S3021-095-84 (s3021-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 50,000 Max Cl/Cd: 37.55 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3021-il-50000-n5.txt Download as CSV file: xf-s3021-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3021-095-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3998 0.09050 0.08374 -0.0316 1.0000 0.0580
-8.000 -0.3987 0.08698 0.08029 -0.0323 1.0000 0.0561
-7.750 -0.4019 0.08339 0.07681 -0.0336 1.0000 0.0544
-7.500 -0.4054 0.07925 0.07276 -0.0360 1.0000 0.0525
-7.000 -0.4193 0.06739 0.06076 -0.0449 1.0000 0.0470
-6.750 -0.4158 0.06411 0.05749 -0.0444 1.0000 0.0465
-6.500 -0.4133 0.06061 0.05395 -0.0441 1.0000 0.0460
-6.250 -0.4104 0.05710 0.05035 -0.0438 1.0000 0.0455
-6.000 -0.4067 0.05365 0.04675 -0.0432 1.0000 0.0450
-5.750 -0.4019 0.05027 0.04318 -0.0424 1.0000 0.0446
-5.500 -0.3954 0.04709 0.03974 -0.0413 1.0000 0.0442
-5.250 -0.3872 0.04406 0.03642 -0.0402 1.0000 0.0439
-5.000 -0.3771 0.04120 0.03321 -0.0389 1.0000 0.0438
-4.750 -0.3649 0.03860 0.03020 -0.0377 1.0000 0.0444
-4.500 -0.3507 0.03630 0.02744 -0.0364 1.0000 0.0456
-4.250 -0.3139 0.03359 0.02400 -0.0389 0.9915 0.0474
-4.000 -0.2779 0.03103 0.02108 -0.0414 0.9833 0.0491
-3.750 -0.2422 0.02905 0.01877 -0.0431 0.9742 0.0507
-3.500 -0.2061 0.02742 0.01684 -0.0447 0.9652 0.0530
-3.250 -0.1677 0.02600 0.01513 -0.0465 0.9572 0.0563
-2.750 -0.0963 0.02388 0.01260 -0.0495 0.9378 0.0745
-2.500 -0.0580 0.02267 0.01148 -0.0516 0.9295 0.1040
-2.250 -0.0278 0.02079 0.01088 -0.0531 0.9196 0.3154
-2.000 -0.0035 0.01892 0.01087 -0.0510 0.9123 0.7123
-1.750 0.0871 0.01847 0.01008 -0.0619 0.9113 1.0000
-1.500 0.1246 0.01850 0.00968 -0.0639 0.9006 1.0000
-1.250 0.1568 0.01857 0.00939 -0.0649 0.8883 1.0000
-1.000 0.1883 0.01866 0.00918 -0.0657 0.8762 1.0000
-0.750 0.2194 0.01876 0.00901 -0.0663 0.8645 1.0000
-0.500 0.2508 0.01885 0.00886 -0.0669 0.8532 1.0000
-0.250 0.2829 0.01893 0.00872 -0.0676 0.8428 1.0000
0.000 0.3094 0.01910 0.00871 -0.0673 0.8303 1.0000
0.250 0.3358 0.01927 0.00873 -0.0669 0.8181 1.0000
0.500 0.3623 0.01945 0.00877 -0.0666 0.8062 1.0000
0.750 0.3892 0.01963 0.00882 -0.0662 0.7948 1.0000
1.000 0.4174 0.01977 0.00884 -0.0660 0.7840 1.0000
1.250 0.4432 0.01997 0.00896 -0.0654 0.7720 1.0000
1.500 0.4678 0.02021 0.00913 -0.0647 0.7596 1.0000
1.750 0.4927 0.02045 0.00931 -0.0639 0.7473 1.0000
2.000 0.5178 0.02067 0.00950 -0.0632 0.7350 1.0000
2.250 0.5432 0.02088 0.00967 -0.0625 0.7229 1.0000
2.500 0.5690 0.02108 0.00984 -0.0617 0.7108 1.0000
2.750 0.5950 0.02125 0.01001 -0.0610 0.6988 1.0000
3.000 0.6189 0.02150 0.01028 -0.0600 0.6854 1.0000
