Table B.2 Properties of the International Standard Atmosphere (ISA) between sea level and 20 kmgeopotential altitude9,0009,500Standard values at altitudeP (Pa)8Alt. (m)T (K)0288.15 1 340.29500 284.90 0.9887 338.371,000 281.65 0.9774 336.431,500 278.40 0.9662 334.492,000 275.15 0.9549 332.532,500 271.90 0.9436 330.563,000 268.65 0.9306 328.583,500 265.40 0.9210326.584,000 262.15 0.9098 324.584,500 258.90 0.8985 322.56255.65 0.8872 320.53252.40 0.8759 318.48249.15 0.8647 316.436,500245.90 0.8534 314.367,000 242.65 0.8421 312.27310.17308.065,0005,5006,0007,500 239.40 0.83088,000 236.15 0.81958,500305.9333,09941,060 0.4052 0.5895 0.481238,251 0.3775 0.5566 0.454435,599 0.3513 0.5252232.90 0.80830.32670.4951229.650.7970 303.7930,742 0.3040 0.4663226.40 0.7857 301.63 28,523 0.2815 0.43890.41270.387710,0000.36390.26550.22680.1851223.150.7744299.46 26,436 0.260910,500 219.90 0.7631 297.27 24,474 0.241511,000 216.65 0.7519 295.07 22,632 0.223412,000 216.65 0.7519 295.07 19,330 0.1908 0.310813,000 216.65 0.7519 295.07 16,510 0.162914,000 216.65 0.,7519 295.07 14,101 0.139215,000 216.65 0.7519 295.07 12,044 0.1189 0.1937 0.158116,000 216.65 0.7519 295.07 10,287 0.1015 0.1654 0.135017,000 216.65 0.7519 295.07 8,786 0.0867 0.1413 0.115318,000 216.65 0.7519 295.07 7,505 0.0741 0.1207 0.098519,000 216.65 0.7519 295.07 6,410 0.0633 0.1031 0.084220,000216.65 0.7519 295.07 5,475 0.0540 0.0880 0.07180a (m/s)p (kg/m³) 0μ/1₂111.22501.1673 0.9529 0.99121.1117 0.9075 0.98231.0581 0.8638 0.97351.0065 0.8216 0.96450.9569 0.7811 0.95560.9091 0.7421 0.94650.8632 0.7055101,325 195,461 0.942189,874 0.887084,556 0.834579,4950.784674,682 0.737170,108 0.691965,764 0.649061,640 0.608357,728 0.569754,020 0.533150,506 0.4985 0.6971 0.5691 0.900647,181 0.4656 0.6597 0.538544,034 0.4346 0.6238 0.50920.90990.8191 0.66860.7768 0.63410.7361 0.60090.93750.92830.91910.25370.2167P₁A₁V₁ = P₂A₂V₂VP₂+PZ=P₁+PZP/= P₁V²C₂T₁+2=C₂T₂+0.8911 V₂ =0.88180.87240.86280.4287 0.85320.4042 0.84360.3807 0.83390.3583 0.82410.81430.33690.31650.80440.29710.7944p=pRTa = √√YRTV₁ =Advanced Aircraft Design: Conceptual Design. Analysis and Optimization of Subsonic Civil Airplanes. First Edition. Egbert Torenbeck.2013 by Tighert Torenbeek. Published 2013 by John Wiley & Sons, Lad.C₂ =h = c₂Te = c₂TP₂P₁PozP₁=0.79440.7944 M0.79442(P₁-P₂)√P[1-(A₂/A₂)²)2(Po-P)P2(Po-P)PsYRY-1-) =)"Y/(-1)17/(-1).(y + 1)²M[4YM-2(y-1)]2 (P₂)(x-1)/y0.79440.7944Y-10.7944 dp = -pvdv0.79440.7944 T₁=To [1 + x2 ¹ Mi ¹0.7944²16) *-₁]Y-2a Po-Pi1-y+2yMY+1PD P² + 1) - / - 1-7/(Y-1)P₁ = Po [(1 + ² = 1¹ M³ ] "2P₁ = Po [(1 + ² = ¹ M²³)]*-1/(-1)(4)Re, =8 =CC₁:8 ="=Ca1 2M² y+15.2xPuVxHoo√Rex0.664a=q=Re1.328REL0.37xRe2ci-ci-c|_ci0.0592Re0.074a=dc₁/daC₂Cp=9004a√M²-1C₂CoatREAR(¹1μ= arcsin(+1)/(-1)1+57.3a0/(ne,AR)1M Consider the flow of air over a small flat plate that is 5 cmlong in the flow direction and 1 m wide. The free-streamconditions correspond to standard sea level, and the flowvelocity is 120 m/s. Assuming completely turbulent flow,calculate1. The boundary layer thickness at the downstream edge(the trailing edge)2. The drag force on the plate

Given:Length of the plate, L=5 cm=0.05 mWidth of the plate, w=1 mFree steam velocity of air, V∞=120…

Consider the flow of air over a small flat plate that is 5 cm long in the flow direction and 1 m wide. The free-stream conditions correspond to standard sea level, and the flow velocity is 120 m/s. Assuming completely turbulent flow, calculate 1. The boundary layer thickness at the downstream edge (the trailing edge) 2. The drag force on the plate

Consider the flow of air over a small flat plate that is 5 cm long in the flow direction and 1 m wide. The free-stream conditions correspond to standard sea level, and the flow velocity is 120 m/s. Assuming completely turbulent flow, calculate 1. The boundary layer thickness at the downstream edge (the trailing edge) 2. The drag force on the plate

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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