S8064 (s8064-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 500,000 Max Cl/Cd: 65.38 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8064-il-500000-n5.txt Download as CSV file: xf-s8064-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8064
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6925 0.09296 0.09047 -0.0400 1.0000 0.0047
-14.000 -0.7034 0.08525 0.08268 -0.0443 1.0000 0.0046
-13.750 -0.7278 0.07444 0.07170 -0.0513 1.0000 0.0045
-13.500 -0.7448 0.06623 0.06336 -0.0572 1.0000 0.0045
-13.250 -0.7665 0.05834 0.05531 -0.0627 1.0000 0.0045
-13.000 -0.7829 0.05233 0.04912 -0.0666 1.0000 0.0045
-12.750 -0.7948 0.04617 0.04270 -0.0719 0.9671 0.0045
-12.500 -0.8009 0.04165 0.03789 -0.0750 0.9533 0.0045
-12.250 -0.8070 0.03857 0.03460 -0.0753 0.9421 0.0045
-12.000 -0.8156 0.03585 0.03162 -0.0740 0.9333 0.0045
-11.750 -0.8204 0.03367 0.02921 -0.0723 0.9269 0.0045
-11.500 -0.8233 0.03172 0.02706 -0.0701 0.9213 0.0045
-11.250 -0.8237 0.03007 0.02519 -0.0677 0.9168 0.0045
-11.000 -0.8208 0.02858 0.02352 -0.0654 0.9127 0.0045
-10.750 -0.8206 0.02674 0.02146 -0.0624 0.9084 0.0046
-10.500 -0.8160 0.02532 0.01984 -0.0596 0.9051 0.0046
-10.250 -0.8093 0.02401 0.01835 -0.0570 0.9025 0.0047
-10.000 -0.7982 0.02268 0.01687 -0.0551 0.9002 0.0048
-9.750 -0.7837 0.02164 0.01571 -0.0536 0.8977 0.0049
-9.500 -0.7682 0.02065 0.01460 -0.0522 0.8952 0.0050
-9.250 -0.7510 0.01980 0.01365 -0.0510 0.8932 0.0052
-9.000 -0.7327 0.01903 0.01277 -0.0498 0.8912 0.0053
-8.750 -0.7141 0.01828 0.01191 -0.0486 0.8893 0.0055
-8.500 -0.6945 0.01762 0.01115 -0.0476 0.8875 0.0057
-8.250 -0.6740 0.01695 0.01039 -0.0467 0.8855 0.0059
-8.000 -0.6528 0.01634 0.00970 -0.0459 0.8833 0.0061
-7.750 -0.6311 0.01577 0.00906 -0.0452 0.8812 0.0063
-7.500 -0.6089 0.01526 0.00846 -0.0444 0.8792 0.0066
-7.250 -0.5865 0.01475 0.00787 -0.0437 0.8773 0.0068
-7.000 -0.5643 0.01423 0.00729 -0.0430 0.8755 0.0075
-6.750 -0.5411 0.01382 0.00682 -0.0424 0.8738 0.0082
-6.500 -0.5171 0.01346 0.00640 -0.0419 0.8721 0.0092
-6.250 -0.4932 0.01304 0.00596 -0.0414 0.8700 0.0106
-6.000 -0.4692 0.01264 0.00554 -0.0409 0.8678 0.0140
-5.750 -0.4452 0.01227 0.00518 -0.0404 0.8655 0.0213
-5.500 -0.4210 0.01190 0.00486 -0.0400 0.8634 0.0323
-5.250 -0.3963 0.01161 0.00458 -0.0396 0.8614 0.0421
-5.000 -0.3719 0.01128 0.00431 -0.0392 0.8596 0.0583
-4.750 -0.3476 0.01093 0.00406 -0.0387 0.8577 0.0813
-4.500 -0.3232 0.01057 0.00383 -0.0384 0.8553 0.1114
