S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 200,000 Max Cl/Cd: 69 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8065-il-200000.txt Download as CSV file: xf-s8065-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4031 0.11319 0.10986 -0.0319 1.0000 0.0529
-11.500 -0.4175 0.10781 0.10453 -0.0367 1.0000 0.0537
-11.250 -0.4240 0.10271 0.09945 -0.0399 1.0000 0.0539
-11.000 -0.4300 0.09602 0.09280 -0.0413 1.0000 0.0547
-10.750 -0.4190 0.09306 0.08983 -0.0399 1.0000 0.0557
-10.500 -0.4146 0.08957 0.08635 -0.0401 1.0000 0.0568
-10.250 -0.4146 0.08542 0.08223 -0.0411 1.0000 0.0579
-10.000 -0.4190 0.08064 0.07747 -0.0427 1.0000 0.0590
-9.750 -0.4271 0.07527 0.07213 -0.0450 1.0000 0.0598
-9.500 -0.4405 0.06910 0.06600 -0.0481 1.0000 0.0606
-9.250 -0.4672 0.06130 0.05824 -0.0535 1.0000 0.0610
-9.000 -0.4999 0.05685 0.05378 -0.0541 1.0000 0.0604
-8.750 -0.5365 0.05467 0.05161 -0.0505 1.0000 0.0600
-8.500 -0.5730 0.05341 0.05034 -0.0450 1.0000 0.0596
-8.250 -0.6029 0.05156 0.04845 -0.0400 1.0000 0.0595
-8.000 -0.6245 0.04909 0.04591 -0.0362 1.0000 0.0599
-7.750 -0.6418 0.04630 0.04303 -0.0326 1.0000 0.0606
-7.500 -0.6554 0.04332 0.03986 -0.0293 1.0000 0.0618
-7.250 -0.7300 0.03947 0.03433 -0.0206 1.0000 0.0295
-7.000 -0.7210 0.03314 0.02722 -0.0187 0.9977 0.0258
-6.750 -0.6973 0.02905 0.02230 -0.0180 0.9949 0.0241
-6.500 -0.6714 0.02657 0.01943 -0.0181 0.9923 0.0241
-6.250 -0.6452 0.02426 0.01686 -0.0182 0.9896 0.0249
-6.000 -0.6159 0.02267 0.01512 -0.0188 0.9869 0.0259
-5.750 -0.5838 0.02167 0.01400 -0.0200 0.9844 0.0286
-5.500 -0.5540 0.02095 0.01310 -0.0205 0.9814 0.0317
-5.250 -0.5309 0.01912 0.01130 -0.0200 0.9778 0.0359
-5.000 -0.5030 0.01796 0.01009 -0.0203 0.9743 0.0456
-4.750 -0.4713 0.01704 0.00926 -0.0215 0.9715 0.0714
-4.500 -0.4473 0.01640 0.00874 -0.0213 0.9670 0.1031
-4.250 -0.4218 0.01561 0.00826 -0.0215 0.9626 0.1567
-4.000 -0.3942 0.01455 0.00783 -0.0225 0.9591 0.2810
-3.750 -0.3735 0.01364 0.00766 -0.0218 0.9546 0.4497
-3.500 -0.3525 0.01318 0.00764 -0.0206 0.9491 0.5646
-3.250 -0.3230 0.01300 0.00778 -0.0206 0.9455 0.6538
-3.000 -0.2941 0.01308 0.00795 -0.0205 0.9414 0.7116
-2.750 -0.2711 0.01317 0.00804 -0.0192 0.9354 0.7476
-2.500 -0.2383 0.01329 0.00814 -0.0199 0.9317 0.7801
-2.250 -0.2008 0.01344 0.00827 -0.0214 0.9294 0.8061
-2.000 -0.1858 0.01354 0.00834 -0.0185 0.9213 0.8277
-1.750 -0.1519 0.01366 0.00844 -0.0192 0.9179 0.8482
-1.500 -0.1135 0.01379 0.00854 -0.0208 0.9157 0.8678
-1.250 -0.0986 0.01391 0.00867 -0.0177 0.9073 0.8863
-1.000 -0.0604 0.01406 0.00877 -0.0192 0.9044 0.9026
-0.750 -0.0167 0.01418 0.00885 -0.0219 0.9026 0.9154
-0.500 0.0133 0.01432 0.00897 -0.0222 0.8965 0.9277
-0.250 0.0607 0.01443 0.00904 -0.0260 0.8934 0.9337
0.000 0.1032 0.01444 0.00902 -0.0288 0.8904 0.9418
