2. Please calculate the lift force, the optimal angle of attack, and drag force for the airfoil listed in the attached c

Post by **answerhappygod** » Mon May 16, 2022 5:46 am

: 2 Please Calculate The Lift Force The Optimal Angle Of Attack And Drag Force For The Airfoil Listed In The Attached C 1 (23.37 KiB) Viewed 39 times

The angle of attack has to be calculated.

: 2 Please Calculate The Lift Force The Optimal Angle Of Attack And Drag Force For The Airfoil Listed In The Attached C 2 (189.68 KiB) Viewed 39 times

2. Please calculate the lift force, the optimal angle of attack, and drag force for the airfoil listed in the attached chart from NACA Report 572, (24-0-0). The chord length is 1 m, the span is 15 m, and the air velocity is 120 m/s. The total weight of the plane is 5,000 lbf.
512 REPORT NO. 672 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS Need section des LUF .026 percentar 5.0243 od from fest calculated 016 Effective RR 800 000 Ylecile R Mod2 L203.800.000 or 28 2.022 2.2.44 7.020 2.0 ,40 La . 8.014 38 L4 .28 al 12.2496.010 LO 8.20 8.088 .005 -$$.12 2.000 4.08 .002 24 20 16 -83.16 Motio of 1 to drag, L/D 0 Airfoit 24-0-0 Vel/sec.): 69.9 Size: 50 sg. in area, in San Pres.farhdot RA090001-2 Arrow: 24-0-0 Where the LRAL Test: War 773 RN (effective) & 160.000 Corrected for funnewall effect. Do 9.27-34 Test: V.D.T. 1173 -16 124 0 4 8 12 16 20 24 28 32 02 + 6 8 20 22 24 26 Angle of flock, a (degrees) referred to root chord LIH coefficient None 13 - N... 1. *- wirfell CMS Moment coef. 8 30 Ratio of w to drag L/D Post wise .026 coor ZWHOW 6.024 3.022 2.2.44 20 Creative RR 8.180 m 42,0 40 28 .36 016 Effective RN 3.000.000, LLI ராகம் 16 22.014 28 Sape of war weer 24 287 012 24 0.010) 20 LO 8.20 8.000 16 12 .69.12 .004 .4 .0 .002) 2.04 0 0 Airfoil 24-15-0 Vol.89.8 Size: 150. in oreg din Span Pressthal 20.3 R100 0001-2 Where tested EMAL. Tas Box 7/74 Corrected for Anal wall alleen 4 13 16 0826 20 24 28 32 Angle of affock (degrees) referred to root chord TORE 14.- N. A... 56-LS- Aterren Airfoil -15-0 RN feticelive) & 182.000 Dore: 9-3 Tel: VOX/174 02 .4 6 8 10 2 14 16 Liff coefficient
-20 10 0 Per cent of chord 6068 -10 0 20 40 60 80 100 Per cent of chord Sto. Upr. zwr. 0 0 0 125 2.3671-2.367 2513.269 -3.268 504.443-4.443 7.5 5.250 -5.250 105.853-5.853 15 6687-6.687 20 7.172-7.172 25 7.427-7.427 30 7.502- 7.502 40 7.254-7.254 50 6.618-6.618 60 5.704 -5.704 704.580-4.580 80 3.279-3279 90 1.810 -1.810 95 1.005 - 1,000 100(.158) (-158) Jogo 0 L.E.Rod: 248 .44 2.0 .40 1.8 .36 1.6.32 Gall 0 1.4 .28 24 20 CA! 1.25 .24 20 40 Drag coefficient, Co 1.0 LD LUA c.p. in per cent of chord (from forward end of chord) 60 Lift coefficient, C 80 Ratio of lift to drag, L/D 128 .6 .12 8 100 .08 .2 .04 VEL o 0 0 Airfoil: N.A.C.A.0015 R.N:3,209,000 Size: 5'x 30" Vel. (ft./sec.): 68.41-2 Pres.(st'nd.atm: 21.0 Date: 12-9-31 Where tested:LMAL. Test: V.D.T. 728 Corrected for tunnel wall effect .4 0 4 8 12 16 20 24 28 32 Angle of attack, a (degrees) -8 -8 -4