S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 500,000 Max Cl/Cd: 64.26 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8065-il-500000-n5.txt Download as CSV file: xf-s8065-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8065 (11% version of 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7019 0.06300 0.06057 -0.0491 1.0000 0.0048
-11.750 -0.7292 0.05355 0.05094 -0.0568 1.0000 0.0047
-11.500 -0.7449 0.04829 0.04552 -0.0602 1.0000 0.0047
-11.250 -0.7770 0.04225 0.03922 -0.0617 1.0000 0.0045
-11.000 -0.7908 0.03898 0.03576 -0.0610 1.0000 0.0045
-10.500 -0.7867 0.03295 0.02909 -0.0616 0.9561 0.0048
-10.250 -0.7898 0.03028 0.02608 -0.0588 0.9443 0.0047
-10.000 -0.7847 0.02828 0.02377 -0.0566 0.9369 0.0048
-9.750 -0.7746 0.02671 0.02192 -0.0547 0.9316 0.0049
-9.500 -0.7631 0.02501 0.01996 -0.0529 0.9270 0.0049
-9.250 -0.7494 0.02341 0.01811 -0.0513 0.9225 0.0050
-9.000 -0.7334 0.02207 0.01655 -0.0499 0.9189 0.0050
-8.750 -0.7162 0.02086 0.01514 -0.0486 0.9158 0.0050
-8.500 -0.6972 0.01973 0.01384 -0.0476 0.9125 0.0051
-8.250 -0.6774 0.01872 0.01268 -0.0466 0.9092 0.0051
-8.000 -0.6572 0.01782 0.01164 -0.0456 0.9060 0.0052
-7.750 -0.6371 0.01692 0.01060 -0.0445 0.9032 0.0053
-7.500 -0.6175 0.01595 0.00950 -0.0434 0.9006 0.0054
-7.250 -0.5959 0.01516 0.00864 -0.0426 0.8977 0.0056
-7.000 -0.5732 0.01454 0.00793 -0.0419 0.8949 0.0059
-6.750 -0.5499 0.01401 0.00733 -0.0413 0.8921 0.0062
-6.500 -0.5263 0.01352 0.00675 -0.0407 0.8896 0.0067
-6.250 -0.5023 0.01310 0.00624 -0.0401 0.8873 0.0070
-6.000 -0.4774 0.01271 0.00578 -0.0397 0.8847 0.0076
-5.750 -0.4527 0.01229 0.00531 -0.0393 0.8818 0.0085
-5.500 -0.4278 0.01193 0.00492 -0.0389 0.8790 0.0104
-5.250 -0.4032 0.01153 0.00452 -0.0384 0.8764 0.0163
-5.000 -0.3785 0.01116 0.00418 -0.0380 0.8740 0.0283
-4.750 -0.3532 0.01085 0.00391 -0.0377 0.8716 0.0406
-4.500 -0.3277 0.01053 0.00366 -0.0374 0.8686 0.0577
-4.250 -0.3020 0.01025 0.00343 -0.0372 0.8656 0.0756
-4.000 -0.2773 0.00985 0.00319 -0.0368 0.8626 0.1130
-3.750 -0.2526 0.00947 0.00296 -0.0365 0.8600 0.1544
-3.500 -0.2274 0.00914 0.00276 -0.0362 0.8573 0.1962
-3.250 -0.2028 0.00872 0.00257 -0.0358 0.8537 0.2573
-3.000 -0.1786 0.00828 0.00238 -0.0354 0.8502 0.3290
-2.750 -0.1544 0.00788 0.00222 -0.0349 0.8470 0.4008
-2.500 -0.1295 0.00757 0.00208 -0.0345 0.8441 0.4617
-2.250 -0.1042 0.00730 0.00199 -0.0341 0.8403 0.5155
-2.000 -0.0785 0.00708 0.00192 -0.0338 0.8362 0.5600
-1.750 -0.0528 0.00688 0.00184 -0.0334 0.8326 0.6018
-1.500 -0.0270 0.00672 0.00178 -0.0329 0.8294 0.6423
-1.250 -0.0008 0.00660 0.00180 -0.0326 0.8247 0.6791
-1.000 0.0259 0.00653 0.00179 -0.0323 0.8201 0.7085
-0.750 0.0529 0.00647 0.00177 -0.0320 0.8161 0.7317
-0.500 0.0801 0.00644 0.00177 -0.0318 0.8110 0.7499
-0.250 0.1074 0.00640 0.00176 -0.0317 0.8053 0.7644
0.000 0.1348 0.00637 0.00173 -0.0315 0.8003 0.7759
0.250 0.1623 0.00634 0.00174 -0.0314 0.7928 0.7854
0.500 0.1899 0.00631 0.00170 -0.0313 0.7856 0.7943
0.750 0.2172 0.00628 0.00170 -0.0312 0.7758 0.8023
1.000 0.2446 0.00627 0.00168 -0.0310 0.7646 0.8104
1.250 0.2717 0.00625 0.00166 -0.0308 0.7513 0.8175
1.500 0.2987 0.00626 0.00164 -0.0305 0.7354 0.8251
1.750 0.3251 0.00629 0.00163 -0.0302 0.7169 0.8318
