S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.55 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8065-il-1000000-n5.txt Download as CSV file: xf-s8065-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8077 0.06217 0.06015 -0.0479 1.0000 0.0029
-13.000 -0.8283 0.05338 0.05120 -0.0548 1.0000 0.0029
-12.750 -0.8516 0.04632 0.04395 -0.0596 1.0000 0.0029
-12.500 -0.8664 0.04177 0.03927 -0.0616 1.0000 0.0029
-12.250 -0.8889 0.03692 0.03417 -0.0624 0.9808 0.0029
-12.000 -0.8776 0.03420 0.03123 -0.0653 0.9562 0.0029
-11.750 -0.8869 0.03178 0.02855 -0.0632 0.9346 0.0029
-11.500 -0.8908 0.03023 0.02681 -0.0602 0.9233 0.0029
-11.250 -0.9018 0.02820 0.02452 -0.0557 0.9141 0.0029
-11.000 -0.8976 0.02678 0.02293 -0.0531 0.9083 0.0030
-10.750 -0.8898 0.02533 0.02127 -0.0510 0.9036 0.0030
-10.500 -0.8771 0.02416 0.01995 -0.0494 0.9003 0.0030
-10.250 -0.8659 0.02259 0.01816 -0.0476 0.8970 0.0030
-10.000 -0.8505 0.02141 0.01681 -0.0462 0.8938 0.0030
-9.750 -0.8321 0.02055 0.01582 -0.0452 0.8910 0.0031
-9.500 -0.8137 0.01962 0.01474 -0.0441 0.8884 0.0031
-9.250 -0.7933 0.01885 0.01385 -0.0433 0.8862 0.0032
-9.000 -0.7714 0.01823 0.01313 -0.0427 0.8838 0.0032
-8.750 -0.7538 0.01694 0.01167 -0.0415 0.8809 0.0033
-8.500 -0.7350 0.01582 0.01040 -0.0403 0.8781 0.0034
-8.250 -0.7146 0.01493 0.00938 -0.0393 0.8757 0.0034
-8.000 -0.6926 0.01423 0.00858 -0.0386 0.8736 0.0035
-7.750 -0.6697 0.01360 0.00786 -0.0379 0.8715 0.0036
-7.500 -0.6461 0.01303 0.00723 -0.0374 0.8693 0.0037
-7.250 -0.6220 0.01252 0.00665 -0.0370 0.8670 0.0038
-7.000 -0.5975 0.01207 0.00614 -0.0365 0.8647 0.0039
-6.750 -0.5727 0.01166 0.00568 -0.0362 0.8624 0.0041
-6.500 -0.5478 0.01128 0.00523 -0.0358 0.8603 0.0043
-6.250 -0.5224 0.01095 0.00483 -0.0355 0.8582 0.0045
-6.000 -0.4965 0.01062 0.00447 -0.0352 0.8561 0.0048
-5.750 -0.4703 0.01034 0.00415 -0.0351 0.8539 0.0051
-5.500 -0.4440 0.01006 0.00384 -0.0349 0.8515 0.0054
-5.250 -0.4178 0.00978 0.00352 -0.0347 0.8491 0.0061
-5.000 -0.3914 0.00954 0.00325 -0.0345 0.8468 0.0071
-4.750 -0.3654 0.00926 0.00298 -0.0343 0.8445 0.0119
-4.500 -0.3395 0.00893 0.00273 -0.0341 0.8422 0.0260
-4.250 -0.3130 0.00867 0.00253 -0.0340 0.8395 0.0395
-4.000 -0.2864 0.00842 0.00235 -0.0339 0.8366 0.0541
-3.750 -0.2598 0.00819 0.00217 -0.0338 0.8338 0.0725
-3.500 -0.2334 0.00794 0.00201 -0.0337 0.8311 0.0957
-3.250 -0.2071 0.00768 0.00184 -0.0336 0.8284 0.1284
-3.000 -0.1811 0.00733 0.00169 -0.0334 0.8251 0.1758
-2.750 -0.1553 0.00699 0.00155 -0.0333 0.8216 0.2306
-2.500 -0.1294 0.00668 0.00141 -0.0331 0.8181 0.2837
-2.250 -0.1036 0.00637 0.00127 -0.0329 0.8149 0.3438
-2.000 -0.0772 0.00610 0.00119 -0.0328 0.8110 0.3956
-1.750 -0.0509 0.00584 0.00110 -0.0326 0.8066 0.4520
-1.500 -0.0243 0.00563 0.00102 -0.0325 0.8023 0.4979
-1.250 0.0026 0.00545 0.00097 -0.0324 0.7976 0.5387
-1.000 0.0297 0.00530 0.00092 -0.0324 0.7917 0.5759
-0.750 0.0565 0.00515 0.00087 -0.0322 0.7858 0.6113
-0.500 0.0834 0.00501 0.00085 -0.0321 0.7779 0.6489
-0.250 0.1101 0.00491 0.00085 -0.0318 0.7688 0.6862
0.000 0.1372 0.00487 0.00084 -0.0317 0.7572 0.7121
