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The Mission of AGAlRD According to its Charter, the mission of AGARD is to bring together the leading personalities of the NATO nations in thi: fields of science and technology relating to aerospace for the following purposes: -Recommending effective ways for the member nations to use their research and development capabilities for the common benefit of the NATO community; - Providing scientific and technical advice and assistance to the Military Committee in the field of aerospace research and development (with particular regard to its military application); Continuously stimulating advances in the aerospace sciences relevant to strengthening the common defence posture; - Improving the co-operation among member nations in aerospace research and development; -Exchange of scientific and technical information; - Providing assistance to member nations for the purpose of increasing their scientific and technical potential; - Rendering scientific and technical assistance, as requested, to other NATO bodies and to member nations in connection with research and development problems in the aerospace field. The highest authority within AGARD is the National Delegates Board consisting of officially appointed senior representatives from each member nation. The mission of AGARD is carried out through the Panels which are composed of experts appointed by the National Delegates, the Consultant and Exchange Programme and the Aerospace Applications Studies Programme. The results of AGARD work are reported to the member nations and the NATO Authorities through the AGARD wits of publications of which this is one. Participation in AGARD activities is by invitation only and is normally limited to citizens of the NATO n .I t' ions. The content of this publication has been reproduced directly from material supplied by AGARD or the authors. Published December 1991 Copyright 0 AGARD 1991 All Rights Reserved ISBN 92-835-0644-8 Printed by Speciulised Printing Services Limited 40 ChigweN Lune, Loughton, Essex IGIO 3TZ
AGARDOGRAPHS (AG) Design and Testing of High-Performance Parachutes AGARD AG-319, November 199 1 Recent Publications of the Fluid Dynamics Panel Experimental Techniques in the Field of Low Density Aerodynamics AGARDAG-318 (E),April 1991 Techniques Experimentales Likes a I’Aerodynamique a Basse Densit6 AGARDAG-318 (FR),April 1990 A Survey of Measurements and Measuring Techniques in Rapidly Distorted Compressible Turhulent Boundary Layers AGARDAG-315,May 196‘9 Reynolds Number Elfects in Transonic Flows AGARD AG-303, Decembcr 1988 REPORTS (R) Aircraft Dynamics at High Angles of Attack Experiments and Modelling AGARD K-776, Special Course Notes, March 1911 1 Inverse Methods in Airfoil Design for Aeronautical and Turbomachinery Applications AGARD R-780, Special Course Noies, Novcmber 1990 Aerodynamics of Rotorcraft AGARD R-781, Special Course Notes, November 1990 Three-Dimensional Supersonic/Hypcrsonic Flows Including Separation AGAKD R-764, Special Course Notes, January 1990 Advances in Cryogenic Wind Tunnel Technology AGARD R-774, Special Course Noies, November 1989 ADVISORY REPORTS (AR) Air Intakes for High Speed Vehicles AGARD AR-270, September 1991 Appraisal of the Suitability of Turbulence Models in Flow Calculations AGARD AR-291, Technical Status Review, July 1 99 1 Rotary-Balance Testing for Aircraft Dynamics AGARDAR-265,Reportof WG 11,December 1990 Calculation of3D Separated Turbulent Flows in Boundary Layer Limit AGARDAR-ZSS,ReportofWGlO, May 1990 Adaptive Wind Tunnel Walls: Technology and Applications AGARDAR-269,Rcportof WG12,April 1990 CONFERENCE PROCEEDINGS (CP) Elfects of Adverse Weather on Aerodynamics AGARD CP-496, December 199 1 Manoeuvring Aerodynamics AGARDCP-497,Novcmber 1991 Vortex Flow Aerodynamics AGAKD CP-494, July 199 1 Missile Aerodynamics AGARD CP-493, October I990
Page 1: I” AGARD-CP-496 K U 3 ADVISORY GR
Page 6 and 7: 1-4 the stall protection and the "A
Page 8 and 9: 1-8 3 TABLE I - DIGITAL FLIGHT WCOR
Page 10 and 11: 1-20 27 CALCULATED CWAR I SON EXPER
Page 12 and 13: 3-4 effect on ice types similar to
Page 14 and 15: 3-6 dimensions, fuel temperature pr
Page 16 and 17: 8-E
Page 18 and 19: 3-12 .S~)eciIy Tank Dimensions _1 S
Page 20 and 21: I 1 Les avions peuvent Btre plus ou
Page 22 and 23: D'une man1 ulO" tren t c degradee e
Page 24 and 25: - Les formes artificielles constitu
Page 27 and 28: Summary ICING SIMULATION A SURVEY O
Page 29 and 30: It is difticult to establish any cl
Page 31 and 32: Potap~zUk3~ has used the ARC2D code
Page 33 and 34: Altitude test facilities provide th
Page 35 and 36: 59) Mikkelsen, K., Juhasz, N., Rana
Page 37 and 38: EZ-S
Page 39: Test Prediction 0 20 40 60 Icing ti
Page 42 and 43: 6-4 - la longueur de la ligne de co
Page 44 and 45: Visualisation de l%volution du coef
Page 46 and 47: 6-8 Maillaae A340 1 Figure 3 - Mail
Page 48 and 49: 6- IO 1.2 1.15 Ec 1.1 1.05 1 A340 C
Page 50 and 51: 6-12 I Figure 11 - Comparalson pour
Page 52 and 53: Initial research on development of
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1-4 Further details regarding the e
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predictions of the vortical spanwis
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7-8 9 9 0 *1 I n I n I 9 N 9 N I I
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y” - , , , - ,0.00.2 0.4 0.6 0.8
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0 n- , I 9 , N N 1 27 'Z SPAN 42 %S
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I v. Fig. 16 Surface oil flow simul
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ABSTRACT EFFECTS OF FROST ON WING A
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sheets originating at the separatio
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The present boundary-layer calculat
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mom ec C, - 0.W7 0.m1 0.0053 0.W9 0
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- "" 4 - 2 - - f '\ - '\ 2D.VARIOUS
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LWC liquid water content, g/m3 MVD
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Powered Force Model The Sikorsky PF
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Total pressure Johnson-Williams Liq
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ange tested there is no statistical
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9-14 rotor diameter. To minimize sc
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9-16 FIGURE 2. ~ FIGURE 1. - OH-58
