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1ozturkbe committed Mar 13, 2017
2 parents fa8e0cb + 4552e5e commit f4b3f8a
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20 changes: 20 additions & 0 deletions Tail Fits/gen_tail_polar.sh
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NACA=$1
POLARFILE=naca$1.cl0.Re$2k.pol

if [ -f $POLARFILE ] ; then
echo "yes"
rm $POLARFILE
fi

xfoil << EOF
naca $1
oper
v $2e3
pacc
$POLARFILE
iter 200
cl 0.0
quit
EOF
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re3500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 3.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00354 0.00023 0.0000 0.6600 0.6600
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re4000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 4.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00371 0.00022 0.0000 0.6122 0.6122
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re4500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 4.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00386 0.00022 0.0000 0.5712 0.5712
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re5000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 5.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00398 0.00022 0.0000 0.5366 0.5366
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re5500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 5.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00407 0.00022 0.0000 0.5067 0.5067
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re6000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 6.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00416 0.00022 0.0000 0.4796 0.4796
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re6500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 6.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00423 0.00022 0.0000 0.4555 0.4555
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re7000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 7.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00429 0.00023 0.0000 0.4342 0.4342
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re7500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 7.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00434 0.00022 0.0000 0.4157 0.4157
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re8000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 8.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00438 0.00023 0.0000 0.3987 0.3987
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re8500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 8.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00442 0.00023 0.0000 0.3826 0.3826
13 changes: 13 additions & 0 deletions Tail Fits/naca0005.cl0.Re9000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0005

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 9.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00446 0.00023 0.0000 0.3674 0.3674
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re3500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 3.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00431 0.00041 0.0000 0.5631 0.5631
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re4000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 4.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00438 0.00040 0.0000 0.5321 0.5321
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re4500k.pol
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@@ -0,0 +1,13 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 4.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00444 0.00040 0.0000 0.5051 0.5051
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re5000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 5.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00448 0.00039 0.0000 0.4829 0.4829
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re5500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 5.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00453 0.00040 0.0000 0.4618 0.4618
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re6000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 6.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00457 0.00039 0.0000 0.4437 0.4437
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re6500k.pol
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@@ -0,0 +1,13 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 6.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00460 0.00039 0.0000 0.4272 0.4272
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re7000k.pol
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@@ -0,0 +1,13 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 7.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00462 0.00039 0.0000 0.4126 0.4126
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re7500k.pol
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@@ -0,0 +1,13 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 7.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00465 0.00039 0.0000 0.3991 0.3991
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re8000k.pol
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@@ -0,0 +1,13 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 8.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00467 0.00039 0.0000 0.3863 0.3863
12 changes: 12 additions & 0 deletions Tail Fits/naca0008.cl0.Re8500k.pol
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@@ -0,0 +1,12 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 8.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
13 changes: 13 additions & 0 deletions Tail Fits/naca0008.cl0.Re9000k.pol
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@@ -0,0 +1,13 @@

XFOIL Version 6.97

Calculated polar for: NACA 0008

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 9.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00471 0.00040 0.0000 0.3640 0.3640
13 changes: 13 additions & 0 deletions Tail Fits/naca0009.cl0.Re3500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0009

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 3.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00452 0.00048 0.0000 0.5407 0.5407
13 changes: 13 additions & 0 deletions Tail Fits/naca0009.cl0.Re4000k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0009

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 4.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00456 0.00047 0.0000 0.5135 0.5135
13 changes: 13 additions & 0 deletions Tail Fits/naca0009.cl0.Re4500k.pol
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XFOIL Version 6.97

Calculated polar for: NACA 0009

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 4.500 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.000 0.0000 0.00462 0.00046 0.0000 0.4890 0.4890
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