2.000 0.3514 0.00636 0.00165 -0.0298 0.6948 0.8392
2.250 0.3770 0.00646 0.00169 -0.0293 0.6696 0.8460
2.500 0.4022 0.00661 0.00175 -0.0287 0.6394 0.8536
2.750 0.4262 0.00681 0.00184 -0.0280 0.6017 0.8609
3.250 0.4723 0.00735 0.00209 -0.0262 0.5116 0.8777
3.500 0.4942 0.00770 0.00227 -0.0252 0.4579 0.8871
3.750 0.5151 0.00814 0.00250 -0.0240 0.3958 0.8980
4.000 0.5358 0.00864 0.00276 -0.0229 0.3300 0.9100
4.250 0.5569 0.00921 0.00306 -0.0219 0.2590 0.9238
4.500 0.5817 0.00976 0.00338 -0.0217 0.2009 0.9382
4.750 0.6115 0.01025 0.00372 -0.0226 0.1573 0.9515
5.000 0.6435 0.01072 0.00405 -0.0240 0.1224 0.9634
5.250 0.6752 0.01118 0.00440 -0.0253 0.0945 0.9745
5.500 0.7058 0.01160 0.00475 -0.0264 0.0760 0.9845
5.750 0.7377 0.01201 0.00510 -0.0277 0.0618 0.9916
6.000 0.7691 0.01243 0.00547 -0.0290 0.0493 0.9984
6.250 0.7918 0.01276 0.00578 -0.0283 0.0424 1.0000
6.500 0.8107 0.01309 0.00610 -0.0268 0.0365 1.0000
6.750 0.8302 0.01343 0.00644 -0.0254 0.0321 1.0000
7.000 0.8498 0.01379 0.00681 -0.0241 0.0286 1.0000
7.250 0.8700 0.01413 0.00718 -0.0228 0.0250 1.0000
7.500 0.8895 0.01456 0.00759 -0.0215 0.0212 1.0000
7.750 0.9095 0.01496 0.00802 -0.0203 0.0178 1.0000
8.000 0.9286 0.01545 0.00853 -0.0190 0.0145 1.0000
8.250 0.9475 0.01594 0.00904 -0.0177 0.0123 1.0000
8.500 0.9657 0.01651 0.00963 -0.0162 0.0108 1.0000
8.750 0.9842 0.01703 0.01022 -0.0148 0.0099 1.0000
9.000 1.0020 0.01760 0.01084 -0.0134 0.0093 1.0000
9.250 1.0181 0.01821 0.01151 -0.0117 0.0087 1.0000
9.500 1.0322 0.01891 0.01228 -0.0096 0.0083 1.0000
9.750 1.0446 0.01973 0.01317 -0.0074 0.0079 1.0000
10.000 1.0587 0.02044 0.01398 -0.0054 0.0077 1.0000
10.250 1.0718 0.02125 0.01488 -0.0035 0.0075 1.0000
10.500 1.0848 0.02208 0.01581 -0.0016 0.0074 1.0000
10.750 1.0967 0.02302 0.01686 0.0004 0.0071 1.0000
11.000 1.1082 0.02400 0.01795 0.0023 0.0069 1.0000
11.250 1.1196 0.02499 0.01904 0.0040 0.0066 1.0000
11.500 1.1309 0.02599 0.02014 0.0057 0.0064 1.0000
11.750 1.1400 0.02719 0.02147 0.0076 0.0063 1.0000
12.000 1.1500 0.02829 0.02265 0.0092 0.0060 1.0000
12.250 1.1567 0.02969 0.02417 0.0110 0.0058 1.0000
12.500 1.1613 0.03128 0.02588 0.0128 0.0057 1.0000
12.750 1.1636 0.03312 0.02785 0.0146 0.0056 1.0000
13.000 1.1651 0.03508 0.02996 0.0163 0.0055 1.0000
13.250 1.1590 0.03787 0.03293 0.0181 0.0054 1.0000
13.500 1.1573 0.04031 0.03554 0.0194 0.0053 1.0000
13.750 1.1573 0.04265 0.03804 0.0202 0.0053 1.0000
14.000 1.1557 0.04526 0.04082 0.0208 0.0052 1.0000
14.250 1.1451 0.04908 0.04483 0.0211 0.0052 1.0000
14.500 1.1402 0.05242 0.04834 0.0207 0.0052 1.0000
14.750 1.1313 0.05653 0.05263 0.0199 0.0051 1.0000
15.000 1.1219 0.06104 0.05731 0.0184 0.0051 1.0000
15.250 1.1101 0.06632 0.06277 0.0161 0.0050 1.0000
15.500 1.0931 0.07293 0.06957 0.0128 0.0050 1.0000
15.750 1.0729 0.08067 0.07748 0.0085 0.0051 1.0000
16.000 1.0551 0.08871 0.08569 0.0037 0.0051 1.0000
16.250 1.0313 0.09862 0.09577 -0.0023 0.0051 1.0000
16.500 1.0006 0.11055 0.10787 -0.0092 0.0052 1.0000
16.750 0.9785 0.12098 0.11842 -0.0151 0.0052 1.0000
17.000 0.9448 0.13441 0.13197 -0.0224 0.0053 1.0000
17.250 0.9117 0.14863 0.14631 -0.0299 0.0055 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8065 (11% version of S8064) (s8065-il)