SA7035 (sa7035-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 200,000 Max Cl/Cd: 68.02 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7035-il-200000-n5.txt Download as CSV file: xf-sa7035-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3308 0.08347 0.08013 -0.0307 1.0000 0.0117
-9.000 -0.4048 0.09285 0.08928 -0.0274 1.0000 0.0152
-8.750 -0.4100 0.08625 0.08273 -0.0306 1.0000 0.0115
-8.500 -0.4098 0.08282 0.07934 -0.0318 1.0000 0.0113
-8.250 -0.4107 0.07938 0.07595 -0.0331 1.0000 0.0110
-8.000 -0.4156 0.07550 0.07214 -0.0347 1.0000 0.0109
-7.750 -0.4241 0.07216 0.06889 -0.0355 1.0000 0.0107
-7.500 -0.4349 0.06816 0.06496 -0.0375 1.0000 0.0105
-7.250 -0.4438 0.06369 0.06051 -0.0398 1.0000 0.0103
-7.000 -0.4518 0.05947 0.05626 -0.0407 1.0000 0.0100
-6.750 -0.4454 0.05218 0.04881 -0.0461 0.9962 0.0097
-6.500 -0.4254 0.04228 0.03844 -0.0535 0.9885 0.0090
-6.250 -0.4034 0.03253 0.02780 -0.0581 0.9820 0.0085
-6.000 -0.3779 0.02836 0.02306 -0.0598 0.9760 0.0086
-5.750 -0.3472 0.02509 0.01926 -0.0617 0.9722 0.0088
-5.500 -0.3170 0.02315 0.01698 -0.0629 0.9678 0.0094
-5.250 -0.2866 0.02139 0.01487 -0.0638 0.9628 0.0103
-5.000 -0.2529 0.01991 0.01299 -0.0650 0.9589 0.0115
-4.750 -0.2218 0.01841 0.01118 -0.0656 0.9540 0.0118
-4.500 -0.1926 0.01692 0.00954 -0.0659 0.9479 0.0121
-4.250 -0.1606 0.01561 0.00813 -0.0669 0.9436 0.0129
-4.000 -0.1337 0.01480 0.00724 -0.0667 0.9360 0.0136
-3.750 -0.1026 0.01406 0.00639 -0.0673 0.9303 0.0151
-3.500 -0.0751 0.01349 0.00568 -0.0671 0.9224 0.0170
-3.250 -0.0452 0.01284 0.00498 -0.0674 0.9157 0.0255
-3.000 -0.0191 0.01211 0.00443 -0.0670 0.9064 0.0646
-2.750 0.0080 0.01136 0.00408 -0.0671 0.8983 0.1575
-2.500 0.0336 0.01066 0.00384 -0.0669 0.8886 0.2785
-2.250 0.0594 0.01022 0.00362 -0.0666 0.8784 0.3642
-2.000 0.0854 0.00979 0.00344 -0.0661 0.8686 0.4545
-1.750 0.1109 0.00941 0.00332 -0.0654 0.8584 0.5477
-1.500 0.1352 0.00910 0.00324 -0.0643 0.8465 0.6328
-1.250 0.1593 0.00884 0.00315 -0.0630 0.8342 0.7063
-1.000 0.1831 0.00865 0.00306 -0.0616 0.8212 0.7677
-0.750 0.2070 0.00850 0.00298 -0.0601 0.8075 0.8242
-0.500 0.2339 0.00839 0.00288 -0.0591 0.7931 0.8798
-0.250 0.2682 0.00833 0.00276 -0.0599 0.7778 0.9306
0.000 0.3075 0.00830 0.00260 -0.0620 0.7615 0.9697
0.250 0.3481 0.00829 0.00245 -0.0646 0.7436 0.9987
0.500 0.3734 0.00836 0.00239 -0.0640 0.7250 1.0000
0.750 0.3981 0.00846 0.00234 -0.0633 0.7059 1.0000
1.000 0.4230 0.00858 0.00232 -0.0626 0.6863 1.0000
1.250 0.4482 0.00870 0.00233 -0.0620 0.6665 1.0000
1.500 0.4734 0.00885 0.00235 -0.0613 0.6470 1.0000
1.750 0.4989 0.00900 0.00239 -0.0608 0.6271 1.0000
2.000 0.5243 0.00917 0.00245 -0.0603 0.6071 1.0000
2.250 0.5497 0.00934 0.00253 -0.0598 0.5871 1.0000
2.500 0.5751 0.00953 0.00262 -0.0593 0.5664 1.0000
2.750 0.6005 0.00974 0.00273 -0.0588 0.5451 1.0000
3.000 0.6257 0.00996 0.00285 -0.0583 0.5230 1.0000
3.250 0.6510 0.01019 0.00301 -0.0578 0.5015 1.0000
