SA7035 (sa7035-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SA7035 (sa7035-il) Reynolds number: 500,000 Max Cl/Cd: 87.18 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7035-il-500000-n5.txt Download as CSV file: xf-sa7035-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4084 0.08516 0.08292 -0.0297 1.0000 0.0069
-8.250 -0.3549 0.05950 0.05748 -0.0360 1.0000 0.0049
-8.000 -0.3675 0.05461 0.05264 -0.0373 1.0000 0.0049
-7.750 -0.4478 0.06566 0.06362 -0.0374 0.9993 0.0049
-7.500 -0.4321 0.05486 0.05273 -0.0533 0.9887 0.0047
-7.250 -0.4155 0.04450 0.04209 -0.0639 0.9812 0.0046
-7.000 -0.4002 0.03588 0.03306 -0.0692 0.9728 0.0044
-6.750 -0.3878 0.02747 0.02398 -0.0712 0.9633 0.0042
-6.500 -0.3686 0.02219 0.01802 -0.0716 0.9566 0.0041
-6.250 -0.3487 0.01919 0.01449 -0.0708 0.9484 0.0042
-6.000 -0.3249 0.01705 0.01195 -0.0703 0.9422 0.0044
-5.750 -0.3015 0.01563 0.01024 -0.0695 0.9343 0.0045
-5.500 -0.2765 0.01455 0.00894 -0.0689 0.9281 0.0048
-5.250 -0.2517 0.01369 0.00791 -0.0683 0.9205 0.0049
-5.000 -0.2272 0.01264 0.00670 -0.0676 0.9140 0.0052
-4.750 -0.2024 0.01190 0.00586 -0.0670 0.9060 0.0056
-4.500 -0.1766 0.01141 0.00528 -0.0666 0.8986 0.0060
-4.250 -0.1505 0.01104 0.00485 -0.0662 0.8898 0.0067
-4.000 -0.1243 0.01069 0.00442 -0.0658 0.8808 0.0075
-3.750 -0.0981 0.01025 0.00388 -0.0653 0.8713 0.0078
-3.500 -0.0716 0.00981 0.00335 -0.0649 0.8610 0.0083
-3.250 -0.0449 0.00946 0.00289 -0.0645 0.8505 0.0095
-3.000 -0.0179 0.00919 0.00254 -0.0642 0.8396 0.0122
-2.750 0.0088 0.00885 0.00222 -0.0639 0.8277 0.0288
-2.500 0.0353 0.00850 0.00200 -0.0637 0.8146 0.0709
-2.250 0.0614 0.00804 0.00180 -0.0635 0.8005 0.1540
-2.000 0.0876 0.00765 0.00165 -0.0633 0.7851 0.2411
-1.750 0.1144 0.00745 0.00153 -0.0631 0.7686 0.2946
-1.500 0.1410 0.00724 0.00142 -0.0629 0.7515 0.3582
-1.250 0.1675 0.00706 0.00134 -0.0627 0.7341 0.4237
-1.000 0.1938 0.00686 0.00130 -0.0624 0.7171 0.5007
-0.750 0.2200 0.00668 0.00128 -0.0621 0.6996 0.5796
-0.500 0.2462 0.00657 0.00126 -0.0617 0.6814 0.6397
-0.250 0.2723 0.00652 0.00126 -0.0612 0.6625 0.6884
0.000 0.2982 0.00648 0.00127 -0.0607 0.6430 0.7346
0.250 0.3237 0.00644 0.00130 -0.0601 0.6239 0.7814
0.500 0.3482 0.00641 0.00133 -0.0591 0.6054 0.8296
0.750 0.3716 0.00640 0.00137 -0.0579 0.5878 0.8800
1.000 0.3970 0.00643 0.00140 -0.0570 0.5698 0.9297
1.250 0.4307 0.00652 0.00142 -0.0582 0.5499 0.9662
1.500 0.4675 0.00664 0.00144 -0.0602 0.5292 0.9927
1.750 0.4965 0.00679 0.00148 -0.0605 0.5081 1.0000
2.000 0.5223 0.00697 0.00155 -0.0602 0.4871 1.0000
2.250 0.5483 0.00714 0.00163 -0.0598 0.4665 1.0000
2.500 0.5744 0.00732 0.00172 -0.0595 0.4480 1.0000
2.750 0.6008 0.00749 0.00181 -0.0593 0.4300 1.0000
3.000 0.6270 0.00768 0.00192 -0.0590 0.4112 1.0000
3.250 0.6531 0.00789 0.00206 -0.0588 0.3927 1.0000
3.500 0.6794 0.00809 0.00219 -0.0585 0.3739 1.0000
