S3021-095-84 (s3021-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 500,000 Max Cl/Cd: 101.36 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3021-il-500000.txt Download as CSV file: xf-s3021-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4171 0.10141 0.09911 -0.0243 1.0000 0.0168
-9.750 -0.4127 0.09836 0.09607 -0.0250 1.0000 0.0171
-9.500 -0.4061 0.09604 0.09376 -0.0251 1.0000 0.0176
-9.250 -0.4020 0.09305 0.09079 -0.0260 1.0000 0.0180
-7.000 -0.4227 0.05558 0.05339 -0.0451 0.9993 0.0223
-6.750 -0.4097 0.04328 0.04066 -0.0553 0.9912 0.0232
-6.500 -0.3811 0.04110 0.03847 -0.0584 0.9867 0.0240
-6.250 -0.3501 0.03892 0.03620 -0.0618 0.9827 0.0255
-6.000 -0.3203 0.03477 0.03173 -0.0649 0.9754 0.0282
-5.750 -0.2955 0.02915 0.02540 -0.0671 0.9654 0.0315
-5.500 -0.2661 0.02696 0.02320 -0.0689 0.9575 0.0330
-5.250 -0.2402 0.02525 0.02134 -0.0692 0.9439 0.0348
-5.000 -0.2086 0.02626 0.02206 -0.0687 0.9291 0.0401
-4.750 -0.1923 0.01704 0.01176 -0.0658 0.9110 0.0218
-4.500 -0.1686 0.01492 0.00932 -0.0647 0.8937 0.0209
-4.250 -0.1438 0.01367 0.00783 -0.0637 0.8765 0.0207
-4.000 -0.1188 0.01278 0.00677 -0.0629 0.8599 0.0209
-3.750 -0.0933 0.01220 0.00604 -0.0621 0.8441 0.0215
-3.500 -0.0684 0.01144 0.00514 -0.0613 0.8293 0.0215
-3.250 -0.0432 0.01083 0.00439 -0.0605 0.8152 0.0216
-3.000 -0.0177 0.01035 0.00380 -0.0599 0.8019 0.0219
-2.750 0.0083 0.00999 0.00333 -0.0593 0.7893 0.0224
-2.500 0.0341 0.00952 0.00274 -0.0587 0.7774 0.0243
-2.250 0.0607 0.00929 0.00242 -0.0583 0.7662 0.0269
-2.000 0.0875 0.00909 0.00216 -0.0579 0.7553 0.0345
-1.750 0.1120 0.00838 0.00193 -0.0574 0.7443 0.1651
-1.500 0.1369 0.00788 0.00183 -0.0571 0.7340 0.2956
-1.250 0.1620 0.00751 0.00176 -0.0566 0.7243 0.4091
-1.000 0.1853 0.00698 0.00173 -0.0559 0.7140 0.5696
-0.750 0.2036 0.00627 0.00176 -0.0536 0.7044 0.7888
-0.500 0.2496 0.00611 0.00189 -0.0564 0.6947 0.9706
-0.250 0.3039 0.00617 0.00183 -0.0620 0.6838 0.9888
0.000 0.3540 0.00619 0.00174 -0.0668 0.6728 0.9991
0.250 0.3815 0.00624 0.00170 -0.0667 0.6628 1.0000
0.500 0.4060 0.00631 0.00167 -0.0660 0.6532 1.0000
0.750 0.4308 0.00635 0.00166 -0.0654 0.6430 1.0000
1.000 0.4556 0.00642 0.00166 -0.0647 0.6331 1.0000
1.250 0.4803 0.00650 0.00166 -0.0640 0.6235 1.0000
1.500 0.5053 0.00656 0.00168 -0.0634 0.6129 1.0000
1.750 0.5304 0.00664 0.00172 -0.0628 0.6026 1.0000
2.000 0.5553 0.00673 0.00175 -0.0621 0.5924 1.0000
2.250 0.5802 0.00683 0.00179 -0.0615 0.5813 1.0000
2.500 0.6053 0.00691 0.00185 -0.0609 0.5697 1.0000
2.750 0.6303 0.00701 0.00192 -0.0603 0.5580 1.0000
3.000 0.6553 0.00712 0.00199 -0.0596 0.5459 1.0000
3.250 0.6802 0.00723 0.00207 -0.0590 0.5329 1.0000
3.500 0.7050 0.00736 0.00216 -0.0584 0.5194 1.0000
3.750 0.7298 0.00750 0.00227 -0.0577 0.5053 1.0000
4.000 0.7546 0.00764 0.00238 -0.0571 0.4896 1.0000
