S6061 9% (s6061-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 200,000 Max Cl/Cd: 68.21 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6061-il-200000.txt Download as CSV file: xf-s6061-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4106 0.08466 0.08149 -0.0203 1.0000 0.0500
-8.750 -0.4234 0.07930 0.07618 -0.0257 1.0000 0.0510
-8.500 -0.4357 0.07362 0.07054 -0.0310 1.0000 0.0512
-8.250 -0.4508 0.06791 0.06482 -0.0366 1.0000 0.0513
-8.000 -0.4658 0.06353 0.06038 -0.0390 1.0000 0.0513
-7.750 -0.4762 0.05891 0.05563 -0.0409 1.0000 0.0515
-7.500 -0.4753 0.05138 0.04824 -0.0411 1.0000 0.0529
-7.250 -0.4655 0.04828 0.04519 -0.0401 1.0000 0.0542
-7.000 -0.4621 0.04469 0.04159 -0.0401 1.0000 0.0557
-6.750 -0.4615 0.04092 0.03774 -0.0401 1.0000 0.0575
-6.500 -0.4650 0.03736 0.03408 -0.0390 1.0000 0.0598
-6.000 -0.4968 0.04286 0.03857 -0.0368 1.0000 0.0661
-5.750 -0.4896 0.04051 0.03624 -0.0347 1.0000 0.0677
-5.500 -0.4676 0.02589 0.02200 -0.0313 0.9990 0.0701
-5.250 -0.4683 0.02797 0.02189 -0.0276 1.0000 0.0291
-5.000 -0.4533 0.02491 0.01858 -0.0259 1.0000 0.0275
-4.750 -0.4173 0.02169 0.01487 -0.0277 0.9961 0.0268
-4.500 -0.3787 0.02043 0.01321 -0.0297 0.9914 0.0289
-4.250 -0.3432 0.01776 0.01029 -0.0313 0.9873 0.0302
-4.000 -0.3047 0.01614 0.00861 -0.0334 0.9836 0.0319
-3.750 -0.2695 0.01506 0.00750 -0.0349 0.9772 0.0352
-3.500 -0.2307 0.01390 0.00630 -0.0372 0.9723 0.0461
-3.250 -0.1965 0.01225 0.00524 -0.0390 0.9663 0.1636
-3.000 -0.1626 0.01098 0.00497 -0.0413 0.9603 0.3804
-2.750 -0.1286 0.01005 0.00487 -0.0427 0.9553 0.5897
-2.500 -0.1003 0.00968 0.00491 -0.0422 0.9471 0.7178
-2.250 -0.0679 0.00955 0.00490 -0.0422 0.9411 0.7966
-2.000 -0.0405 0.00952 0.00490 -0.0411 0.9323 0.8465
-1.750 -0.0128 0.00953 0.00488 -0.0401 0.9241 0.8854
-1.500 0.0193 0.00953 0.00482 -0.0398 0.9167 0.9163
-1.250 0.0546 0.00954 0.00473 -0.0405 0.9085 0.9415
-1.000 0.1009 0.00950 0.00458 -0.0436 0.9024 0.9586
-0.750 0.1505 0.00944 0.00441 -0.0476 0.8945 0.9722
-0.500 0.1998 0.00931 0.00417 -0.0517 0.8870 0.9842
-0.250 0.2492 0.00916 0.00394 -0.0561 0.8763 0.9962
0.000 0.2771 0.00905 0.00376 -0.0562 0.8632 1.0000
0.250 0.2955 0.00900 0.00363 -0.0544 0.8492 1.0000
0.500 0.3144 0.00897 0.00354 -0.0527 0.8354 1.0000
0.750 0.3341 0.00896 0.00346 -0.0510 0.8217 1.0000
1.000 0.3545 0.00896 0.00340 -0.0494 0.8080 1.0000
1.250 0.3756 0.00898 0.00337 -0.0480 0.7942 1.0000
1.500 0.3974 0.00901 0.00334 -0.0467 0.7802 1.0000
1.750 0.4199 0.00905 0.00333 -0.0455 0.7661 1.0000
2.000 0.4429 0.00911 0.00334 -0.0444 0.7517 1.0000
2.250 0.4663 0.00917 0.00338 -0.0433 0.7368 1.0000
2.500 0.4902 0.00925 0.00341 -0.0424 0.7214 1.0000
2.750 0.5144 0.00933 0.00344 -0.0414 0.7052 1.0000
3.000 0.5390 0.00942 0.00349 -0.0406 0.6885 1.0000
3.250 0.5637 0.00952 0.00361 -0.0398 0.6696 1.0000
3.500 0.5886 0.00964 0.00370 -0.0391 0.6504 1.0000
3.750 0.6135 0.00978 0.00380 -0.0383 0.6304 1.0000
4.000 0.6385 0.00992 0.00394 -0.0376 0.6077 1.0000
4.250 0.6633 0.01009 0.00411 -0.0369 0.5832 1.0000
4.500 0.6880 0.01029 0.00427 -0.0362 0.5566 1.0000
4.750 0.7124 0.01051 0.00446 -0.0355 0.5261 1.0000
5.000 0.7360 0.01079 0.00465 -0.0346 0.4878 1.0000
5.250 0.7587 0.01117 0.00489 -0.0336 0.4394 1.0000
5.500 0.7808 0.01165 0.00519 -0.0327 0.3867 1.0000
5.750 0.8018 0.01229 0.00557 -0.0318 0.3267 1.0000
6.000 0.8229 0.01299 0.00603 -0.0309 0.2696 1.0000
6.250 0.8440 0.01374 0.00657 -0.0301 0.2156 1.0000
6.500 0.8634 0.01473 0.00727 -0.0292 0.1485 1.0000
6.750 0.8747 0.01696 0.00877 -0.0272 0.0547 1.0000
7.000 0.8916 0.01838 0.01017 -0.0257 0.0420 1.0000
7.250 0.9117 0.01935 0.01126 -0.0245 0.0378 1.0000
7.500 0.9304 0.02050 0.01248 -0.0232 0.0350 1.0000
7.750 0.9474 0.02197 0.01398 -0.0217 0.0328 1.0000
8.000 0.9641 0.02433 0.01637 -0.0202 0.0313 1.0000
8.250 0.9859 0.02588 0.01809 -0.0193 0.0304 1.0000
8.500 1.0075 0.02719 0.01959 -0.0183 0.0288 1.0000
8.750 1.0287 0.02908 0.02169 -0.0174 0.0277 1.0000
9.000 1.0489 0.03145 0.02432 -0.0163 0.0272 1.0000
9.250 1.0667 0.03429 0.02750 -0.0150 0.0270 1.0000
9.500 1.0800 0.03765 0.03127 -0.0133 0.0272 1.0000
9.750 1.0889 0.04094 0.03497 -0.0114 0.0270 1.0000
10.000 1.0951 0.04382 0.03818 -0.0095 0.0262 1.0000
10.250 1.0960 0.04710 0.04179 -0.0073 0.0258 1.0000
10.500 1.0854 0.05164 0.04677 -0.0045 0.0267 1.0000
10.750 1.0681 0.05563 0.05107 -0.0014 0.0275 1.0000
11.000 1.0489 0.05956 0.05523 0.0007 0.0282 1.0000
11.250 1.0298 0.06380 0.05967 0.0013 0.0288 1.0000
11.500 1.0083 0.06860 0.06466 0.0007 0.0291 1.0000
11.750 0.9874 0.07399 0.07020 -0.0013 0.0295 1.0000
12.000 0.9660 0.08016 0.07651 -0.0045 0.0298 1.0000
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Polar data table (+)
Polar graphs
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