S6061 9% (s6061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S6061 9% (s6061-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.72 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6061-il-1000000-n5.txt Download as CSV file: xf-s6061-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6061 9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5468 0.08486 0.08329 -0.0162 1.0000 0.0032
-9.500 -0.5559 0.07877 0.07723 -0.0197 1.0000 0.0031
-9.250 -0.5653 0.07263 0.07111 -0.0236 1.0000 0.0032
-9.000 -0.5870 0.06408 0.06262 -0.0311 1.0000 0.0032
-8.750 -0.6172 0.05298 0.05140 -0.0396 1.0000 0.0030
-8.500 -0.6689 0.03362 0.03137 -0.0422 1.0000 0.0030
-8.250 -0.6590 0.02600 0.02303 -0.0445 0.9741 0.0030
-8.000 -0.6396 0.02291 0.01954 -0.0447 0.9585 0.0031
-7.750 -0.6219 0.02064 0.01692 -0.0438 0.9436 0.0031
-7.500 -0.6020 0.01913 0.01515 -0.0429 0.9310 0.0032
-7.250 -0.5808 0.01780 0.01357 -0.0420 0.9199 0.0033
-7.000 -0.5568 0.01723 0.01286 -0.0415 0.9100 0.0034
-6.750 -0.5333 0.01637 0.01182 -0.0409 0.9001 0.0034
-6.500 -0.5104 0.01506 0.01027 -0.0402 0.8902 0.0035
-6.250 -0.4874 0.01368 0.00866 -0.0395 0.8810 0.0035
-6.000 -0.4639 0.01250 0.00725 -0.0388 0.8720 0.0036
-5.750 -0.4393 0.01161 0.00621 -0.0383 0.8626 0.0037
-5.500 -0.4140 0.01090 0.00538 -0.0379 0.8537 0.0039
-5.000 -0.3616 0.00999 0.00429 -0.0373 0.8355 0.0043
-4.750 -0.3349 0.00964 0.00386 -0.0371 0.8268 0.0047
-4.500 -0.3080 0.00933 0.00345 -0.0369 0.8174 0.0050
-4.250 -0.2809 0.00904 0.00310 -0.0367 0.8081 0.0054
-4.000 -0.2537 0.00880 0.00278 -0.0366 0.7989 0.0057
-3.750 -0.2263 0.00860 0.00251 -0.0365 0.7891 0.0060
-3.500 -0.1989 0.00836 0.00220 -0.0364 0.7794 0.0069
-3.250 -0.1714 0.00816 0.00193 -0.0363 0.7697 0.0086
-3.000 -0.1438 0.00800 0.00172 -0.0362 0.7594 0.0117
-2.750 -0.1165 0.00774 0.00152 -0.0361 0.7485 0.0311
-2.500 -0.0892 0.00752 0.00137 -0.0360 0.7371 0.0581
-2.250 -0.0619 0.00730 0.00122 -0.0360 0.7249 0.0922
-2.000 -0.0348 0.00702 0.00110 -0.0360 0.7123 0.1471
-1.750 -0.0080 0.00670 0.00099 -0.0360 0.6995 0.2228
-1.500 0.0193 0.00652 0.00090 -0.0360 0.6867 0.2703
-1.250 0.0464 0.00627 0.00082 -0.0360 0.6738 0.3417
-1.000 0.0737 0.00611 0.00077 -0.0360 0.6606 0.3944
-0.750 0.1009 0.00591 0.00072 -0.0360 0.6472 0.4603
-0.500 0.1280 0.00573 0.00069 -0.0359 0.6332 0.5277
-0.250 0.1550 0.00557 0.00068 -0.0359 0.6185 0.5936
0.000 0.1822 0.00546 0.00068 -0.0358 0.6038 0.6475
0.250 0.2094 0.00539 0.00069 -0.0356 0.5896 0.6923
0.500 0.2367 0.00536 0.00072 -0.0355 0.5753 0.7292
0.750 0.2639 0.00535 0.00075 -0.0353 0.5604 0.7607
1.000 0.2912 0.00537 0.00079 -0.0352 0.5448 0.7877
1.250 0.3183 0.00540 0.00083 -0.0350 0.5276 0.8109
1.500 0.3451 0.00546 0.00089 -0.0347 0.5079 0.8330
1.750 0.3718 0.00552 0.00095 -0.0345 0.4881 0.8550
2.000 0.3981 0.00560 0.00102 -0.0341 0.4674 0.8758
2.250 0.4241 0.00569 0.00109 -0.0337 0.4456 0.8965
2.500 0.4496 0.00581 0.00118 -0.0331 0.4223 0.9165
3.000 0.5020 0.00616 0.00139 -0.0324 0.3607 0.9580
3.250 0.5328 0.00652 0.00155 -0.0333 0.3084 0.9748
3.500 0.5650 0.00697 0.00173 -0.0346 0.2495 0.9878
3.750 0.5974 0.00731 0.00191 -0.0359 0.2119 0.9997
4.000 0.6225 0.00768 0.00211 -0.0356 0.1738 1.0000
