels would choke, shocks reflected from walls! • Initial solutions: – Bumps on the tunnel floor – Test on an airplane wing in flight – Rocket and free-fall tests • At Langley (1946-1948): – Make the tunnel walls porous: slots – John Stack and co-workers: the Collier Trophy • Later at AEDC, Tullahoma, TN: – Walls with holes! Wall interference is still an issue - corrections and uncertainty See Becker The High Speed Frontier for the LaRC tunnel story Wall Interference Solution 1: -
Download the Index
The Aviation Historian® The modern journal of classic aeroplanes and the history of flying Issue Number is indicated by Air Force of Zimbabwe: 11 36–49 bold italic numerals Air France: 21 18, 21–23 “Air-itis”: 13 44–53 INDEX Air National Guard (USA): 9 38–49 Air racing: 7 62–71, 9 24–29 350lb Mystery, a: 5 106–107 Air Registration Board (ARB): 6 126–129 578 Sqn Association: 14 10 to Issues 1–36 Air Service Training Ltd: 29 40–46 748 into Africa: 23 88–98 Air-squall weapon: 18 38–39 1939: Was the RAF Ready for War?: Air traffic control: 21 124–129, 24 6 29 10–21 compiled by Airacobra: Hero of the Soviet Union: 1940: The Battle of . Kent?: 32 10–21 30 18–28 1957 Defence White Paper: 19 10–20, Airbus 20 10–19, 21 10–17 MICK OAKEY A300: 17 130, 28 10–19, back cover A320 series: 28 18, 34 71 A A400M Atlas: 23 7 À Paris avec les Soviets: 12 98–107 TAH Airbus Industrie: The early political ABC landscape — and an aerospace Robin: 1 72 “proto-Brexit”: 28 10–19 Abbott, Wg Cdr A.H., RAF: 29 44 Airco: see de Havilland Abell, Charles: 18 14 Aircraft carriers (see also Deck landing, Absolute Beginners: 28 80–90 Ships): 3 110–119, 4 10–15, 36–39, Acheson, Dean: 16 58 42–47, 5 70–77, 6 7–8, 118–119, Addams, Wg Cdr James R.W., RAF: Aeronca 7 24–37, 130, 10 52–55, 13 76–89, 26 10–21 Champion: 22 103–104 15 14, 112–119, 19 65–73, Adderley, Sqn Ldr The Hon Michael, RAF: Aeroplane & Armament Experimental 24 70–74, 29 54 34 75 Establishment (A&AEE): 8 20–27, Aircraft Industry Working Party (AIWP): Addison, Maj Syd, Australian Flying 11 107–109, 26 12–13, 122–129 -
Aerodynamics for Professional Pilots 4Th Edition - 2010
Aerodynamics for Professional Pilots 4th Edition - 2010 Ray Preston B.Sc., M.Ed. Introduction The subject we are studying is called aerodynamics, which means that it has to do with “air” and motion. You may find it productive to imagine how an aeroplane would act in the absence of air and then realize that the difference between that and what happens in the presence of air is what we are studying. In the absence of air an aeroplane would simply fall toward the center of the earth. If it was upside down when dropped it would remain so, if dropped tail first it would fall in that orientation, etc. If you spun it, say like a Frisbee, it would spin around its CG, but otherwise fall. If you started it pitching it would also rotate around its CG while falling, and so on. Such motions are called tumbling. In the air an aeroplane does not fall or tumble. In air, aeroplanes tend to fly straight and always with the front forward and the tail behind. At air shows you may have seen aeroplanes slide tail first, but only for a second or two, then they right themselves and fly nose first. The study of aerodynamics must explain all this as well as the obvious topic of lift, and the unfortunate one of drag. This text was written specifically for students in the Professional Pilot Program at Selkirk College. It is tailored to students interested in becoming pilots, not engineers. The objective of this text is to help pilots understand how an airplane flies in order to pilot it more effectively. -
High-Speed Flow Around Objects Flight Can Be Roughly Classified in Six
High-speed flow around objects Flight can be roughly classified in six categories: High- Regime Subsonic Transonic Sonic Supersonic Hypersonic hypersonic Mach <0.75 0.75–1.2 1.0 1.2–5.0 5.0–10.0 >10.0 For comparison: the required speed for low Earth orbit is approximately 7.5 km/s = Mach 25.4 in air at high altitudes. The speed of light in a vacuum corresponds to a Mach number of approximately 881,000 (relative to air at sea level). At transonic speeds, the flow field around the object includes both sub- and supersonic parts. The transonic period begins when first zones of M>1 flow appear around the object. In case of an airfoil (such as an aircraft's wing), this typically happens above the wing. Supersonic flow can decelerate back to subsonic only in a normal shock; this typically happens before the trailing edge. (Fig.1a) As the speed increases, the zone of M>1 flow increases towards both leading and trailing edges. As M=1 is reached and passed, the normal shock reaches the trailing edge and becomes a weak oblique shock: the flow decelerates over the shock, but remains supersonic. A normal shock is created ahead of the object, and the only subsonic zone in the flow field is a small area around the object's leading edge. (Fig.1b) (a) (b) Fig. 1. Mach number in transonic airflow around an airfoil; M<1 (a) and M>1 (b). When an aircraft exceeds Mach 1 (i.e. the sound barrier) a large pressure difference is created just in front of the aircraft.