-4.250 -0.2988 0.01021 0.00361 -0.0380 0.8527 0.1458
-4.000 -0.2744 0.00985 0.00338 -0.0377 0.8501 0.1849
-3.750 -0.2506 0.00945 0.00316 -0.0372 0.8477 0.2349
-3.500 -0.2275 0.00899 0.00294 -0.0366 0.8455 0.3013
-3.250 -0.2041 0.00857 0.00274 -0.0360 0.8434 0.3678
-3.000 -0.1805 0.00820 0.00260 -0.0354 0.8403 0.4319
-2.750 -0.1561 0.00790 0.00249 -0.0350 0.8372 0.4865
-2.500 -0.1312 0.00765 0.00238 -0.0345 0.8343 0.5327
-2.250 -0.1059 0.00743 0.00227 -0.0341 0.8316 0.5741
-2.000 -0.0805 0.00723 0.00219 -0.0336 0.8292 0.6145
-1.750 -0.0550 0.00708 0.00219 -0.0332 0.8257 0.6513
-1.500 -0.0287 0.00700 0.00220 -0.0329 0.8220 0.6830
-1.250 -0.0016 0.00695 0.00218 -0.0327 0.8186 0.7068
-1.000 0.0257 0.00691 0.00215 -0.0325 0.8157 0.7253
-0.750 0.0532 0.00689 0.00215 -0.0324 0.8121 0.7395
-0.500 0.0807 0.00688 0.00215 -0.0324 0.8075 0.7507
-0.250 0.1084 0.00684 0.00213 -0.0324 0.8033 0.7599
0.000 0.1365 0.00681 0.00208 -0.0324 0.7996 0.7670
0.250 0.1641 0.00680 0.00210 -0.0324 0.7935 0.7739
0.500 0.1920 0.00676 0.00206 -0.0324 0.7879 0.7802
0.750 0.2197 0.00673 0.00206 -0.0324 0.7810 0.7858
1.000 0.2474 0.00670 0.00202 -0.0324 0.7731 0.7917
1.250 0.2750 0.00667 0.00201 -0.0323 0.7630 0.7966
1.500 0.3024 0.00664 0.00198 -0.0322 0.7514 0.8016
1.750 0.3297 0.00664 0.00195 -0.0321 0.7373 0.8068
2.000 0.3565 0.00665 0.00192 -0.0319 0.7202 0.8112
2.250 0.3827 0.00671 0.00192 -0.0315 0.7003 0.8159
2.500 0.4086 0.00681 0.00196 -0.0311 0.6768 0.8209
2.750 0.4337 0.00695 0.00201 -0.0306 0.6498 0.8254
3.000 0.4575 0.00714 0.00210 -0.0298 0.6168 0.8302
3.250 0.4802 0.00739 0.00221 -0.0289 0.5763 0.8356
3.500 0.5021 0.00768 0.00236 -0.0278 0.5343 0.8407
3.750 0.5230 0.00801 0.00254 -0.0266 0.4884 0.8464
4.000 0.5424 0.00843 0.00276 -0.0252 0.4343 0.8530
4.250 0.5608 0.00889 0.00301 -0.0236 0.3766 0.8596
4.500 0.5783 0.00944 0.00331 -0.0220 0.3132 0.8675
4.750 0.5963 0.00993 0.00361 -0.0204 0.2587 0.8755
5.000 0.6145 0.01044 0.00391 -0.0189 0.2074 0.8844
5.250 0.6334 0.01089 0.00422 -0.0175 0.1661 0.8936
5.500 0.6534 0.01128 0.00453 -0.0163 0.1356 0.9030
5.750 0.6743 0.01164 0.00483 -0.0152 0.1127 0.9144
6.250 0.7228 0.01242 0.00554 -0.0146 0.0766 0.9417
6.500 0.7536 0.01287 0.00596 -0.0158 0.0626 0.9544
6.750 0.7860 0.01334 0.00639 -0.0174 0.0513 0.9673
7.000 0.8174 0.01382 0.00683 -0.0188 0.0416 0.9829
7.250 0.8487 0.01426 0.00727 -0.0202 0.0355 0.9962