4.250 0.6472 0.00810 0.00235 -0.0353 0.1342 1.0000
4.500 0.6726 0.00845 0.00257 -0.0350 0.1064 1.0000
4.750 0.6977 0.00884 0.00283 -0.0347 0.0779 1.0000
5.000 0.7224 0.00931 0.00314 -0.0343 0.0473 1.0000
5.250 0.7465 0.00987 0.00354 -0.0339 0.0168 1.0000
5.500 0.7724 0.01016 0.00381 -0.0337 0.0126 1.0000
5.750 0.7985 0.01043 0.00409 -0.0334 0.0113 1.0000
6.000 0.8246 0.01069 0.00438 -0.0332 0.0110 1.0000
6.250 0.8505 0.01097 0.00469 -0.0330 0.0106 1.0000
6.500 0.8762 0.01127 0.00503 -0.0327 0.0103 1.0000
6.750 0.9017 0.01160 0.00542 -0.0324 0.0099 1.0000
7.000 0.9268 0.01196 0.00582 -0.0321 0.0096 1.0000
7.250 0.9517 0.01235 0.00626 -0.0318 0.0092 1.0000
7.500 0.9763 0.01277 0.00672 -0.0314 0.0088 1.0000
7.750 1.0004 0.01323 0.00722 -0.0309 0.0083 1.0000
8.000 1.0237 0.01380 0.00785 -0.0304 0.0079 1.0000
8.250 1.0454 0.01455 0.00870 -0.0296 0.0074 1.0000
8.500 1.0650 0.01553 0.00980 -0.0285 0.0071 1.0000
8.750 1.0884 0.01597 0.01029 -0.0280 0.0069 1.0000
9.000 1.1118 0.01638 0.01074 -0.0276 0.0068 1.0000
9.250 1.1345 0.01687 0.01129 -0.0270 0.0066 1.0000
9.500 1.1557 0.01750 0.01199 -0.0262 0.0064 1.0000
9.750 1.1770 0.01807 0.01263 -0.0255 0.0061 1.0000
10.000 1.1976 0.01869 0.01333 -0.0247 0.0058 1.0000
10.250 1.2191 0.01917 0.01385 -0.0240 0.0054 1.0000
10.500 1.2401 0.01967 0.01440 -0.0233 0.0051 1.0000
10.750 1.2603 0.02021 0.01498 -0.0225 0.0049 1.0000
11.000 1.2803 0.02072 0.01552 -0.0217 0.0046 1.0000
11.250 1.2966 0.02153 0.01640 -0.0204 0.0044 1.0000
11.500 1.3069 0.02277 0.01775 -0.0184 0.0042 1.0000
11.750 1.3227 0.02336 0.01842 -0.0170 0.0041 1.0000
12.000 1.3316 0.02425 0.01943 -0.0146 0.0040 1.0000
12.250 1.3422 0.02503 0.02028 -0.0127 0.0039 1.0000
12.500 1.3517 0.02592 0.02127 -0.0108 0.0037 1.0000
12.750 1.3612 0.02687 0.02229 -0.0091 0.0035 1.0000
13.000 1.3670 0.02815 0.02368 -0.0073 0.0034 1.0000
13.250 1.3761 0.02924 0.02484 -0.0060 0.0032 1.0000
13.500 1.3869 0.03025 0.02591 -0.0050 0.0030 1.0000
13.750 1.3935 0.03167 0.02740 -0.0039 0.0029 1.0000
14.000 1.4059 0.03266 0.02841 -0.0033 0.0027 1.0000
14.250 1.4085 0.03460 0.03045 -0.0024 0.0026 1.0000
14.500 1.4126 0.03651 0.03242 -0.0019 0.0024 1.0000
14.750 1.4095 0.03930 0.03535 -0.0015 0.0024 1.0000
15.000 1.4059 0.04233 0.03851 -0.0016 0.0023 1.0000
15.250 1.4036 0.04542 0.04173 -0.0020 0.0023 1.0000
15.500 1.3992 0.04896 0.04540 -0.0029 0.0022 1.0000
15.750 1.3947 0.05270 0.04927 -0.0041 0.0021 1.0000
16.000 1.3822 0.05786 0.05458 -0.0061 0.0021 1.0000
16.250 1.3739 0.06265 0.05950 -0.0083 0.0021 1.0000
16.500 1.3589 0.06886 0.06586 -0.0114 0.0020 1.0000
16.750 1.3405 0.07607 0.07323 -0.0153 0.0020 1.0000
17.000 1.3149 0.08512 0.08245 -0.0203 0.0020 1.0000
17.250 1.2975 0.09291 0.09037 -0.0248 0.0020 1.0000
17.500 1.2729 0.10253 0.10014 -0.0303 0.0020 1.0000
17.750 1.2373 0.11490 0.11268 -0.0374 0.0021 1.0000
18.000 1.2121 0.12535 0.12325 -0.0435 0.0021 1.0000
18.250 1.1772 0.13843 0.13647 -0.0511 0.0022 1.0000
18.500 1.1415 0.15242 0.15059 -0.0593 0.0023 1.0000
18.750 1.1172 0.16396 0.16224 -0.0661 0.0023 1.0000
19.000 1.0912 0.17663 0.17502 -0.0736 0.0024 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S6061 9% (s6061-il)