3.250 0.6429 0.02176 0.01055 -0.0591 0.6719 1.0000
3.500 0.6669 0.02201 0.01083 -0.0581 0.6581 1.0000
3.750 0.6909 0.02226 0.01111 -0.0571 0.6442 1.0000
4.000 0.7148 0.02250 0.01144 -0.0561 0.6300 1.0000
4.250 0.7388 0.02274 0.01174 -0.0551 0.6155 1.0000
4.500 0.7626 0.02298 0.01203 -0.0540 0.6006 1.0000
4.750 0.7866 0.02320 0.01232 -0.0529 0.5853 1.0000
5.000 0.8099 0.02344 0.01268 -0.0518 0.5692 1.0000
5.250 0.8317 0.02377 0.01311 -0.0505 0.5515 1.0000
5.500 0.8541 0.02405 0.01349 -0.0493 0.5336 1.0000
5.750 0.8771 0.02428 0.01380 -0.0480 0.5155 1.0000
6.000 0.8991 0.02457 0.01424 -0.0467 0.4963 1.0000
6.250 0.9201 0.02493 0.01470 -0.0453 0.4756 1.0000
6.500 0.9419 0.02523 0.01506 -0.0439 0.4553 1.0000
6.750 0.9616 0.02569 0.01563 -0.0424 0.4327 1.0000
7.000 0.9816 0.02614 0.01614 -0.0409 0.4104 1.0000
7.250 1.0006 0.02666 0.01679 -0.0393 0.3872 1.0000
7.500 1.0183 0.02731 0.01752 -0.0376 0.3633 1.0000
7.750 1.0354 0.02801 0.01825 -0.0359 0.3398 1.0000
8.000 1.0514 0.02880 0.01908 -0.0342 0.3164 1.0000
8.250 1.0661 0.02973 0.02009 -0.0324 0.2931 1.0000
8.500 1.0799 0.03071 0.02109 -0.0306 0.2713 1.0000
8.750 1.0923 0.03184 0.02237 -0.0287 0.2496 1.0000
9.000 1.1030 0.03303 0.02359 -0.0267 0.2291 1.0000
9.250 1.1120 0.03436 0.02503 -0.0246 0.2088 1.0000
9.500 1.1184 0.03576 0.02643 -0.0223 0.1901 1.0000
9.750 1.1217 0.03731 0.02807 -0.0199 0.1717 1.0000
10.000 1.1206 0.03901 0.02982 -0.0173 0.1534 1.0000
10.250 1.1153 0.04101 0.03175 -0.0151 0.1357 1.0000
10.500 1.1092 0.04341 0.03418 -0.0136 0.1153 1.0000
10.750 1.1022 0.04620 0.03691 -0.0129 0.0977 1.0000
11.000 1.0960 0.04935 0.04002 -0.0125 0.0821 1.0000
11.250 1.0897 0.05281 0.04347 -0.0123 0.0710 1.0000
11.500 1.0849 0.05638 0.04715 -0.0121 0.0619 1.0000
11.750 1.0790 0.06025 0.05109 -0.0121 0.0551 1.0000
12.000 1.0754 0.06391 0.05483 -0.0123 0.0510 1.0000
12.250 1.0705 0.06787 0.05890 -0.0127 0.0472 1.0000
12.500 1.0687 0.07169 0.06295 -0.0130 0.0438 1.0000
12.750 1.0659 0.07559 0.06701 -0.0137 0.0415 1.0000
13.000 1.0613 0.07974 0.07121 -0.0147 0.0394 1.0000
13.250 1.0565 0.08423 0.07583 -0.0159 0.0375 1.0000
13.500 1.0517 0.08906 0.08096 -0.0173 0.0364 1.0000
13.750 1.0443 0.09450 0.08666 -0.0193 0.0354 1.0000
14.000 1.0348 0.10050 0.09291 -0.0218 0.0347 1.0000
14.250 1.0236 0.10717 0.09981 -0.0250 0.0344 1.0000
14.500 1.0092 0.11488 0.10774 -0.0290 0.0343 1.0000
14.750 0.9926 0.12368 0.11674 -0.0338 0.0347 1.0000
15.000 0.9728 0.13401 0.12721 -0.0396 0.0354 1.0000
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Polar data table (+)
Polar graphs
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