Basic Glider Criteria HandbookFederal Aviation Agency, Flight Standards Service, 1962 - 139 էջ |
From inside the book
Արդյունքներ 33–ի 1-ից 5-ը:
Էջ vii
... Fuselage tests_ Test loads__ Page 54 54 54 55 55 57 57 57 57 57 57 60 60 60 60 60 60 61 61 62 62 62 62 62 62 62 62 62 62 62 62 67 67 67 67 71 71 71 71 71 71 71 72 72 74 74 74 74 74 75 12135 75 CONTENTS - Continued Page Test methods_ ...
... Fuselage tests_ Test loads__ Page 54 54 54 55 55 57 57 57 57 57 57 60 60 60 60 60 60 61 61 62 62 62 62 62 62 62 62 62 62 62 62 67 67 67 67 71 71 71 71 71 71 71 72 72 74 74 74 74 74 75 12135 75 CONTENTS - Continued Page Test methods_ ...
Էջ ix
... Shock absorption . 111 Wheel support structure_ 112 Brakes 112 Dual wheels _ _ 112 Fuselage design . 112 Purpose- 112 Nose_ 112 Landing gear_ Ground angle and clearance . 112 112 CONTENTS - Continued Page Tail skid .. Provisions for turn ...
... Shock absorption . 111 Wheel support structure_ 112 Brakes 112 Dual wheels _ _ 112 Fuselage design . 112 Purpose- 112 Nose_ 112 Landing gear_ Ground angle and clearance . 112 112 CONTENTS - Continued Page Tail skid .. Provisions for turn ...
Էջ xvi
... flaps , but ignoring fairings and fillets ) , on a surface containing the wing chords . The outline is assumed to extend through the fuselage to the plane of symmetry . ( See fig . i - I . ) Design wing loading , s = W / S. - XVI.
... flaps , but ignoring fairings and fillets ) , on a surface containing the wing chords . The outline is assumed to extend through the fuselage to the plane of symmetry . ( See fig . i - I . ) Design wing loading , s = W / S. - XVI.
Էջ 21
... fuselage . For balancing purposes the net factor is assumed to act at the center of gravity of the glider . FLIGHT PATH β M.A.C. +3 REF . AXIS पुनर LOCATED AT 20 % OF MEAN TAIL CHORD ( CHORD LINE OF M.A.C. ) Aerodynamic center of ...
... fuselage . For balancing purposes the net factor is assumed to act at the center of gravity of the glider . FLIGHT PATH β M.A.C. +3 REF . AXIS पुनर LOCATED AT 20 % OF MEAN TAIL CHORD ( CHORD LINE OF M.A.C. ) Aerodynamic center of ...
Էջ 22
... fuselage drag acts at the center of gravity . When more accurate data are available , the resultant fuselage drag force can of course be computed and applied at the proper point . Where large independent items having considerable drag ...
... fuselage drag acts at the center of gravity . When more accurate data are available , the resultant fuselage drag force can of course be computed and applied at the proper point . Where large independent items having considerable drag ...
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Common terms and phrases
aerodynamic center aileron airfoil airspeed airspeed indicator analysis angle of attack angular applied area under curve axis balancing loads basic flight envelope bending bolts cable center of gravity clevis pins coefficient components computations construction control surface control system criteria curve deflection design gliding speed drag elevator engine equipment factor of safety Federal Aviation Agency Figure flap flight conditions flight tests fuel tank fuselage glider gust load hinge line indicated airspeed inertia installed leading edge load distribution load factor loading conditions located maneuvering load material maximum mean aerodynamic method minimum multiplying factor normal nose obtained operation percent pilot placard plywood portion position powerplant primary structure recommendations ribs rudder skid span distribution spar Splices stabilizer strength stress strut suitable table 1-I table 1-III tail load tail surfaces test load tion torsional towing trailing edge truss tube ultimate load tests vertical vibration weight wheel wires
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Էջ 123 - The airplane shall be controllable and maneuverable during take-off, climb, level flight, glide, and landing and it shall be possible to make a smooth transition from one flight condition to another without requiring an exceptional degree of skill, alertness, or strength on the part of the pilot...
Էջ 47 - Box beams. In computing the ability of box beams to resist bending loads only that portion of the web with its grain parallel to the beam axis and one-half of that portion of the web with its grain at an angle of 45 degrees to the beam shall be considered. The more conservative method of neglecting the web entirely may be employed.
Էջ 43 - Double drag trusses. Whenever double drag trussing is employed, all drag wires shall incorporate a multiplying factor of safety varying linearly from 3.0, when the ratio of overhang to root chord of overhang Is 2.0 or greater, to 1.20 when such ratio Is 1.0 or less, assuming an equal division of drag load between the two systems.
Էջ 135 - Provisions must be made to allow rapid and complete drainage of the cowling in normal ground and flight attitudes. Drains must not discharge In locations constituting a fire hazard.
Էջ xv - Balancing loads. Loads by which the airplane is placed in a state of equilibrium under the action of external forces resulting from specified loading conditions. The state of equilibrium thus obtained may be either real or fictitious. Balancing loads may represent air loads, inertia loads, or both. (See § 4a.ll6.) § 4a.44 Aerodynamic coefficients, CL, CM, CP, etc. The coefficients hereinafter specified are those of the "absolute" (nondimensional) system adopted as standard in the United States.
Էջ xv - CP, etc. The coefficients hereinafter specified are those of the "absolute" (nondimensional) system adopted as standard in the United States. The subscripts N and C used hereinafter refer respectively to directions normal to and parallel with the basic chord of the airfoil section. Other subscripts have the usual significance. When applied to an entire wing or surface, the coefficients represent average values and shall be properly correlated with local conditions (load distribution) as required...
Էջ 133 - Engine breathers must discharge in a location that does not constitute a fire hazard in case foaming occurs and so that oil emitted from the line does not impinge upon the pilots
Էջ 123 - This shall be so at any speed which can be obtained without excessive control force, except that such speeds need not be greater than the appropriate maximum permissible speed or less than the minimum speed in steady unstalled flight.
Էջ 136 - ... cross-feed positions. (2) When more than one fuel tank is provided, and if safe operation depends upon the use of tanks in a specific sequence, the fuel tank selector controls shall be marked adjacent to or on the control to indicate to the flight personnel the order in which the tanks must be used.
Էջ 123 - A pull must be required to obtain and maintain speeds below the specified trim speed, and a push must be required to obtain and maintain speeds above the specified trim speed. This must be shown at any speed that can be obtained except...