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ADVISORY GROUP FOR AEROSPACE RESEARCH 81 DEVELOPMENT 7 RUE ANCELLE 92200 NEUILLY SUR SEINE FRANCE AGARD CONFERENCE PROCEEDINGS 496 Effects of Adverse Weather on Aerodynamics (Les Effets des Conditions Metkorologiques Adverses sur YALrodynamique) Papers presented and discussions held at the Fluid Dynamics Panel -6 Specialists' Meeting held in Toulouse, France, 29th April-1st May 1991. - North Atlantic Treaty Organization Organisation du Traite de I'Atlantique Nord I
Page 1: I” AGARD-CP-496 K U 3 ADVISORY GR
Page 5 and 6: AGARDOGRAPHS (AG) Design and Testin
Page 7 and 8: I I i I (bl Protection against icin
Page 9 and 10: 5 (81 HANNIBAL. MO. APRIL lbl MORTO
Page 11 and 12: Pressure 24 altltude, 16 Pressure 2
Page 13 and 14: test cells intended for aero-engine
Page 15 and 16: Fig 1: Positions and fields of view
Page 17 and 18: tar = -5°C \ tar = 0°C 3 Fig 12:
Page 19 and 20: 1. -E EVOLUTION REGLEMENTAIRE EN MA
Page 21 and 22: - L'utilisation en service montre q
Page 23 and 24: 8.- APPLICATION DE L'AW A D'AUTRES
Page 25: 1, - MAXIMIM CONTINU DEFINITION DES
Page 28 and 29: incorporating an increased understa
Page 30 and 31: mined by evaluating the local colle
Page 32 and 33: ief descriptions of three new icing
Page 34 and 35: 36) Bragg, M.B. and Khodadoust, A,,
Page 36 and 37: 5-22 Figure 1 .--Close-up grazing-a
Page 38 and 39: 5-26 Rgure 21 -Swept. finite w ng w
Page 41 and 42: R&Ud Methcde de calcul de cwEident8
Page 43 and 44: calcul pour obtenir le bon coemcien
Page 45 and 46: Z 0. _- - !x, X V 1 % Pointe avant
Page 47 and 48: L ATR 72 Recherche outomotique de I
Page 49 and 50: 2.5 2 Ec 1.5 1 0.5 __c_/ ATR 72 Coe
Page 51 and 52: Simulation of Iced Wing Aerodynamic
Page 53 and 54:
wing root plane and on the surface
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oundary conditiori misses a signifi
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The computations were performed by
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17 % SPAN 50 %SPAN 0.0 0.2 0.4 0.6
Page 61 and 62:
CHORD CHORD Calculation - Experimen
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0.2 89 %SPAN 56 Z SPAN Calculotion
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? L I 9 - I ? 0 a' u9 0 - ? 0 9 - .