3.750 0.7054 0.00832 0.00234 -0.0583 0.3534 1.0000
4.000 0.7313 0.00857 0.00251 -0.0580 0.3327 1.0000
4.250 0.7574 0.00881 0.00269 -0.0578 0.3139 1.0000
4.500 0.7831 0.00907 0.00288 -0.0575 0.2949 1.0000
4.750 0.8090 0.00933 0.00308 -0.0572 0.2777 1.0000
5.000 0.8349 0.00958 0.00331 -0.0570 0.2615 1.0000
5.250 0.8605 0.00987 0.00354 -0.0567 0.2427 1.0000
5.500 0.8856 0.01021 0.00380 -0.0564 0.2228 1.0000
5.750 0.9106 0.01056 0.00408 -0.0560 0.2009 1.0000
6.000 0.9353 0.01095 0.00438 -0.0556 0.1804 1.0000
6.250 0.9601 0.01131 0.00470 -0.0553 0.1626 1.0000
6.500 0.9847 0.01168 0.00504 -0.0549 0.1466 1.0000
6.750 1.0088 0.01211 0.00540 -0.0544 0.1295 1.0000
7.000 1.0330 0.01252 0.00578 -0.0540 0.1152 1.0000
7.250 1.0569 0.01297 0.00620 -0.0535 0.0997 1.0000
7.500 1.0796 0.01353 0.00667 -0.0529 0.0805 1.0000
7.750 1.1020 0.01410 0.00717 -0.0523 0.0645 1.0000
8.000 1.1245 0.01464 0.00768 -0.0516 0.0524 1.0000
8.250 1.1466 0.01522 0.00823 -0.0509 0.0417 1.0000
8.500 1.1684 0.01580 0.00880 -0.0502 0.0338 1.0000
8.750 1.1905 0.01633 0.00939 -0.0495 0.0285 1.0000
9.000 1.2114 0.01697 0.01004 -0.0486 0.0233 1.0000
9.250 1.2324 0.01755 0.01067 -0.0478 0.0193 1.0000
9.500 1.2521 0.01825 0.01140 -0.0467 0.0153 1.0000
9.750 1.2711 0.01898 0.01215 -0.0457 0.0122 1.0000
10.000 1.2897 0.01970 0.01293 -0.0445 0.0101 1.0000
10.250 1.3076 0.02044 0.01374 -0.0433 0.0087 1.0000
10.500 1.3230 0.02136 0.01472 -0.0418 0.0074 1.0000
10.750 1.3395 0.02208 0.01555 -0.0404 0.0065 1.0000
11.000 1.3537 0.02287 0.01642 -0.0387 0.0056 1.0000
11.250 1.3637 0.02380 0.01743 -0.0364 0.0050 1.0000
11.500 1.3717 0.02486 0.01859 -0.0339 0.0045 1.0000
11.750 1.3810 0.02584 0.01969 -0.0318 0.0040 1.0000
12.000 1.3885 0.02699 0.02096 -0.0297 0.0038 1.0000
12.250 1.3955 0.02821 0.02228 -0.0277 0.0035 1.0000
12.500 1.4004 0.02965 0.02383 -0.0258 0.0031 1.0000
12.750 1.4018 0.03146 0.02575 -0.0238 0.0029 1.0000
13.000 1.4022 0.03347 0.02790 -0.0222 0.0027 1.0000
13.250 1.4044 0.03543 0.03000 -0.0210 0.0026 1.0000
13.500 1.4046 0.03772 0.03246 -0.0200 0.0024 1.0000
13.750 1.4013 0.04054 0.03543 -0.0194 0.0024 1.0000
14.000 1.3989 0.04349 0.03853 -0.0193 0.0022 1.0000
14.250 1.3961 0.04668 0.04186 -0.0195 0.0020 1.0000
14.500 1.3894 0.05058 0.04592 -0.0203 0.0020 1.0000
14.750 1.3832 0.05467 0.05015 -0.0215 0.0019 1.0000
15.000 1.3718 0.05980 0.05545 -0.0233 0.0020 1.0000
15.250 1.3611 0.06513 0.06093 -0.0256 0.0019 1.0000
15.500 1.3511 0.07059 0.06653 -0.0281 0.0018 1.0000
15.750 1.3359 0.07725 0.07336 -0.0314 0.0019 1.0000
16.000 1.3218 0.08395 0.08020 -0.0348 0.0018 1.0000
16.250 1.3021 0.09200 0.08843 -0.0390 0.0019 1.0000
16.500 1.2852 0.09978 0.09636 -0.0432 0.0018 1.0000
16.750 1.2665 0.10816 0.10488 -0.0477 0.0018 1.0000
17.000 1.2476 0.11684 0.11370 -0.0524 0.0019 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SA7035 (sa7035-il)