4.250 0.7792 0.00780 0.00250 -0.0565 0.4733 1.0000
4.500 0.8037 0.00798 0.00264 -0.0558 0.4557 1.0000
4.750 0.8280 0.00820 0.00281 -0.0551 0.4368 1.0000
5.000 0.8524 0.00841 0.00298 -0.0545 0.4163 1.0000
5.250 0.8764 0.00867 0.00317 -0.0538 0.3952 1.0000
5.500 0.9005 0.00894 0.00340 -0.0532 0.3725 1.0000
5.750 0.9240 0.00925 0.00364 -0.0525 0.3487 1.0000
6.000 0.9466 0.00966 0.00391 -0.0516 0.3150 1.0000
6.250 0.9684 0.01015 0.00423 -0.0507 0.2797 1.0000
6.500 0.9907 0.01061 0.00457 -0.0499 0.2491 1.0000
6.750 1.0129 0.01107 0.00492 -0.0491 0.2210 1.0000
7.250 1.0566 0.01207 0.00571 -0.0474 0.1692 1.0000
7.500 1.0773 0.01267 0.00617 -0.0465 0.1399 1.0000
7.750 1.0957 0.01348 0.00676 -0.0452 0.1020 1.0000
8.000 1.1143 0.01426 0.00736 -0.0440 0.0713 1.0000
8.250 1.1269 0.01556 0.00834 -0.0419 0.0275 1.0000
8.500 1.1430 0.01653 0.00923 -0.0402 0.0149 1.0000
8.750 1.1615 0.01725 0.01002 -0.0388 0.0128 1.0000
9.000 1.1797 0.01795 0.01082 -0.0374 0.0118 1.0000
9.250 1.1968 0.01870 0.01167 -0.0359 0.0112 1.0000
9.500 1.2116 0.01958 0.01263 -0.0341 0.0106 1.0000
9.750 1.2221 0.02070 0.01386 -0.0317 0.0101 1.0000
10.000 1.2273 0.02190 0.01516 -0.0285 0.0097 1.0000
10.250 1.2307 0.02313 0.01650 -0.0252 0.0095 1.0000
10.500 1.2380 0.02417 0.01764 -0.0227 0.0094 1.0000
10.750 1.2430 0.02545 0.01902 -0.0201 0.0093 1.0000
11.000 1.2487 0.02675 0.02044 -0.0180 0.0090 1.0000
11.250 1.2516 0.02837 0.02217 -0.0158 0.0090 1.0000
11.500 1.2548 0.03009 0.02399 -0.0140 0.0089 1.0000
11.750 1.2575 0.03198 0.02600 -0.0125 0.0087 1.0000
12.000 1.2597 0.03405 0.02819 -0.0111 0.0087 1.0000
12.250 1.2618 0.03624 0.03049 -0.0100 0.0086 1.0000
12.500 1.2638 0.03854 0.03291 -0.0091 0.0084 1.0000
12.750 1.2656 0.04093 0.03543 -0.0084 0.0083 1.0000
13.000 1.2667 0.04354 0.03818 -0.0077 0.0084 1.0000
13.250 1.2667 0.04634 0.04111 -0.0073 0.0082 1.0000
13.500 1.2659 0.04933 0.04424 -0.0071 0.0082 1.0000
13.750 1.2637 0.05259 0.04765 -0.0070 0.0081 1.0000
14.000 1.2605 0.05609 0.05132 -0.0072 0.0082 1.0000
14.250 1.2555 0.05988 0.05527 -0.0077 0.0081 1.0000
14.500 1.2481 0.06421 0.05982 -0.0085 0.0082 1.0000
14.750 1.2392 0.06891 0.06470 -0.0098 0.0082 1.0000
15.000 1.2283 0.07412 0.07009 -0.0115 0.0083 1.0000
15.250 1.2163 0.07974 0.07591 -0.0138 0.0084 1.0000
15.500 1.2015 0.08616 0.08252 -0.0167 0.0085 1.0000
15.750 1.1861 0.09300 0.08954 -0.0202 0.0085 1.0000
16.000 1.1701 0.10030 0.09702 -0.0241 0.0087 1.0000
16.250 1.1523 0.10836 0.10525 -0.0287 0.0087 1.0000
16.500 1.1354 0.11658 0.11364 -0.0335 0.0088 1.0000
16.750 1.1175 0.12540 0.12259 -0.0389 0.0090 1.0000
17.000 1.1007 0.13439 0.13173 -0.0444 0.0090 1.0000
17.250 1.0812 0.14450 0.14197 -0.0507 0.0091 1.0000
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Polar data table (+)
Polar graphs
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