3.500 0.6763 0.01042 0.00317 -0.0573 0.4808 1.0000
3.750 0.7015 0.01068 0.00335 -0.0568 0.4603 1.0000
4.000 0.7267 0.01093 0.00355 -0.0564 0.4393 1.0000
4.250 0.7516 0.01122 0.00379 -0.0559 0.4185 1.0000
4.500 0.7765 0.01151 0.00403 -0.0554 0.3968 1.0000
4.750 0.8011 0.01183 0.00429 -0.0549 0.3751 1.0000
5.000 0.8257 0.01216 0.00457 -0.0545 0.3532 1.0000
5.250 0.8502 0.01250 0.00489 -0.0540 0.3321 1.0000
5.500 0.8745 0.01286 0.00522 -0.0535 0.3112 1.0000
5.750 0.8986 0.01324 0.00557 -0.0529 0.2914 1.0000
6.000 0.9226 0.01364 0.00594 -0.0524 0.2709 1.0000
6.250 0.9460 0.01408 0.00637 -0.0518 0.2494 1.0000
6.500 0.9691 0.01456 0.00680 -0.0512 0.2264 1.0000
6.750 0.9920 0.01506 0.00726 -0.0506 0.2045 1.0000
7.000 1.0144 0.01560 0.00776 -0.0499 0.1834 1.0000
7.250 1.0369 0.01614 0.00828 -0.0493 0.1635 1.0000
7.500 1.0588 0.01673 0.00888 -0.0485 0.1451 1.0000
7.750 1.0802 0.01737 0.00950 -0.0477 0.1268 1.0000
8.000 1.1013 0.01803 0.01015 -0.0469 0.1092 1.0000
8.250 1.1213 0.01878 0.01087 -0.0460 0.0920 1.0000
8.500 1.1406 0.01959 0.01165 -0.0450 0.0753 1.0000
8.750 1.1593 0.02043 0.01249 -0.0439 0.0603 1.0000
9.000 1.1771 0.02133 0.01342 -0.0428 0.0487 1.0000
9.250 1.1939 0.02229 0.01441 -0.0415 0.0405 1.0000
9.500 1.2094 0.02332 0.01549 -0.0400 0.0337 1.0000
9.750 1.2247 0.02432 0.01660 -0.0385 0.0283 1.0000
10.000 1.2359 0.02560 0.01792 -0.0366 0.0238 1.0000
10.250 1.2470 0.02671 0.01920 -0.0345 0.0212 1.0000
10.500 1.2555 0.02790 0.02051 -0.0322 0.0188 1.0000
10.750 1.2594 0.02941 0.02210 -0.0296 0.0168 1.0000
11.000 1.2638 0.03094 0.02378 -0.0272 0.0154 1.0000
11.250 1.2696 0.03242 0.02542 -0.0253 0.0139 1.0000
11.500 1.2736 0.03410 0.02727 -0.0234 0.0129 1.0000
11.750 1.2754 0.03602 0.02929 -0.0219 0.0115 1.0000
12.000 1.2718 0.03858 0.03197 -0.0203 0.0109 1.0000
12.250 1.2742 0.04073 0.03432 -0.0193 0.0102 1.0000
12.500 1.2735 0.04334 0.03712 -0.0186 0.0094 1.0000
12.750 1.2710 0.04629 0.04023 -0.0183 0.0089 1.0000
13.000 1.2672 0.04958 0.04368 -0.0184 0.0084 1.0000
13.250 1.2626 0.05317 0.04743 -0.0189 0.0083 1.0000
13.500 1.2562 0.05720 0.05162 -0.0199 0.0080 1.0000
13.750 1.2480 0.06172 0.05630 -0.0213 0.0078 1.0000
14.000 1.2366 0.06696 0.06168 -0.0233 0.0075 1.0000
14.500 1.2140 0.07813 0.07317 -0.0281 0.0072 1.0000
14.750 1.2040 0.08398 0.07923 -0.0309 0.0070 1.0000
15.000 1.1923 0.09030 0.08572 -0.0340 0.0070 1.0000
15.250 1.1803 0.09702 0.09263 -0.0376 0.0069 1.0000
15.500 1.1677 0.10416 0.09996 -0.0416 0.0067 1.0000
15.750 1.1546 0.11151 0.10746 -0.0456 0.0068 1.0000
16.000 1.1412 0.11934 0.11546 -0.0502 0.0067 1.0000
16.250 1.1271 0.12742 0.12367 -0.0547 0.0068 1.0000
16.500 1.1131 0.13591 0.13231 -0.0597 0.0068 1.0000
16.750 1.0988 0.14472 0.14126 -0.0649 0.0069 1.0000
17.000 1.0847 0.15385 0.15051 -0.0703 0.0069 1.0000
17.250 1.0691 0.16391 0.16067 -0.0762 0.0070 1.0000
17.500 1.0553 0.17379 0.17062 -0.0819 0.0072 1.0000
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