S8064 (s8064-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S8064 (s8064-il) Reynolds number: 500,000 Max Cl/Cd: 80.17 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8064-il-500000.txt Download as CSV file: xf-s8064-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5213 0.08451 0.08238 -0.0535 1.0000 0.0241
-11.000 -0.5490 0.07209 0.06996 -0.0630 1.0000 0.0234
-10.750 -0.5777 0.06344 0.06117 -0.0707 0.9927 0.0231
-10.500 -0.6843 0.04082 0.03735 -0.0789 0.9748 0.0137
-10.250 -0.6934 0.03711 0.03336 -0.0772 0.9669 0.0131
-10.000 -0.7289 0.02928 0.02457 -0.0707 0.9574 0.0111
-9.750 -0.7212 0.02692 0.02181 -0.0683 0.9531 0.0107
-9.500 -0.7081 0.02532 0.01996 -0.0666 0.9493 0.0106
-9.250 -0.6936 0.02355 0.01797 -0.0650 0.9462 0.0106
-9.000 -0.6783 0.02172 0.01594 -0.0635 0.9436 0.0108
-8.750 -0.6603 0.02043 0.01453 -0.0624 0.9407 0.0110
-8.500 -0.6419 0.01945 0.01347 -0.0613 0.9378 0.0115
-8.250 -0.6233 0.01856 0.01249 -0.0600 0.9350 0.0117
-8.000 -0.6045 0.01781 0.01163 -0.0587 0.9324 0.0123
-7.750 -0.5864 0.01710 0.01083 -0.0572 0.9300 0.0126
-7.500 -0.5654 0.01646 0.01011 -0.0563 0.9275 0.0133
-7.250 -0.5452 0.01584 0.00941 -0.0552 0.9247 0.0138
-7.000 -0.5263 0.01515 0.00864 -0.0539 0.9219 0.0145
-6.750 -0.5075 0.01454 0.00801 -0.0525 0.9192 0.0166
-6.500 -0.4866 0.01413 0.00753 -0.0513 0.9169 0.0184
-6.250 -0.4666 0.01352 0.00688 -0.0500 0.9144 0.0223
-6.000 -0.4463 0.01289 0.00632 -0.0489 0.9113 0.0382
-5.750 -0.4239 0.01252 0.00600 -0.0481 0.9084 0.0544
-5.500 -0.4012 0.01220 0.00572 -0.0473 0.9059 0.0705
-5.250 -0.3791 0.01185 0.00545 -0.0464 0.9036 0.0936
-5.000 -0.3577 0.01148 0.00523 -0.0454 0.9013 0.1286
-4.750 -0.3361 0.01100 0.00500 -0.0447 0.8979 0.1824
-4.500 -0.3162 0.01043 0.00475 -0.0436 0.8946 0.2558
-4.250 -0.2966 0.00987 0.00449 -0.0424 0.8916 0.3394
-4.000 -0.2770 0.00935 0.00429 -0.0410 0.8891 0.4244
-3.750 -0.2562 0.00900 0.00418 -0.0398 0.8864 0.4973
-3.500 -0.2340 0.00872 0.00410 -0.0388 0.8825 0.5558
-3.250 -0.2109 0.00848 0.00401 -0.0379 0.8792 0.6053
-3.000 -0.1868 0.00830 0.00395 -0.0370 0.8765 0.6459
-2.750 -0.1617 0.00821 0.00393 -0.0363 0.8742 0.6808
-2.500 -0.1361 0.00822 0.00395 -0.0358 0.8712 0.7070
-2.250 -0.1101 0.00822 0.00397 -0.0354 0.8672 0.7259
-2.000 -0.0836 0.00820 0.00394 -0.0350 0.8639 0.7423
-1.750 -0.0566 0.00817 0.00390 -0.0346 0.8613 0.7561
-1.500 -0.0296 0.00816 0.00386 -0.0342 0.8590 0.7686
-1.250 -0.0036 0.00819 0.00390 -0.0339 0.8546 0.7808
-1.000 0.0231 0.00818 0.00390 -0.0335 0.8506 0.7917
-0.750 0.0503 0.00813 0.00386 -0.0332 0.8476 0.8013
-0.500 0.0778 0.00809 0.00379 -0.0329 0.8450 0.8106
-0.250 0.1044 0.00808 0.00382 -0.0326 0.8404 0.8180
0.000 0.1314 0.00804 0.00377 -0.0324 0.8358 0.8253
0.250 0.1593 0.00794 0.00369 -0.0322 0.8324 0.8312
0.500 0.1874 0.00788 0.00360 -0.0321 0.8291 0.8378
0.750 0.2138 0.00781 0.00358 -0.0318 0.8227 0.8432
1.000 0.2417 0.00770 0.00347 -0.0317 0.8181 0.8489
1.250 0.2693 0.00760 0.00337 -0.0315 0.8129 0.8546
1.500 0.2963 0.00749 0.00330 -0.0312 0.8058 0.8594
1.750 0.3245 0.00736 0.00316 -0.0311 0.8002 0.8649
