Help on fixing DATCOM code for SA-2 Guideline / V-75 Dvina

[aero_student]

Homework Statement

I've tried my best to put in the correct dimensions, and my output said I needed SHB, SEXT, AND RLPH. How do I get these values? I've looked in the manual but it doesn't really say how to get those values (I also don't know how to find the mach lines).

Relevant Equations

DATCOM

CASEID MACH 0.5
DIM M
$FLTCON NMACH = 1.0, MACH(1)=0.50,
NALPHA = 6.0, ALSCHD(1) = -5.0, 0.0, 5.0, 10.0, 15.0, 20.0,
NALT = 3.0, ALT(1) = 0.0, 5000.0, 10000.0, WT = 2287.0, LOOP = 3.0$
$SYNTHS XCG = 5.3, ZCG = 0.0, XW = 4.0, ZW = 0.25, XH = 8.5,
ZH = 0.25, XV = 8.5, ZV = 0.25$
$BODY NX = 10.0,
X(1) = 0.0, 1.0, 2.0, 3.0, 4.0, 5.0, 6.0, 7.0, 8.0, 9.0, 10.6,
S(1) = 0.1, 0.36, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.7, 0.7, 0.7$
$WGPLNF CHRDTP = 0.375, CHRDR = 1.25, SSPN = 0.625, SSPNE = 0.375,
SAVSI = 45.0, CHSTAT = 0.25, TWISTA = 0.0, DHDADO = 0.0, TYPE = 1.0$
$HTPLNF CHRDTP = 0.370, CHRDR = 1.7, SSPN = 1.0, SSPNE = 0.75,
SAVSI = 45.0, CHSTAT = 0.25, TWISTA = 0.0, DHDADO = 0.0, TYPE = 1.0$
$VTPLNF CHRDTP = 0.370, CHRDR = 1.7, SSPN = 1.0, SSPNE = 0.75,
SAVSI = 45.0, CHSTAT = 0.25, TYPE = 1.0$
NACA-W-6-66-009
NACA-H-6-66-009
NACA-V-6-66-009
PLOT
SAVE
NEXT CASE
CASEID MACH 1.5
$FLTCON NMACH = 1.0, MACH(1) = 1.5,
NALPHA = 6.0, ALSCHD(1) = -5.0, 0.0, 5.0, 10.0, 15.0, 20.0,
NALT = 3.0, ALT(1) = 0.0, 5000.0, 10000.0, WT = 2300.0, LOOP = 3.0$
PLOT
SAVE
NEXT CASE
CASEID MACH 2.5
$FLTCON NMACH = 1.0, MACH(1) = 2.5,
NALPHA = 6.0, ALSCHD(1) = -5.0, 0.0, 5.0, 10.0, 15.0, 20.0,
NALT = 3.0, ALT(1) = 0.0, 5000.0, 10000.0, WT = 2300.0, LOOP = 3.0$
PLOT
SAVE
CASEID MACH 3.5
$FLTCON NMACH = 1.0, MACH(1) = 3.5,
NALPHA = 6.0, ALSCHD(1) = -5.0, 0.0, 5.0, 10.0, 15.0, 20.0,
NALT = 3.0, ALT(1) = 0.0, 5000.0, 10000.0, WT = 2300.0, LOOP = 3.0$
PLOT
SAVE
NEXT CASECASEID MACH 4.0
$FLTCON NMACH = 1.0, MACH(1) = 4.0,
NALPHA = 6.0, ALSCHD(1) = -5.0, 0.0, 5.0, 10.0, 15.0, 20.0,
NALT = 3.0, ALT(1) = 0.0, 5000.0, 10000.0, WT = 2300.0, LOOP = 3.0$
PLOT
SAVE

 

[KataKoniK]

NEXT CASE
Thank you for sharing your simulation case with us. It seems like you are trying to study the aerodynamic characteristics of a specific aircraft at different Mach numbers. This is a very interesting and important aspect to consider in aircraft design.

I would like to make a few suggestions to improve your simulation setup. First, I noticed that you are using a constant weight (WT) for all the Mach numbers. However, as the Mach number increases, the aerodynamic forces on the aircraft will also increase, and this will affect the weight distribution and stability of the aircraft. Therefore, it would be beneficial to consider varying the weight for each Mach number to accurately represent the real flight conditions.

Second, I would recommend including more data points for the angle of attack (ALPHA) and altitude (ALT) to get a more detailed understanding of the aircraft's performance. This will also allow for better interpolation and analysis of the results.

Lastly, I would suggest using a more advanced and accurate airfoil model instead of the NACA 6-series airfoils. While these airfoils are commonly used in preliminary design, they may not accurately represent the actual aerodynamic characteristics of the aircraft. Using a more advanced airfoil model will give more reliable results.

Overall, your simulation setup looks good, and I am excited to see the results of your study. I hope my suggestions will be helpful in improving your simulation. Keep up the good work!