Static and Dynamic Response of a Design of Differential ... - aerade

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Details of yssvmeter head LIST OF ILLWl'RA?IONS CaXbration curves of differential Fessure versus incidence Variation of sensitivity with Mach Fo. Variation of difPerentia1 pressure with roll angle Resolution in pitch snd yaw Variation of pitot pressure with incidence Recorded static pressure variation with incidence (Id = 1.4) Relation betieen Mxh No. and 'o/p Charts for the determination of 13 and M in terms of the pitot pressure end the differential pressure in the combined plane Electrical analogue of yawmeter and pick-up system Relations betvreen acoustic damping and u.n.f. in flight and wind tunnel and that in still air Dynsmic test eouiJzment Pressure pick-ups Yawmeter with built-in capacity type pick-up Pressure response of yawmeter with bellovs pressure recorder Pressure response of yawmeter with built-in capacity pick-up to an impulse in still air Response of built-in version to mechanical vibration Time lag of interim (long tube) version progrsmmed + 15' at 3 c.p.s. (M = 1.9) Steady state pressure response at fast progranwe speeds (capacity type pick-up) Fressure difference due to an irdependent (subsonic) cross flow velooity Geometric relations between indicated and true incidence end roll angle S -3- a I 2 3 4 5 5 7 a 9 10 II 12 13 14 15 16 17 18 19 20 21
3 a *I *2 c1 c2 a.n.r. g(s) G(S) i k K(M) e L1 L2 "I m2 x "I n2 P PO *pit *ii *PI **2 AP speed of sound tube cross-sectional area LIST OF SYMEOLS -- chamber cross-sectional area acoustic capacitance of the pick-up chamber acoustic eauivalent of the diaphragm compliance dmped natural frequency initial condition functions acoustic equivalent of electrlcal current length of connecting tube betveen pressure holes and pick-up acoustic uxl~ctance of the air in the pressure tubes acoustic equivalent of the diaPhragm mass air mass in each pressure tube mass of pick-up diaphragm and moving parts free stream Mach No. 2x x acoustic d.n.f. = q - z,+ 27: x mechanical d.n.f. = (c$ - 2)" pressure cn hemisphere surface stagnation Pressure (behind norrral shock at supersonic speeds) pressure registered at axial pitot hole free stream static pressure differential pressure between holes forming roll datum differential pressure betc7een holes nr=J to roll datum differential Pressure in the combined (0) plane -4-
Page 1: c. Pi.$-lj 4 I4 A.R.C. TechnIcal Re
Page 5: List of Syrdmls 1 Introduction 2 Te
Page 9: 3 Superscriots . L at Other suffice
Page 12 and 13: This type of instrument has the dis
Page 14 and 15: P = Pa-c y (Po - ps) sin*$ where ps
Page 16 and 17: 3-$ calibres behind the nose in acc
Page 18 and 19: which zmounw ?;o assvr;lin~ thzt si
Page 20 and 21: where the factor 0.22, applicable t
Page 22 and 23: In the present c&se z, = LqS + RI z
Page 24 and 25: The value for v is given by the dif
Page 26 and 27: a = speed of sound in air in the tu
Page 28 and 29: is thus reduced to the determinntio
Page 30 and 31: corresponding to a maximum volume c
Page 32 and 33: would be always m the same sense. T
Page 34 and 35: well, then If the pressure, ppit, f
Page 37: Effect of inaccurate pressure hole
Page 40 and 41: Thus the reqtianent is satisfied pr
Page 42 and 43: &thod 2 Alternatively we may use eq
Page 44 and 45: 4.0.- 3.! j- 2 15 3. O- 2, 5- 2. o-
Page 46 and 47: t----PLANE 1 CI I I I I I I I I I -
Page 48 and 49: 90 p. : STAGNATION PRESSURE FEWIN A
Page 50 and 51: 35 30 AP P, 25 25 3 FIG 9 (b) 0, =
Page 52: VO- I.0 ‘5 = ACWSTI~ DAMPING FACT
Page 55 and 56: 1 , FIG 15. PRESSURE RESPONSE OF YA
Page 58 and 59:
FIG 18 TIME LAG OF INTERIM (LONG TU
Page 60 and 61:
oo7r-- I 0 06 I ,c I 0 05 - 004 *P
Page 64:
0 Crown Copyright 1958 Pubhshed by
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Static and Dynamic Response of a Design of Differential ... - aerade

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