進氣道 的英文怎麼說

中文拼音 [jìnqìdào]
進氣道 英文
air inlet; admission passage; passage
  • 進 : 進構詞成分。
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 道 : Ⅰ名詞（道路） road; way; route; path 2 （水流通過的途徑） channel; course 3 （方向; 方法; 道理） ...
  • 氣道 : air flue; air passage
  1. Tahir r b, molder s and timofeev e v. unsteady starting of high number air inlets - a cfd study [ r ]. aiaa 2003 - 5191

    梁德旺，袁化成，張曉嘉.影響高超聲速進氣道起動能力的因素[ c ] / / 2005年沖壓發動機技術交流會論文集， 2005
  2. On exploring design of hypersonic forebody inlet and isolator of integrated scramjet

    進氣道和隔離段氣動設計
  3. The effect of exit back pressure and length / height ratio of isolator on forebody / inlet flow field is analyzed and discussed in the paper

    本文還研究了隔離段出口反壓及隔離段長高比對進氣道流場的影響。
  4. This demonstrates that for propulsion - airframe integration, this genus of inlet would be advantageous in keeping the stability of boundary layer coming from the forebody

    一體化設計時，該進氣道對保持前機體來流附面層的穩定性十分有利。
  5. The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km. the three - ramp, mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed. nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given

    根據飛行任務要求，以飛行馬赫數6 ，飛行高度25km為設計點，給定前體預壓縮角、隔離段高度，對具有不同前體長度和不同總壓縮轉角的帶隔離段的前體進氣道進行了設計。
  6. With account for the effect of temperature and shock - boundary layer interaction, the forebody / inlet with plane lip and wedge lip are designed by using the design methods of constant shock wave intensity and constant shock wave angle. in the design, the incidence angle of the first ramp, height of isolator, length of forebody and total turning angle of the designed forebody / inlet models are given

    另外，根據優選結果，給定前體長度、前體預壓縮楔角、總壓縮轉角及隔離段高度，分別用等激波強度和等激波角度的方法設計了唇口平直和唇口帶楔角的前體進氣道。
  7. The calculation results indicate that the starting performance of forebody / inlet with wedge - shaped lip is better than that with plane lip at low flight mach number. at high flight mach number, the performance of the forebody / inlets designed by the two methods is approximate. at low flight mach number, the starting performance of forebody / inlet designed by the method of constant shock wave intensity is better

    結果表明：唇口帶楔角的進氣道在低飛行馬赫數下的起動性能優于唇口平直的進氣道；採用等激波強度和等激波角度方法設計的進氣道在高飛行馬赫數下的性能相近，在低飛行馬赫數下，採用等激波強度方法設計的進氣道起動性能較優。
  8. This engine consists of an inlet, a combustor, and a nozzle.

    這臺發動機由一個進氣道，一個燃燒室和一個尾噴管組成。
  9. The silhouette on top of this post sports intakes stashed beneath the strakes, that cgi shows an older version

    （本貼頂部的側視圖中進氣道被置於邊條的下面，那副cg顯示的是個更老的版本。 ）
  10. The prototype to be flown on may 10 has been modified with work done on its air - intakes, strake and vertical fins, besides modifications in the fuselage

    這架重新設計了機身進氣道，邊條和腹鰭的新型原型機將於5月10日正式試飛。
  11. In addition to a longer nose, aerodynamic modifications feature kfir - style small nose side - strakes to prevent yaw departure at high aoa, a pair of fixed delta canards on the upper parts of the air intakes, dog - tooth outboard leading - edge extensions, and short fences replacing leading - edge slots

    除了一個加長的機鼻外，氣動布局的修改包括：在機鼻兩則裝上可以防止在高攻角下脫離偏航的「幼獅」式小邊條，一對固定在進氣道的三角鴨翼，鋸齒型外翼前緣，和代替前緣翼槽的短翼刀。
  12. Design and performance of s - shaped inlet for high subsonic missiles

    彎進氣道設計及其特性
  13. Numerical simulation of turbulent flow field supersonic inlet

    超聲速進氣道湍流流場的數值模擬
  14. By using the design concept of construction integrating with equipment and dangerous equipment isolating from construction object, the outdoor installing cage is designed for the gas stove, which includes installing burning chamber, waste gas ventage and gas inlet

    以「建築與設備互動」和「危險設施與建築主體隔離」為設計思想，對多功能燃氣具室外安裝箱進行了具體設計，包括燃氣具安裝燃燒室、廢氣排放通道、進氣道3部分。
  15. Cross - section design of a controllable hypersonic inlet. the research is being done at the nanjing university of aeronautics and astronautics

    南京航空航天大學正在進行一個可控高超音速進氣道斷面設計研究。
  16. For studying the performance of solid rocket ramjet under the influence of different flight conditions, it ' s significant to simulate the integrated flow field of inlet and combustor

    因此，開展超聲速進氣道/補燃室流場一體化數值模擬研究對于考查飛行狀態對於火箭沖壓發動機性能的直接影響具有重要的現實意義。
  17. On the basis of these results, the relations of total - pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established

    根據流場計算結果並利用超曲面擬合方法建立了進氣道總壓恢復系數、流量系數與飛行馬赫數、進氣道攻角及二級可調斜板角度之間的關系，由此得到了二元混壓式超聲速進氣道數學模型。
  18. Experiment of boundary layer suction in serpentine inlet under ground running

    蛇形進氣道地面工作狀態附面層抽吸試驗研究
  19. Based on the temperature field obtained by the thermal analysis, a parametric analysis is conducted to investigate the interlaminar stress at the interface between the composite and the thermal barrier in the cross - section of the inlet duct, using the commercial finite element software ansys

    在熱分析的基礎上，採用ansys有限元軟體計算了復合材料進氣道截面在假設工況下的應力場，為碳纖維纏繞復合材料進氣道熱防護方案的設計提供了實用的參考依據。
  20. When there are struts at the divergent parts of inlet, the total pressure recovery coefficients and the kinetic energy coefficients of inlet decrease, and the flow distortion index increases obviously

    當進氣道擴壓段有側向支柱存在時，進氣道總壓恢復系數和動能系數均有所降低，而流場畸變指數則顯著增大。
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