0.250 0.1572 0.01443 0.00898 -0.0340 0.8889 0.9445
0.500 0.2102 0.01435 0.00890 -0.0389 0.8872 0.9472
0.750 0.2421 0.01441 0.00897 -0.0399 0.8790 0.9555
1.000 0.2915 0.01422 0.00881 -0.0441 0.8757 0.9582
1.250 0.3398 0.01396 0.00856 -0.0479 0.8728 0.9610
1.500 0.3741 0.01387 0.00851 -0.0493 0.8634 0.9678
1.750 0.4159 0.01347 0.00816 -0.0516 0.8588 0.9719
2.000 0.4544 0.01321 0.00795 -0.0536 0.8483 0.9770
2.250 0.4883 0.01286 0.00764 -0.0544 0.8383 0.9834
2.500 0.5288 0.01227 0.00711 -0.0563 0.8288 0.9874
2.750 0.5651 0.01175 0.00664 -0.0575 0.8156 0.9930
3.000 0.6018 0.01126 0.00622 -0.0591 0.7975 0.9986
3.250 0.6247 0.01093 0.00595 -0.0579 0.7794 1.0000
3.500 0.6430 0.01062 0.00567 -0.0558 0.7604 1.0000
3.750 0.6606 0.01041 0.00547 -0.0536 0.7362 1.0000
4.000 0.6787 0.01024 0.00527 -0.0514 0.7078 1.0000
4.250 0.6959 0.01020 0.00515 -0.0491 0.6708 1.0000
4.500 0.7114 0.01031 0.00511 -0.0465 0.6236 1.0000
4.750 0.7240 0.01060 0.00516 -0.0435 0.5621 1.0000
5.000 0.7320 0.01114 0.00532 -0.0397 0.4797 1.0000
5.250 0.7356 0.01198 0.00566 -0.0355 0.3814 1.0000
5.500 0.7377 0.01307 0.00617 -0.0312 0.2776 1.0000
5.750 0.7418 0.01425 0.00682 -0.0274 0.1878 1.0000
6.000 0.7501 0.01532 0.00752 -0.0243 0.1355 1.0000
6.250 0.7623 0.01621 0.00825 -0.0217 0.1102 1.0000
6.500 0.7759 0.01708 0.00904 -0.0194 0.0951 1.0000
6.750 0.7914 0.01789 0.00983 -0.0174 0.0836 1.0000
7.000 0.8072 0.01876 0.01070 -0.0155 0.0741 1.0000
7.250 0.8233 0.01967 0.01157 -0.0138 0.0647 1.0000
7.500 0.8415 0.02037 0.01233 -0.0123 0.0571 1.0000
7.750 0.8588 0.02160 0.01360 -0.0107 0.0500 1.0000
8.000 0.8762 0.02295 0.01489 -0.0094 0.0428 1.0000
8.250 0.8967 0.02408 0.01619 -0.0081 0.0380 1.0000
8.500 0.9168 0.02535 0.01750 -0.0071 0.0345 1.0000
8.750 0.9428 0.02851 0.02080 -0.0072 0.0317 1.0000
9.000 0.9608 0.02957 0.02214 -0.0056 0.0296 1.0000
9.250 0.9789 0.03121 0.02402 -0.0043 0.0277 1.0000
9.500 0.9957 0.03335 0.02640 -0.0028 0.0267 1.0000
9.750 1.0091 0.03563 0.02894 -0.0011 0.0259 1.0000
10.000 1.0189 0.03835 0.03197 0.0010 0.0255 1.0000
10.250 1.0236 0.04148 0.03544 0.0036 0.0253 1.0000
10.500 1.0221 0.04482 0.03915 0.0068 0.0253 1.0000
10.750 0.9961 0.04989 0.04482 0.0126 0.0266 1.0000
11.000 0.9716 0.05424 0.04954 0.0171 0.0274 1.0000
11.250 0.9478 0.05857 0.05414 0.0201 0.0281 1.0000
11.500 0.9249 0.06292 0.05872 0.0218 0.0288 1.0000
11.750 0.9006 0.06767 0.06366 0.0223 0.0292 1.0000
12.000 0.8773 0.07284 0.06898 0.0214 0.0296 1.0000
12.250 0.8524 0.07894 0.07522 0.0189 0.0300 1.0000
12.500 0.8271 0.08615 0.08255 0.0146 0.0303 1.0000
12.750 0.8029 0.09470 0.09119 0.0090 0.0309 1.0000
13.000 0.6767 0.10063 0.09743 0.0049 0.0309 1.0000
13.250 0.6571 0.10876 0.10554 0.0011 0.0318 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8065 (11% version of S8064) (s8065-il)