hypersonic 中文意思是什麼
hypersonic
解釋
adj. 形容詞 高超音速的〈指超音速五倍以上者〉。-
At last, the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed
最後，初步分析了高超聲速彈翼表面發生燒蝕后對其外彈道特性的影響。 -
On exploring design of hypersonic forebody inlet and isolator of integrated scramjet
進氣道和隔離段氣動設計 -
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。 -
Hypersonic wind tunnels operating at very low densities were developed starting in about 1960.
低密度超音速風洞大約開始發展於1960年。 -
Departures form the ideal practice followed by the wright have been particularly noticeable in the development of supersonic and hypersonic vehicles.
特別值得注意的是在發展超音速和高超音速飛行器的過程中，偏離了萊特理想的工作方式。 -
A numerical method for hypersonic aerothermoelasticity
一種高超音速熱氣動彈性數值研究方法 -
Numerical simulation of 3d hypersonic thermochemical nonequilibrium flow
高超聲速三維熱化學非平衡流場的數值模擬 -
Trajectory characteristics of hypersonic waverider missile with rocket extended range
火箭增程乘波外形導彈彈道特性研究 -
Hypersonic sql database
超音速sql數據庫 -
Hypersonic shock tube
高超聲速激波管 -
The paper provides an description of stage separaton of hypersonic vechicle
本文簡述了高超聲速飛行器飛行過程中的分離問題。 -
Hypersonic technology mensurate the amylase content of southernwood form different producing area
超聲法測定不同產地青蒿多糖含量 -
The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc
摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。 -
In this paper, some flows around naca 0012 aerofoil, m6 wing and two different blunt vehicles are simulated, the results show that the present algorithm possesses good characteristics and capability for normal mach number and for hypersonic of simple configurations
通過對naca0012翼型、 m6機翼、鈍頭以及雙鈍錐?柱體的算例驗證，本文能很好的解決一般馬赫數問題，能夠很好的求解簡單外形的高超聲速問題，對于復雜外形飛行器還需要進一步進行研究驗證。 -
Hypersonic propulsion test facility is important for the scramjet ground tests
摘要高超聲速推進風洞是進行超燃沖壓發動機模型地面模擬的重要試驗設備。 -
Scramjet is the perfect propulsive device to hypersonic vehicle, and is a hot issue in current hypersonic technology area
超燃沖壓發動機是高超聲速飛行器理想的動力裝置，是當前高超聲速技術領域的研究熱點。 -
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。 -
Using local piston theory based on cfd to solve hypersonic unsteady aerodynamic loads, the hypersonic aerothermoelasticity is simulated in time domain
在時間域內實現了高超音速熱氣動彈性的模擬。 -
( 2 ) to evaluate the effects of a reaction control jet on the aerodynamic performance of a missile operating at supersonic / hypersonic flight condition, the single and two attitude jet - interaction flow between a lateral jet and the external flow has been analyzed by detailed numerical simulation
（ 2 ）分別計算了單噴流和雙噴流干擾流場。詳細分析了流場結構和彈體表面壓力分佈特性，獲得了一些有實用價值的結果。 -
In the range of flight mach number mo = 3 ~ 7, in order to take the advantage of ramjet and scramjet, a fix - shaped dual - mode scramjet, in which both subsonic and supersonic combustion can be obtained, is used for hypersonic vehicle
在飛行馬赫數m _ = 3 - 7的范圍內，為充分發揮沖壓發動機的性能優勢，高超聲速飛行器採用了既能在亞聲速燃燒模態，又能在超聲速燃燒模態下工作的固定幾何形狀的雙模態沖壓發動機。
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