2.000 0.3509 0.00725 0.00309 -0.0308 0.7910 0.8701
2.250 0.3780 0.00713 0.00301 -0.0305 0.7821 0.8750
2.500 0.4052 0.00701 0.00289 -0.0302 0.7720 0.8805
2.750 0.4318 0.00691 0.00282 -0.0298 0.7589 0.8855
3.000 0.4579 0.00685 0.00277 -0.0294 0.7422 0.8908
3.250 0.4836 0.00684 0.00273 -0.0288 0.7224 0.8968
3.500 0.5090 0.00687 0.00272 -0.0282 0.7011 0.9020
3.750 0.5336 0.00695 0.00277 -0.0275 0.6777 0.9085
4.000 0.5575 0.00707 0.00284 -0.0267 0.6502 0.9150
4.250 0.5800 0.00725 0.00294 -0.0256 0.6180 0.9224
4.500 0.6013 0.00750 0.00308 -0.0243 0.5770 0.9306
4.750 0.6203 0.00785 0.00327 -0.0226 0.5270 0.9406
5.000 0.6409 0.00837 0.00355 -0.0214 0.4598 0.9497
5.250 0.6622 0.00908 0.00392 -0.0207 0.3805 0.9598
5.500 0.6858 0.00991 0.00438 -0.0207 0.2977 0.9698
5.750 0.7147 0.01081 0.00490 -0.0220 0.2168 0.9763
6.000 0.7429 0.01166 0.00542 -0.0231 0.1516 0.9841
6.250 0.7753 0.01242 0.00595 -0.0249 0.1058 0.9892
6.500 0.8077 0.01308 0.00648 -0.0267 0.0799 0.9953
6.750 0.8419 0.01367 0.00698 -0.0289 0.0634 1.0000
7.000 0.8434 0.01395 0.00722 -0.0242 0.0576 1.0000
7.250 0.8564 0.01425 0.00753 -0.0216 0.0521 1.0000
7.500 0.8679 0.01474 0.00799 -0.0188 0.0462 1.0000
7.750 0.8825 0.01504 0.00835 -0.0165 0.0424 1.0000
8.000 0.8937 0.01559 0.00886 -0.0138 0.0373 1.0000
8.250 0.9094 0.01597 0.00929 -0.0118 0.0335 1.0000
8.500 0.9219 0.01662 0.00992 -0.0094 0.0284 1.0000
8.750 0.9378 0.01712 0.01046 -0.0077 0.0244 1.0000
9.000 0.9483 0.01801 0.01134 -0.0052 0.0208 1.0000
9.250 0.9628 0.01868 0.01208 -0.0033 0.0190 1.0000
9.500 0.9776 0.01935 0.01281 -0.0016 0.0174 1.0000
9.750 0.9914 0.02011 0.01361 0.0002 0.0165 1.0000
10.000 0.9966 0.02158 0.01514 0.0031 0.0152 1.0000
10.250 1.0092 0.02255 0.01620 0.0049 0.0147 1.0000
10.500 1.0221 0.02353 0.01728 0.0067 0.0143 1.0000
10.750 1.0347 0.02458 0.01843 0.0084 0.0138 1.0000
11.000 1.0471 0.02564 0.01958 0.0100 0.0131 1.0000
11.250 1.0606 0.02644 0.02043 0.0114 0.0124 1.0000
11.500 1.0710 0.02761 0.02168 0.0130 0.0118 1.0000
11.750 1.0802 0.02898 0.02314 0.0147 0.0115 1.0000
12.000 1.0823 0.03175 0.02609 0.0170 0.0110 1.0000
12.250 1.0896 0.03351 0.02801 0.0187 0.0108 1.0000
12.500 1.0961 0.03515 0.02982 0.0203 0.0107 1.0000
12.750 1.1007 0.03693 0.03178 0.0220 0.0105 1.0000
13.000 1.1027 0.03909 0.03413 0.0236 0.0103 1.0000
13.250 1.1019 0.04155 0.03678 0.0252 0.0103 1.0000
13.500 1.0981 0.04429 0.03973 0.0266 0.0101 1.0000
13.750 1.0929 0.04719 0.04284 0.0278 0.0100 1.0000
14.000 1.0826 0.05084 0.04670 0.0286 0.0100 1.0000
14.250 1.0712 0.05472 0.05079 0.0289 0.0100 1.0000
14.500 1.0588 0.05890 0.05516 0.0285 0.0098 1.0000
14.750 1.0407 0.06425 0.06073 0.0274 0.0099 1.0000
15.000 1.0215 0.07024 0.06693 0.0253 0.0099 1.0000
15.250 0.9999 0.07722 0.07411 0.0221 0.0099 1.0000
15.500 0.9747 0.08562 0.08271 0.0175 0.0101 1.0000
15.750 0.9551 0.09381 0.09107 0.0124 0.0099 1.0000
16.000 0.9242 0.10519 0.10261 0.0054 0.0104 1.0000
16.250 0.8921 0.11814 0.11572 -0.0026 0.0105 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8064 (s8064-il)