Aerowerx
Well-Known Member
I was kicking around the idea of a BWB aircraft, and hand sketched up an airfoil for the center, where the pilot and passenger would sit.
The requirements are that it be 4 feet thick and short enough chord to be built in my garage (less than 19 feet). This will be a tandem seat pusher, and I would like to have good visibility out the front and sides, at least for the pilot.
When I tried it on XFLR5, the program choked on it and never converged. Do I not have enought points, or is there something else wrong?
:ermm:
What airfoils would be recommended for the center of a small (LSA size) BWB? And yes, I have seen the Atlantica---very close to what I have in mind.
The points I used:
BWB000
1.0000 0.0000
0.9333 0.05789
0.86667 0.1000
0.8000 0.11579
0.7333 0.14211
0.6667 0.15789
0.6000 0.15789
0.5333 0.15789
0.4666 0.15789
0.4000 0.16105
0.3333 0.15263
0.2667 0.14316
0.2000 0.12895
001333 0.10520
0.0667 0.07368
0.0000 0.0000
0.0667 -0.05263
0.1333 -0.08421
0.2000 -0.1000
0.2667 -0.1000
0.3333 -0.1000
0.40000 -0.1000
0.4667 -0.1000
0.5333 -0.1000
0.6000 -0.09474
0.6667 -0.08947
0.7333 -0.08421
0.8000 -0.07368
0.8667 -0.05263
0.9333 -0.03158
1.0000 0.0000
The requirements are that it be 4 feet thick and short enough chord to be built in my garage (less than 19 feet). This will be a tandem seat pusher, and I would like to have good visibility out the front and sides, at least for the pilot.
When I tried it on XFLR5, the program choked on it and never converged. Do I not have enought points, or is there something else wrong?
:ermm:
What airfoils would be recommended for the center of a small (LSA size) BWB? And yes, I have seen the Atlantica---very close to what I have in mind.
The points I used:
BWB000
1.0000 0.0000
0.9333 0.05789
0.86667 0.1000
0.8000 0.11579
0.7333 0.14211
0.6667 0.15789
0.6000 0.15789
0.5333 0.15789
0.4666 0.15789
0.4000 0.16105
0.3333 0.15263
0.2667 0.14316
0.2000 0.12895
001333 0.10520
0.0667 0.07368
0.0000 0.0000
0.0667 -0.05263
0.1333 -0.08421
0.2000 -0.1000
0.2667 -0.1000
0.3333 -0.1000
0.40000 -0.1000
0.4667 -0.1000
0.5333 -0.1000
0.6000 -0.09474
0.6667 -0.08947
0.7333 -0.08421
0.8000 -0.07368
0.8667 -0.05263
0.9333 -0.03158
1.0000 0.0000
