召集所有想考Cadet Pilot既巴絲

skytest

要錢，有冇free software?

... 少少錢都唔肯比 叫你比錢去試飛咪更加唔洗諗

有無玩skytest既coordination test?我個個支針幾乎唔識跳，但係setting 已經校到好難，求教

邊個version 雖然唔覺得有關係

middle east, 其他方面都好好，係哩個好麻麻

巴打覺得有冇用？

有，抵買

有冇巴打知道lift generation有冇定論？
有啲人話bernoulli principles + equal time assumption係錯嘅
有啲人又話啱

乜你諗到咁深奧

Moving air + different pressure on top and below the aerofoil 咪算

你咁樣又好似簡單咗啲喎
個different pressure係因為咩？
空氣流動速度越快氣壓越低，反之亦然
但點解upper wing surface會快過lower wing surface？

以前學 upper wing 個curvature大啲，因為上下方嘅air要meet at trailing edge at the same time所以upper wing surface嘅空氣流動速度快啲
但好似好多人都話equal time 個assumption唔啱...

Equal time assumption 一定係錯 咁解釋唔到點解symetric airfoil 會有lift

但係symetric airfoil喺AOA=0 deg 係冇lift ga bor

Angel of attack =/= angel of incidence

有冇巴打知道lift generation有冇定論？
有啲人話bernoulli principles + equal time assumption係錯嘅
有啲人又話啱

乜你諗到咁深奧

Moving air + different pressure on top and below the aerofoil 咪算

你咁樣又好似簡單咗啲喎
個different pressure係因為咩？
空氣流動速度越快氣壓越低，反之亦然
但點解upper wing surface會快過lower wing surface？

以前學 upper wing 個curvature大啲，因為上下方嘅air要meet at trailing edge at the same time所以upper wing surface嘅空氣流動速度快啲
但好似好多人都話equal time 個assumption唔啱...

Equal time assumption 一定係錯 咁解釋唔到點解symetric airfoil 會有lift

但係symetric airfoil喺AOA=0 deg 係冇lift ga bor

Angel of attack =/= angel of incidence

sorry 唔明,同angle of incidence 有關係?

有冇巴打知道lift generation有冇定論？
有啲人話bernoulli principles + equal time assumption係錯嘅
有啲人又話啱

乜你諗到咁深奧

Moving air + different pressure on top and below the aerofoil 咪算

你咁樣又好似簡單咗啲喎
個different pressure係因為咩？
空氣流動速度越快氣壓越低，反之亦然
但點解upper wing surface會快過lower wing surface？

以前學 upper wing 個curvature大啲，因為上下方嘅air要meet at trailing edge at the same time所以upper wing surface嘅空氣流動速度快啲
但好似好多人都話equal time 個assumption唔啱...

Equal time assumption 一定係錯 咁解釋唔到點解symetric airfoil 會有lift

但係symetric airfoil喺AOA=0 deg 係冇lift ga bor

Angel of attack =/= angel of incidence

sorry 唔明,同angle of incidence 有關係?

我都唔明...

各位巴絲, 我有個問題想問問,
Bernoulli's Principle (唔好理同唔同意呢個principle先)話
the higher the velocity, the lower the pressure
under equal time assertion, air pass through above is faster than below.
問題來了, 咁點解beoing airbus都副引擎係翼底度? (當然都有裝係個頂度)
引擎吸入既airflow唔會比above the wing快咩?

唔知我有無問錯問題, 各位請解答

有冇巴打知道lift generation有冇定論？
有啲人話bernoulli principles + equal time assumption係錯嘅
有啲人又話啱

乜你諗到咁深奧

Moving air + different pressure on top and below the aerofoil 咪算

你咁樣又好似簡單咗啲喎
個different pressure係因為咩？
空氣流動速度越快氣壓越低，反之亦然
但點解upper wing surface會快過lower wing surface？

以前學 upper wing 個curvature大啲，因為上下方嘅air要meet at trailing edge at the same time所以upper wing surface嘅空氣流動速度快啲
但好似好多人都話equal time 個assumption唔啱...

Bernoulli Principle可以理解做Total pressure = constant
而Total pressure ＝ Static + Dynamic
如果個Speed上升, base on dynamic pressure個Equation (1/2 rho v-squared), dynamic pressure就會上升
根據Bernoulli Principle, Dynamic pressure多左, static pressure就會相對降低
所以Speed上升, static pressure就會越低
個Wing既Design係令到上面既Airflow係快過下面
所以Static pressure difference就會Generate到Lift

有無人知因航而家係咪ban哂考過一次以上嘅人？我同另一個考過一次嘅friend上個月報咗到而家都無回音，相反未考過嘅人一報就一個月內有得1A

有無人知因航而家係咪ban哂考過一次以上嘅人？我同另一個考過一次嘅friend上個月報咗到而家都無回音，相反未考過嘅人一報就一個月內有得1A

我未考過都未有，3月尾報

留名轉渣飛機

想問下apply 咗超過一個月都冇email係咪收得皮

想問下apply 咗超過一個月都冇email係咪收得皮

唔係

已經唔係物唔物理既問題
係連邏輯有冇都成問題, 好難救

膠都廢事俾，由頭到尾淨係得你自己講唔係讀理科就Pass唔到gfs written, 依家我就同你講唔係，事實上份野大部份都係簡單maths加計下時間。e.g唔同time zone搵返flight time.所以先顯出咁都覺得難就唔適合做機師

根住你自己就話好多機師都係文科出身 都唔知你講乜勁。

最後想話你知，好多人fail written係因為第二份卷，即係matrix考邏輯個份

利申year 2個陣得閑得滯去左考，冇prep過in去到leadership assessment

師兄請問你點知比較多人fail第二份matrix卷?

請教各位，點解個L/D ratio點計到呢條線出黎
Coefficient of lift / coefficient of drag
除左L/D計到10之外，其他點畫到條線出黎

請教各位，點解個L/D ratio點計到呢條線出黎
Coefficient of lift / coefficient of drag
除左L/D計到10之外，其他點畫到條線出黎

?咪每一個點 CL/CD 計出黎
定你問點知CL同CD

請教各位，點解個L/D ratio點計到呢條線出黎
Coefficient of lift / coefficient of drag
除左L/D計到10之外，其他點畫到條線出黎

?咪每一個點 CL/CD 計出黎
定你問點知CL同CD

我想知個lift drag ratio每點計出黎同個圖既線點解唔同
同埋兩個coefficient係同AOA有關？
係點計出黎
Thanks 巴打

請教各位，點解個L/D ratio點計到呢條線出黎
Coefficient of lift / coefficient of drag
除左L/D計到10之外，其他點畫到條線出黎

?咪每一個點 CL/CD 計出黎
定你問點知CL同CD

我想知個lift drag ratio每點計出黎同個圖既線點解唔同

同埋兩個coefficient係同AOA有關？
係點計出黎
Thanks 巴打

有邊到唔同？

CL同CD係同AoA有關
與其話計出黎 我覺得係sim或者風洞做出黎

請教各位，點解個L/D ratio點計到呢條線出黎
Coefficient of lift / coefficient of drag
除左L/D計到10之外，其他點畫到條線出黎

?咪每一個點 CL/CD 計出黎
定你問點知CL同CD

我想知個lift drag ratio每點計出黎同個圖既線點解唔同
同埋兩個coefficient係同AOA有關？
係點計出黎
Thanks 巴打

條式係L=1/2pV^2*CL* wing area
Drag條式一樣係改咗L同D
兩者者會比AOA影響