Page 68 and 69:
8-2 Here k is the roughness height
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X-J and IO which show pressure dist
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X-6 10. Head, M.R., "Entrainment in
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Fig. 1 Actual and Preserved Frost S
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SUMMARY MODEL ROTOR ICING TESTS IN
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encounters occurred in the 14 days
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model shaft. This resulted in both
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of the derived parameters will be i
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(pressure) surface. Detailed com- p
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Longer term goals include further P
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FIGURE 3. ~ NASA LEWIS ICING RESEAR
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2100 RPH 31.3 U S e75 = Go -15.0 OC
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2100 RPH 0,5 = 20 31.3 M/S 7 = 2 nl
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0.m D E 4.w L T A 4.010 c L , -0.01
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% 40 30 c 20 . H A N 10 . 0 E 0- 0
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water concentration (LWC), the supe
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periodically varying conditions. Th
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10-6 Figure 14 shows the results ob
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IO-x negative), the program predict
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FLIGHT b ENVIRONMENTAL CONOITIONS E
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IO- I 2 0 Figure 9. Measured drag c
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I 10-14 ACO g Load Factor. L = - =
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CL, Cos, C, wing coefficients with
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11-4 The roughness was applied init
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I 11-6 now no longer contributing a
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MAXIMUM LIFT -5 -4 -3 -2 -1 0 ANGLE
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11-10 1. 1. 1. d k. 0. !A fi & 0. -
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1-12 J v J Y 1. 1. 1. 1. 0. 0. 0. 0
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_1 u PROPELLER THRUST, NORMAL FORCE
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11-16 4. UNPOWERED WING ' 'ROUGHNES
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0.1 E 0 0.0 -0.0 -0.1 -0.1 ALPHA DR
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SUMMARY THE ADVERSE AEROUYNAMIC IMP
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Figure 4. Sideuall SuctionlVenting
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0.5 0.4 0.2 0.0 0.2 0.4 0.8 0.8 10
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-22 .IS A40 = 0.20 Rn = 9 x IO6 g&
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THE EFFECT OF HOAR-FROSTEO WINGS ON
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Wings are normally designed so as t
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t3 Advisory - Circular 1. HIRPOSE.
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30 i Relative loss of maximum lift
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Elevator deflection at take-off Tim
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The tests were accomplished in the
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3.6 Tunne'l Test Program 3.6.1 Inst
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+-L -0.10 -0.05 0 .oo 0 .os XW) FIG
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I-0.02 0 -03 X(M) ___ ., *L TIP SEC
Page 161 and 162:
- c Figure 16: Dornier Do 328 Air I
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Figure 24: Dornier Do 328 Nacelle/I
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SUMNl ARY A SUMMARY OF NASA RESEARC
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a rainf.all rate greater than 200 m
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droplets. The manifold was aligned
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ecorded along with temperature and
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REFERENCES 1. 2. 3. 4. 5. 6. 7. 8.
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Figure 5 - Rain simulation system m
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Figure 15 - An underside view of th
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ABSTRWE Cal.ibration results of liq
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water films on airfoil surfaces und
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is of the order of the inherent err
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4. 5. 6. 7. 8. 9. Tests of a Transp
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0 fIG.4.- DOUBLE ELECTRODE REPRESEN
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F'IG.9.- CLEAN DOUBLE ELECTRODE CAL
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,/ L Landing configuration FIG.13.-
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SUNMFLRY The eEfects of simulated h
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Reynolds number the water film that
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POROUS TURNTABLE NOZZLE PANELS AND
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cnl I a :300 mmlhr IMODEL SURFACE M
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c:l Or -0.4 -I'Ot RC o ClRY 8.8X106
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SUMMARY AERODYNAMIC EFFECTS OF DE/A
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wavy fluid film are different : ind
Page 207 and 208:
6- DEFIIKI'ION OF AN AERODYNAMIC AC
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SETTLING CHAMBER AND CONTRACTION WI
Page 211 and 212:
(mm I (mm I w : : cc w 2 Ix Y o 0 1
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Fig. 7 AIRFOIL MODEL IN TEST SECTIO
Page 215 and 216:
Fig. 9 DIFFERENCE IN WIND-INDUCED S
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2.4 2.0 1.6 1.2 I I I I VKI - A EA
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CONTRACTION I VIU CASSETTE DATA LOG
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- E ,014- E Y ,012- E 8 ,010- 2 H z
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SUMMARY A follow-on wind tunnel inv
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environment for5 minunderessentiall
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737-200ADV. 3D half model 0 Flaps 5
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d. Adequate takeoff acceleration an
Page 231 and 232:
ROUND TABLE DISCUSSION EFFECTS OF A
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Paper 11 was a wind tumel investiga
Page 235 and 236:
Professor Dr. C. Ciray, Middle %st
Page 237 and 238:
AGARD Conference Proceedings 496 Ad
Page 239 and 240:
L" NATO -6- OTAN 7 RUE ANCELLE .922
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