7.500 0.8703 0.01465 0.00768 -0.0195 0.0320 1.0000
7.750 0.8849 0.01497 0.00801 -0.0172 0.0286 1.0000
8.000 0.8990 0.01536 0.00839 -0.0150 0.0256 1.0000
8.250 0.9146 0.01574 0.00880 -0.0130 0.0229 1.0000
8.500 0.9298 0.01620 0.00926 -0.0111 0.0194 1.0000
8.750 0.9459 0.01667 0.00977 -0.0094 0.0166 1.0000
9.000 0.9612 0.01723 0.01032 -0.0076 0.0140 1.0000
9.250 0.9770 0.01779 0.01091 -0.0059 0.0121 1.0000
9.500 0.9926 0.01838 0.01153 -0.0043 0.0110 1.0000
9.750 1.0073 0.01906 0.01224 -0.0026 0.0100 1.0000
10.000 1.0224 0.01971 0.01297 -0.0011 0.0094 1.0000
10.250 1.0373 0.02040 0.01374 0.0005 0.0091 1.0000
10.500 1.0519 0.02112 0.01453 0.0021 0.0086 1.0000
10.750 1.0654 0.02192 0.01540 0.0037 0.0083 1.0000
11.000 1.0785 0.02277 0.01631 0.0053 0.0079 1.0000
11.250 1.0895 0.02377 0.01739 0.0071 0.0077 1.0000
11.500 1.0992 0.02488 0.01858 0.0089 0.0074 1.0000
11.750 1.1082 0.02607 0.01986 0.0107 0.0073 1.0000
12.000 1.1180 0.02720 0.02110 0.0124 0.0072 1.0000
12.250 1.1277 0.02836 0.02238 0.0140 0.0070 1.0000
12.500 1.1370 0.02957 0.02371 0.0155 0.0068 1.0000
12.750 1.1444 0.03095 0.02520 0.0170 0.0066 1.0000
13.000 1.1532 0.03223 0.02658 0.0183 0.0063 1.0000
13.250 1.1577 0.03390 0.02838 0.0198 0.0063 1.0000
13.500 1.1637 0.03548 0.03006 0.0211 0.0062 1.0000
13.750 1.1673 0.03731 0.03201 0.0223 0.0059 1.0000
14.000 1.1700 0.03929 0.03411 0.0234 0.0059 1.0000
14.250 1.1716 0.04143 0.03637 0.0243 0.0057 1.0000
14.500 1.1711 0.04388 0.03895 0.0250 0.0057 1.0000
14.750 1.1702 0.04648 0.04167 0.0254 0.0055 1.0000
15.000 1.1668 0.04948 0.04481 0.0256 0.0055 1.0000
15.250 1.1620 0.05286 0.04835 0.0255 0.0055 1.0000
15.500 1.1556 0.05661 0.05225 0.0249 0.0054 1.0000
15.750 1.1476 0.06081 0.05658 0.0238 0.0053 1.0000
16.000 1.1346 0.06603 0.06196 0.0220 0.0053 1.0000
16.250 1.1256 0.07096 0.06706 0.0201 0.0053 1.0000
16.500 1.1105 0.07717 0.07342 0.0172 0.0052 1.0000
16.750 1.0979 0.08338 0.07979 0.0140 0.0052 1.0000
17.000 1.0800 0.09092 0.08749 0.0099 0.0052 1.0000
17.250 1.0633 0.09861 0.09535 0.0056 0.0052 1.0000
17.500 1.0420 0.10761 0.10451 0.0005 0.0052 1.0000
17.750 1.0203 0.11706 0.11411 -0.0049 0.0052 1.0000
18.000 0.9995 0.12661 0.12382 -0.0102 0.0053 1.0000
18.250 0.9726 0.13800 0.13535 -0.0166 0.0054 1.0000
18.500 0.9348 0.15274 0.15027 -0.0246 0.0055 1.0000
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Polar data table (+)
Polar graphs
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