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FIGURE 5. - SIKORSKY PFB ROTOR HEAD
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2100 RPM 075 = 20 31.3 Ws i = z MlN
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2100 RPM 7 = 2 MIN 15 p 31.3 pl/i -
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9-24 i i i i t i I I FIGURE 19. - E
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S W Y A REVIEW OF ICING RESEARCH AT
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at the surface and at internal posi
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and the temperature and cloud liqui
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drag coefficient with ambient tempe
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9. Flemming, R.J.; Lednicer, D.A.:
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(I io' c1.4' .=8' NK.4 0012 RAE 964
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Figure 13. Comparison of drag coeff
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Pi 4, d 50 1 do Time. sec - Theory
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~ I ! ! I ! ! contaminated. Figure
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esulting from slipstream interactio
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2) The magnitude of the loss of max
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WING-PROPELLER MODEL WITH DISTRIBUT
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2 u J Y 1. 1. 1. 1. 0. 0. 0. 0. -0.
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1. ALPHA 1. I I -b- 1. 1. i Y 0. E
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E Y 1.6 t FIGURE 8 0.1 0.0 -0.0 -0.
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J Y 1. 1. 1. 1. 0. 0. 0. 0. A MEDIU
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CHORD FORCE C, DRAG Cg CLEAN CALCUL
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12-2 (roughness). As can be seen fr
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12-4 discrete leading-edge roughnes
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12-6 installation is shown in Figur
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12-x margin to stall as a function
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13-2 2.0 Windtunnel tests 2.1 FFA W
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13-4 Finallv a take-off was simulat
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13-6 Relative loss of maximum lin C
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0 -5 Peak DE ai rotation -1 5 ~ . ~
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Prcparation of the Ice Certificatio
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14-4 sting at Pratt EU Whitney to v
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14-6 A CFD analysis was undertaken
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- 0 X I + C z 5 r 5 r , . . . '-0.2
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14-11)
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14-12 Figure 20: Flight Cond. Climb
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14-14 I8 18 18 30 3 30 - Figure 29:
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intensity, short-duration rainfall,
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In 1985, Kisielewski (ref 16) perfo
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immersed in rain to achieve a stead
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test conditions. The two sets of da
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15-10 21 22 23 24 25 26 Tunnel via
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Figure 10 - Photograph of 64-210 mo
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Angle of attack for max lift, deg 2
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16-2 Although quantification of the
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16-4 In order to eliminate the capa
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The same cable configuration and Da
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0. c 0 0 FIG.l.- CONDUCTANCE MEASUR
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16-10 / -*- FIG.6.- CALIBRATION UNI
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Y 5.e 4 e 3 8 2 E I E B E . .. .I .
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16-14 0.4 . 0 1 2 3 4 5 t (Sl - -RF
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17-2 force, normal force and pitchi
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17-4 Simulated rainfall rates of 50
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WATER SUPPLY PIPE FROM SPRAY CONTRO
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17-8 2.75 2.50 - m 100 mmlhr MODEL
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17-10 3.00 2.75 2.50 - 2.25 - CL 2.
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IX-2 thinning properties, should fl
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18-4 knots and a pitch-up angle of
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18-6 define a limit curve, below wh
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IX-8 Fig. 2 5.0 4.0 3.0 2.0 1.0 0 D
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AXIN. FORCE BALANCE ONT NORUAL BALA
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18-12 7 I a) Initial wave formation
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18-14 2.4 2.0 1.6 1.2 , 4.9" 4 VKI
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Fig. 14 14 - VKI/AEA Phase 3 12 _Vi
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I E E 24 I 2 20 w z 11 v - 16 z + S
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18-20 - 14 H 12 Y 10 in 0 H z w la
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19-2 low viscosity throughout the n
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19-4 I , -30 -11 -10 Temperature, '
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Fipm 14. Lfi LosslBos,idor? Layo- D
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Tunnel lnvestigarion of Aerodynamic
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RTL-2 extended. The paint that he m
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RTD-4 Another paper in that group w
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1. Recipient’s Reference 2. Origi
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1 The FDP organized this meeting to
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aGam NATO @ OTAN 7 RUE ANCELLE 9220
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