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6-8 Maillaae A340 1 Figure 3 - Maillages ATR et Airbus pour le calcul aerodynamique Figure 4 - Positionnement des sondes sur ATR A t6moin frontal B: thoin lateral
L ATR 72 Recherche outomotique de Io trojectoire de goutte orrivunt en un point cible donne Guuttes de 50 microns QTR 72 Figure 5 - Recherche automatique du depart des trajectoires Recherche automat ique de la trnjectoire de goutte orriuont en un point cible donne Guutt1:s de 50 microns #
Page 1: I” AGARD-CP-496 K U 3 ADVISORY GR
Page 4 and 5: The Mission of AGAlRD According to
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 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
Page 54 and 55: 1-4 Further details regarding the e
Page 56 and 57: predictions of the vortical spanwis
Page 58 and 59: 7-8 9 9 0 *1 I n I n I 9 N 9 N I I
Page 60 and 61: y” - , , , - ,0.00.2 0.4 0.6 0.8
Page 62 and 63: 0 n- , I 9 , N N 1 27 'Z SPAN 42 %S
Page 64 and 65: I v. Fig. 16 Surface oil flow simul
Page 67 and 68: ABSTRACT EFFECTS OF FROST ON WING A
Page 69 and 70: sheets originating at the separatio
Page 71 and 72: The present boundary-layer calculat
Page 73 and 74: mom ec C, - 0.W7 0.m1 0.0053 0.W9 0
Page 75: - "" 4 - 2 - - f '\ - '\ 2D.VARIOUS
Page 78 and 79: LWC liquid water content, g/m3 MVD
Page 80 and 81: Powered Force Model The Sikorsky PF
Page 82 and 83: Total pressure Johnson-Williams Liq
Page 84 and 85: ange tested there is no statistical
Page 86 and 87: 9-14 rotor diameter. To minimize sc
Page 88 and 89: 9-16 FIGURE 2. ~ FIGURE 1. - OH-58
Page 90 and 91: FIGURE 5. - SIKORSKY PFB ROTOR HEAD
Page 92 and 93: 2100 RPM 075 = 20 31.3 Ws i = z MlN
Page 94 and 95: 2100 RPM 7 = 2 MIN 15 p 31.3 pl/i -
Page 96 and 97:
9-24 i i i i t i I I FIGURE 19. - E
Page 99 and 100:
S W Y A REVIEW OF ICING RESEARCH AT
Page 101 and 102:
at the surface and at internal posi
Page 103 and 104:
and the temperature and cloud liqui
Page 105 and 106:
drag coefficient with ambient tempe
Page 107 and 108:
9. Flemming, R.J.; Lednicer, D.A.:
Page 109 and 110:
(I io' c1.4' .=8' NK.4 0012 RAE 964
Page 111 and 112:
Figure 13. Comparison of drag coeff
Page 113 and 114:
Pi 4, d 50 1 do Time. sec - Theory
Page 115 and 116:
~ I ! ! I ! ! contaminated. Figure
Page 117 and 118:
esulting from slipstream interactio
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2) The magnitude of the loss of max
Page 121 and 122:
WING-PROPELLER MODEL WITH DISTRIBUT
Page 123 and 124:
2 u J Y 1. 1. 1. 1. 0. 0. 0. 0. -0.
Page 125 and 126:
1. ALPHA 1. I I -b- 1. 1. i Y 0. E
Page 127 and 128:
E Y 1.6 t FIGURE 8 0.1 0.0 -0.0 -0.
Page 129 and 130:
J Y 1. 1. 1. 1. 0. 0. 0. 0. A MEDIU
Page 131:
CHORD FORCE C, DRAG Cg CLEAN CALCUL
Page 134 and 135:
12-2 (roughness). As can be seen fr
Page 136 and 137:
12-4 discrete leading-edge roughnes
Page 138 and 139:
12-6 installation is shown in Figur
Page 140 and 141:
12-x margin to stall as a function
Page 142 and 143:
13-2 2.0 Windtunnel tests 2.1 FFA W
Page 144 and 145:
13-4 Finallv a take-off was simulat
Page 146 and 147:
13-6 Relative loss of maximum lin C
Page 148 and 149:
0 -5 Peak DE ai rotation -1 5 ~ . ~
Page 151:
Prcparation of the Ice Certificatio
Page 154 and 155:
14-4 sting at Pratt EU Whitney to v
Page 156 and 157:
14-6 A CFD analysis was undertaken
Page 158 and 159:
- 0 X I + C z 5 r 5 r , . . . '-0.2
Page 160 and 161:
14-11)
Page 162 and 163:
14-12 Figure 20: Flight Cond. Climb
Page 164 and 165:
14-14 I8 18 18 30 3 30 - Figure 29:
Page 166 and 167:
intensity, short-duration rainfall,
Page 168 and 169:
In 1985, Kisielewski (ref 16) perfo
Page 170 and 171:
immersed in rain to achieve a stead
Page 172 and 173:
test conditions. The two sets of da
Page 174 and 175:
15-10 21 22 23 24 25 26 Tunnel via
Page 176 and 177:
Figure 10 - Photograph of 64-210 mo
Page 178 and 179:
Angle of attack for max lift, deg 2
Page 180 and 181:
16-2 Although quantification of the
Page 182 and 183:
16-4 In order to eliminate the capa
Page 184 and 185:
The same cable configuration and Da
Page 186 and 187:
0. c 0 0 FIG.l.- CONDUCTANCE MEASUR
Page 188 and 189:
16-10 / -*- FIG.6.- CALIBRATION UNI
Page 190 and 191:
Y 5.e 4 e 3 8 2 E I E B E . .. .I .
Page 192 and 193:
16-14 0.4 . 0 1 2 3 4 5 t (Sl - -RF
Page 194 and 195:
17-2 force, normal force and pitchi
Page 196 and 197:
17-4 Simulated rainfall rates of 50
Page 198 and 199:
WATER SUPPLY PIPE FROM SPRAY CONTRO
Page 200 and 201:
17-8 2.75 2.50 - m 100 mmlhr MODEL
Page 202 and 203:
17-10 3.00 2.75 2.50 - 2.25 - CL 2.
Page 204 and 205:
IX-2 thinning properties, should fl
Page 206 and 207:
18-4 knots and a pitch-up angle of
Page 208 and 209:
18-6 define a limit curve, below wh
Page 210 and 211:
IX-8 Fig. 2 5.0 4.0 3.0 2.0 1.0 0 D
Page 212 and 213:
AXIN. FORCE BALANCE ONT NORUAL BALA
Page 214 and 215:
18-12 7 I a) Initial wave formation
Page 216 and 217:
18-14 2.4 2.0 1.6 1.2 , 4.9" 4 VKI
Page 218 and 219:
Fig. 14 14 - VKI/AEA Phase 3 12 _Vi
Page 220 and 221:
I E E 24 I 2 20 w z 11 v - 16 z + S
Page 222 and 223:
18-20 - 14 H 12 Y 10 in 0 H z w la
Page 224 and 225:
19-2 low viscosity throughout the n
Page 226 and 227:
19-4 I , -30 -11 -10 Temperature, '
Page 228 and 229:
Fipm 14. Lfi LosslBos,idor? Layo- D
Page 230 and 231:
Tunnel lnvestigarion of Aerodynamic
Page 232 and 233:
RTL-2 extended. The paint that he m
Page 234 and 235:
RTD-4 Another paper in that group w
Page 236 and 237:
1. Recipient’s Reference 2. Origi
Page 238 and 239:
1 The FDP organized this meeting to
Page 240:
aGam NATO @ OTAN 7 RUE ANCELLE 9220
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