Downloaded from https://www.everyspec.com MIL-STD-810D ,19Ju1y. 1983 TABLE 514.3-III. test values for let ~ m. Aerodynamically induced vibration (fisure 51b.3-26) 1/ Functional test level,3/,’1/ ,. W. = K(q)2 ~ Jet engine noise inducedvibration (figure 514.3-26) 1/ -., Functional test level Z/, 3;, J/, 5/, h/ ,,,, , ,.. W. = (0.48 COS2 8/;) [DC”(Vc;1850)3+Df/1850)31” K ~ = 217 x 1o-8 for cockpit panel equipment and equipment attached to structure in compartments adjacent to external surfacee that are smooth, free from discontinuities. !.
for’‘equipment”attached “to”atructuiiein’compartment adjacent to or immediately aft of external surfaces having diacontinuities (cavities, chins, blade antennas, speed brakes, etc.) and equipments in wings, pylons, stabilizers, and fuselage aft of trailing-edge Wing root. q= 1200 lb/ft2 or maximum aircraft q,.whichever ie leas. Dc = engine core exhaust diameter, feet. (For engines without fana, use maximum exhaust diameter.) Df = engine fan exhau,stdiameter, feet. R = minimum distance,between center of engine aft exhaust plane and the center of gravity of installed equipment, feet. Vc = engine core exhaust velocity, feet peraec..
(For engines without fans’,use maximum exhaust velocity without afterburner?.) Vf i engine fan exhauat velocity, feet per sec. e = angle between R line and engine exhaust axis, aft-vectored, degrees. . . . .. . . ... . .. ... . . ,,, . .0 : ~~~~~~~~~ ., . MRTHOD-514.3 19 July 1983 514.3-37