Ulazni podaci:Vitkost 7.85Tezina 1067917 NPotisak T 170000 NPovrsina krila 172 m2SAT 5.24 mϑ-strela krila 25ugao ugradnje kr ϑk=1.2⁰= 0.020944Xa/la 0.25X/l cg 0.335Za/la 0.19

DOPRINOS KRILA DOPRINOS TRUPAa 0.0858 max.porecni presek trupa D.Cz 0.300 0.0401425728 Duzina trupaCmac 0.03 Ln/L

Cx kr= 0.0161+0.0507Cz2 polara krila 0.0161 lm

(dCm/dCz)k -0.007 + X/l cg-Xa/la= 0.078 (dCm/dCz)tr=

Kao sto vidimo doprinos stabilnosti od krila, trupa I pogonske grupe je DESTABILISUCI. Potrebnu stabilnost letelici dace horizontalni rep.

DOPRINOS HRShr 24.4 m2Zh 2.25 mkrak hr d= 28.85nh 0.990 d/b/2 1.520Vh=Sh*d/S*la 0.781 Zh/b/2 0.119

0.085 iz dijagramaϗ1

suzenje krila 4.142 5.89 ϗ2razmah 37.950 ϗ3

dε/dα= 0.513dCmh/dCz -0.373

Ugao ugradnje horiznotalnog repa

ϑh(⁰)= 2.41Cmk Cmac+(Cx-Cz(α-ϑk))Za/la+CzXa/la 0.107Cmtr 0.057007

α=2.3⁰=

ah=ao*λh/λh+3dε/dα=46.2/λ*ϗ1ϗ2ϗ3

ηp=η(1+sinϑ)

(1-dε/dα)*(-ah/a)*Vh*ηh

Gradijent krive stabilnosti

dCm/dCz= -0.091 vidi se da je letelica staticki stabilna

NEUTRALNA TACKA

N= 0.419 42 % neutralna tacka za drzanu komandu za motorni letNo= 0.423 42 % neutralna tacka za drzanu komandu zabezmotorni let

Cz max 1.207Cm za Czmax 0.072dCm/dCz= 0.034797

X/l = 0.14 14 % prednja granica Cz max u vazduhu

tau 0.800δk=0 δk=5 0.087

Cmac 0.032 δk=-5 -0.087Cz Cm δk=-10 -0.1750 0.032 0.027 0.037 0.041

0.5 -0.014 -0.018 -0.009 -0.0041 -0.059 -0.064 -0.055 -0.050

0 0.2 0.4 0.6 0.8 1

-0.100

-0.080

-0.060

-0.040

-0.020

0.000

0.020

0.040

δk=5

δk=0

δk=-5

δk=-10

Cz

Cm

DOPRINOS TRUPA DOPRINOS POGONSKE GRUPEmax.porecni presek trupa D. 4.53 l 8.75

Duzina trupa L 47.32 Ln 14.615 h 0.3815337660.309 lo 8.260 lo/l= 0.175 (dCm/dCz) 0.0138824624.681 S*lm/w*^l 2.605 Sa dijagrama (dCm/dCz) 0.02

(dCm/dCz)tr*(S*lm/w*^l2)= 0.495(dCm/dCz)tr= 0.190 (dCm/dCz) 0.0139

Kao sto vidimo doprinos stabilnosti od krila, trupa I pogonske grupe je DESTABILISUCI.

1.30.950.83→ε= 0.03 ugao povijanja vazdusne stuje

neutralna tacka za drzanu komandu za motorni letneutralna tacka za drzanu komandu zabezmotorni let

Cz sletanje 1.66(dCm/dCz)k -0.122888

δk' 0.087266 5-0.244 -0.329392

Cz δk( RAD)0 0.0873 5 0.0873 5

0.2 0.0384 2 0.0214 10.4 -0.0105 -1 -0.0445 -30.6 -0.0594 -3 -0.1104 -60.8 -0.1082 -6 -0.1762 -101 -0.1571 -9 -0.2421 -14

1.2 -0.2060 -12 -0.3080 -181.4 -0.2548 -15 -0.3739 -211.6 -0.3037 -17 -0.4398 -25

0 51.6 5

dδk/dCz dδk/dCz sletδk(⁰)

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

-30

-25

-20

-15

-10

-5

0

5

10

(X/l)cz=0.3

Sletanje + UT

N

Cz

δk

Krilo:(dCn/dψ)k= -0.0003 stabilisuci

25

Trup: Pogonska grupa:(dCn/dψ)t 0.0043739 (dCn/dψ)g 0.000013

St 171.48768 St 7.392S 172 S 172Lt 47.32 Lt 4.2b 37.95 b 37.95

h1 4.53 h1 2.2h2 4.53 h2 2.1h 4.53 h 2.2

dt1 4.2 dt1 2dt2 4.2 dt2 2lg 3.15 lg 1.1

0.21 0.15Lt/h 10.445916 Lt/h 1.90909091lg/Lt 0.066568 lg/Lt 0.26190476

(dCn/dψ)t,g= 0.004387 destabilisuci

Provera efikasnosti vertikalnog repa-0.001 → optimalno -0.001

av 0.047τv 0.2Vv 0.12647ηv 0.94

Sk/Sh 0.29 → τv 0.2

dCn/dψ=(dCn/dψ)k+(dCn/dψ)t,g+(dCn/dψ)pg+(dCn/dψ)vr+(dCn/dψ)int

ugao strele krila ϑ=

Kβ Kβ

dCn/dδv

Uticaj vertikalnog repa: (dCn/dψ)int: 0niskokrilac

(dCn/dψ)vr -0.00599 stabilisuciav 0.047Sv 39.5 Sk 11.31dv 20.9Vv 0.12647ηv 0.94

Δ2Cnψ -0.0004λve 2.57457 → 0.05bv 8.1

dCn/dψ= -0.001901 stabilisuci

Cn ψ0 0 0

-0.0095 5 0.0873-0.0190 10 0.1745-0.0285 15 0.2618-0.0380 20 0.3491-0.0475 25 0.4363-0.0570 30 0.5236-0.0665 35 0.6109

0 5 10 15 20 25 30 35 40

-0.07

-0.06

-0.05

-0.04

-0.03

-0.02

-0.01

0ψ

Cn

0 5 10 15 20 25 30 35 40

-0.07

-0.06

-0.05

-0.04

-0.03

-0.02

-0.01

0ψ

Cn

Efekat diedra Krilo Trup Vert. rep

ϑ= 3a= 0.0858S= 172 av 0.047b= 37.9 ηv 0.95

Sr= 158 0 Sv 39.5y' 5.46 Zt 2.2 Zv 1.4

-0.001189 0 -0.000379

-0.000928 stabilisuci

Provera efikasnosti krilaca

le/l= 0.19krilca 72-87%

otklon 35lk/lo= 2

λ= 7.85

iz dijagrama Clp -0.47

0.26τ 0.45Δδe 17.5k 0.95pb/2V 0.072226244848 ugao zavojnice koju opisuju krajevi krilaza transportne avione pb/2V=0.07

dCy/dβ

dClkr/dβ= dCltr/dβ= dClvr/dβ=

dCl/dβ

Clδ/τ= (Clδ/τ)0.72b/2- (Clδ/τ)0.87b/2

Inerferencija krilo-trup Inerferencija krilo-v.rep

0.0008 -0.00016dCint/dβ= dCint/dβ=