Basic Glider Criteria HandbookFederal Aviation Agency, Flight Standards Service, 1962 - 139 էջ |
From inside the book
Արդյունքներ 8–ի 1-ից 5-ը:
Էջ xv
... represent average values and shall be properly correlated with local conditions ( wing load distribution ) as required in Chapter 1 , p . 13. ( See figs . i - II , i - III and i - IV . ) Air density , P. - The mass density of the air ...
... represent average values and shall be properly correlated with local conditions ( wing load distribution ) as required in Chapter 1 , p . 13. ( See figs . i - II , i - III and i - IV . ) Air density , P. - The mass density of the air ...
Էջ 3
... represent wing load factors . The net load factor or acceleration factor should be obtained by proper consideration of balancing loads acting on the glider in the flight conditions specified in this chapter under " Maneuv- ering load ...
... represent wing load factors . The net load factor or acceleration factor should be obtained by proper consideration of balancing loads acting on the glider in the flight conditions specified in this chapter under " Maneuv- ering load ...
Էջ 13
... represent two extreme cases of tip loading . Each case should be investigated , unless it is demonstrated that only one is critical . As an alternative method , it will be acceptable to investigate each design condition for only one ...
... represent two extreme cases of tip loading . Each case should be investigated , unless it is demonstrated that only one is critical . As an alternative method , it will be acceptable to investigate each design condition for only one ...
Էջ 20
... represent a dynamic condition , for structural purposes , as a static condition by the expedi- ent of assigning to each item of mass the increased force with which it resists acceleration . Thus , if the total load acting on the glider ...
... represent a dynamic condition , for structural purposes , as a static condition by the expedi- ent of assigning to each item of mass the increased force with which it resists acceleration . Thus , if the total load acting on the glider ...
Էջ 33
... represent simplified requirements which will result in satisfactory control systems . If he so desires , the designer may use a more rational loading for the design of the control system . The following loadings are considered ...
... represent simplified requirements which will result in satisfactory control systems . If he so desires , the designer may use a more rational loading for the design of the control system . The following loadings are considered ...
Այլ խմբագրություններ - View all
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
Սիրված հատվածներ
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...