S8035 for RC aerobatic 14% thick (s8035-il)
S8035 for RC aerobatic 14% thick - Selig S8035 low Reynolds number airfoil
| Details | Dat file | Parser | |
|
(s8035-il) S8035 for RC aerobatic 14% thick Selig S8035 low Reynolds number airfoil Max thickness 14% at 29.1% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S8035 for RC aerobatic 14% thick
1.00000 0.00000
0.99899 0.00005
0.99604 0.00033
0.99135 0.00097
0.98510 0.00198
0.97745 0.00329
0.96848 0.00476
0.95817 0.00629
0.94646 0.00786
0.93335 0.00955
0.91891 0.01137
0.90320 0.01332
0.88626 0.01543
0.86817 0.01770
0.84901 0.02015
0.82890 0.02276
0.80791 0.02550
0.78613 0.02833
0.76361 0.03123
0.74042 0.03418
0.71664 0.03717
0.69236 0.04015
0.66764 0.04310
0.64253 0.04601
0.61713 0.04886
0.59152 0.05161
0.56575 0.05423
0.53988 0.05671
0.51400 0.05905
0.48818 0.06120
0.46248 0.06315
0.43694 0.06488
0.41165 0.06640
0.38669 0.06767
0.36210 0.06867
0.33792 0.06939
0.31423 0.06985
0.29111 0.07002
0.26858 0.06986
0.24668 0.06940
0.22548 0.06865
0.20504 0.06758
0.18539 0.06617
0.16655 0.06445
0.14856 0.06243
0.13150 0.06012
0.11537 0.05748
0.10018 0.05456
0.08598 0.05138
0.07283 0.04794
0.06072 0.04423
0.04964 0.04028
0.03961 0.03615
0.03071 0.03186
0.02292 0.02739
0.01620 0.02279
0.01057 0.01814
0.00613 0.01352
0.00288 0.00888
0.00077 0.00428
0.00000 0.00000
0.00077 -0.00428
0.00288 -0.00888
0.00613 -0.01352
0.01057 -0.01814
0.01620 -0.02279
0.02292 -0.02739
0.03071 -0.03186
0.03961 -0.03615
0.04964 -0.04028
0.06072 -0.04423
0.07283 -0.04794
0.08598 -0.05138
0.10018 -0.05456
0.11537 -0.05748
0.13150 -0.06012
0.14856 -0.06243
0.16655 -0.06445
0.18539 -0.06617
0.20504 -0.06758
0.22548 -0.06865
0.24668 -0.06940
0.26858 -0.06986
0.29111 -0.07002
0.31423 -0.06985
0.33792 -0.06939
0.36210 -0.06867
0.38669 -0.06767
0.41165 -0.06640
0.43694 -0.06488
0.46248 -0.06315
0.48818 -0.06120
0.51400 -0.05905
0.53988 -0.05671
0.56575 -0.05423
0.59152 -0.05161
0.61713 -0.04886
0.64253 -0.04601
0.66764 -0.04310
0.69236 -0.04015
0.71664 -0.03717
0.74042 -0.03418
0.76361 -0.03123
0.78613 -0.02833
0.80791 -0.02550
0.82890 -0.02276
0.84901 -0.02015
0.86817 -0.01770
0.88626 -0.01543
0.90320 -0.01332
0.91891 -0.01137
0.93335 -0.00955
0.94646 -0.00786
0.95817 -0.00629
0.96848 -0.00476
0.97745 -0.00329
0.98510 -0.00198
0.99135 -0.00097
0.99604 -0.00033
0.99899 -0.00005
1.00000 0.00000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for S8035 for RC aerobatic 14% thick (s8035-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8035-il | 50,000 | 9 | 24.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 50,000 | 5 | 27.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 100,000 | 9 | 38.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 100,000 | 5 | 39.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 200,000 | 9 | 52 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 200,000 | 5 | 51.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 500,000 | 9 | 70.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 500,000 | 5 | 66.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 1,000,000 | 9 | 83.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 1,000,000 | 5 | 78.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||