NAVY MIL-D-17984 A-1956 DATA PRESENTATION REQUIREMENTS INSTALLED ENGINE PERFORMANCE AND AIR INDUCTION SYSTEMS《安装的引擎和空气电磁感应系统的数据显示需求》.pdf

1、MIL-0- 17984A(ASG) I MAY 1956 SuDersedina MILITARY SPECIFICATION DATA PRESENTATION REQuIRE;MENTS, INSTAILED ENGINE PERFORMBNCE AND AIR WCTION SE3TEXS I This specification has been approved by the Department of the Air Force and by the Navy Bureau of Aeronautics. 1. SCOPE 1.1 This specification cover

2、s requirements for presentation of performance characteristics of power plant installations and inlet geomtv srsteiaS, a8 follow, far systems other than reciprocating enghes for all piloted aircraft, guided dasiles, aad target drones: (a) The basic engine performance data, corrected for instal- lati

3、on effects, to be presented as the source of the values of power available in calculating aircraft peic MILD8706 and Bureau of Aeronautics publication SAR-304, or Air Force requirements of Specifications MILD-803b and MIL-D-799. The desired method of calculating and presenting these installation los

4、ses. The infomation required on the control agatems used in manipulating variable geometry features of pow plant installations. a3l ramjet, pulse jet, turbojet, turboprop, and other air-breathing-type propulsion i I formance under the Navy requirements of Specification i (b) (c) 2. APPLICABLE WCDMEN

5、TS of invitation for bids, form a part of this specification to the extent specified herein: 2.1 The following specifications and publication, of the issue in effect on date SPECIFICATIONS Military MIL-A-8629 Airplane Strength and Rigid* MSD-7579 Data, Development Airplane Engineering MIL-D-803k MIL

6、D8706 Data, Design: Contract Requiremeh.l . blet and inlet duct anabsic+- 3.4.1.1 A plan view and For dasiles or special purpose aircraft, ty$ical important conditions in the mission or trajectory should be substituted as appropriate. corrected engine airflow, using free stream Mach number as a para

7、meter. of capture area ratio with angle of attack, up to the manmUm angle practicably attainable by the aircraft, shall dso be shown, 3.4.1.7 versus mass flow ratio at zero angle of attack, using free stream Mach number as a parameter. 3.4.1.6 Plots shall be presented of mass flow ratio and capture

8、area ratio versus The variation A plot shall be presented of total pressure recovery of the inlet and duct 3.4.1.8 A plot shall be presented of total pressure recovery of the inlet and duct versus angle of attack at design mass flow ratios, using free stream Machnumber as a parameter? Dremmre recave

9、rn variations obtdnsd frommsdel or fUl-aca3.e Ceats far oonbjnations of Bactical negative angles of attack shall be included. 3J+,1.8.1 Plote ahstll be presented showing Che radiai and circumferential total conditions shown- below: Mo = O, Subsonic, 1-59 2.0, ,= attainable by the aircraft. Mach numb

10、ers AO/AC Where: k oc AO/AC ._ P Y at which marked changes in the inlet operathg characteristics occur shall be included. Five representative angles of attack ranging fram the minimum to maximum practicably attainable by the aircraft. Approximately six representative values between the maximum and m

11、inimum normally to be encountered with the aircraft. Two representative angles of yawp including the maximum likely to be eaicam-bcired by the aircraft. Free stream Mach niunber, Airplane angle of attack. inlet captuse area ratio. Aircraft paw angle. 3.4.1.9 A plot shdl be presentedl of total pressu

12、re recovery of the inlet and duct VFSUS enghe airflw9 using engine porra= setting and idet area as parameters. This plot shall be presented for each of the operating conditions shorn in table II. inlet-engine matching points selected and wstable openking regions sixdl be shown on this plot. aaxinmm

13、expected for the aircraft shall also be shown on this plot. 3.4.2 appropriate, me exhaust ductg noaaleyos ejector is supplied by the airframe manufacturer and hen the effects of these pwbs ase not included in the engine per- formance curves of the applicable engine specification. The The effects of

14、yaw on inlet stable operating egioris at angles up to the Exhaust duct and exhaust e2tor andLl holude spacing ratio and diameter raticr Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-s L 3.4.2.5.1 mots shall be presented and the fact that the Govern

15、- ment may have formulated, furnished, or in any way supplied Me said drawings, specifications, or other data is not to be regarded by inplication or otherwise as in any manner licensing the holdel- or uiy other person or corporation, or conveying any rights or pe. .;.ssion to manufacture, use, or sell any patented invenkiori 9 - my in any way be related thereto. custodians: Navy - Bureau of Aeronautics Air Force Y Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-