0.250 0.1645 0.00486 0.00083 -0.0315 0.7430 0.7301
0.500 0.1917 0.00489 0.00084 -0.0314 0.7267 0.7437
0.750 0.2189 0.00494 0.00085 -0.0313 0.7084 0.7542
1.000 0.2458 0.00502 0.00087 -0.0311 0.6888 0.7631
1.250 0.2726 0.00511 0.00091 -0.0309 0.6663 0.7707
1.500 0.2991 0.00523 0.00096 -0.0307 0.6411 0.7785
1.750 0.3253 0.00537 0.00102 -0.0305 0.6126 0.7852
2.000 0.3510 0.00555 0.00110 -0.0301 0.5774 0.7923
2.250 0.3759 0.00580 0.00119 -0.0297 0.5330 0.7986
2.500 0.4000 0.00611 0.00132 -0.0291 0.4797 0.8052
3.000 0.4479 0.00678 0.00162 -0.0279 0.3741 0.8180
3.250 0.4715 0.00715 0.00180 -0.0274 0.3209 0.8249
3.500 0.4946 0.00754 0.00199 -0.0267 0.2673 0.8316
3.750 0.5170 0.00801 0.00223 -0.0259 0.2050 0.8389
4.000 0.5410 0.00831 0.00242 -0.0254 0.1716 0.8464
4.250 0.5651 0.00860 0.00262 -0.0249 0.1423 0.8546
4.500 0.5888 0.00889 0.00283 -0.0242 0.1146 0.8633
4.750 0.6129 0.00915 0.00304 -0.0237 0.0932 0.8728
5.500 0.6830 0.00988 0.00372 -0.0215 0.0504 0.9174
5.750 0.7085 0.01008 0.00397 -0.0211 0.0434 0.9407
6.000 0.7407 0.01036 0.00426 -0.0223 0.0366 0.9592
6.250 0.7744 0.01071 0.00457 -0.0240 0.0296 0.9728
6.750 0.8381 0.01134 0.00520 -0.0265 0.0220 0.9925
7.000 0.8692 0.01166 0.00552 -0.0276 0.0189 0.9982
7.250 0.8927 0.01204 0.00587 -0.0271 0.0134 1.0000
7.500 0.9121 0.01243 0.00622 -0.0257 0.0100 1.0000
7.750 0.9320 0.01281 0.00661 -0.0244 0.0083 1.0000
8.000 0.9524 0.01317 0.00700 -0.0232 0.0076 1.0000
8.250 0.9731 0.01353 0.00739 -0.0221 0.0072 1.0000
8.500 0.9933 0.01393 0.00783 -0.0209 0.0068 1.0000
8.750 1.0133 0.01435 0.00828 -0.0197 0.0065 1.0000
9.000 1.0329 0.01480 0.00877 -0.0185 0.0062 1.0000
9.250 1.0519 0.01530 0.00933 -0.0172 0.0059 1.0000
9.500 1.0698 0.01587 0.00996 -0.0157 0.0056 1.0000
9.750 1.0865 0.01651 0.01066 -0.0141 0.0053 1.0000
10.000 1.1030 0.01701 0.01122 -0.0124 0.0052 1.0000
10.250 1.1188 0.01750 0.01177 -0.0105 0.0051 1.0000
10.500 1.1343 0.01802 0.01234 -0.0087 0.0050 1.0000
10.750 1.1490 0.01862 0.01301 -0.0069 0.0048 1.0000
11.000 1.1630 0.01928 0.01374 -0.0050 0.0047 1.0000
11.250 1.1768 0.01998 0.01453 -0.0032 0.0045 1.0000
11.500 1.1900 0.02073 0.01535 -0.0014 0.0045 1.0000
11.750 1.2021 0.02156 0.01627 0.0005 0.0044 1.0000
12.000 1.2148 0.02235 0.01713 0.0022 0.0042 1.0000
12.250 1.2260 0.02327 0.01813 0.0040 0.0041 1.0000
12.500 1.2366 0.02424 0.01919 0.0058 0.0040 1.0000
12.750 1.2464 0.02526 0.02030 0.0075 0.0039 1.0000
13.000 1.2547 0.02642 0.02155 0.0094 0.0039 1.0000
13.250 1.2626 0.02764 0.02286 0.0111 0.0038 1.0000
13.500 1.2664 0.02919 0.02453 0.0130 0.0038 1.0000
13.750 1.2707 0.03074 0.02619 0.0147 0.0037 1.0000
14.000 1.2701 0.03274 0.02832 0.0165 0.0035 1.0000
14.250 1.2693 0.03484 0.03056 0.0181 0.0035 1.0000
14.500 1.2609 0.03774 0.03363 0.0197 0.0034 1.0000
14.750 1.2674 0.03937 0.03534 0.0203 0.0034 1.0000
15.000 1.2615 0.04233 0.03845 0.0211 0.0033 1.0000
15.250 1.2644 0.04452 0.04074 0.0214 0.0033 1.0000
15.500 1.2565 0.04804 0.04441 0.0213 0.0033 1.0000
15.750 1.2413 0.05276 0.04930 0.0205 0.0033 1.0000
16.000 1.2470 0.05509 0.05171 0.0199 0.0032 1.0000
16.250 1.2356 0.05996 0.05674 0.0182 0.0032 1.0000
16.500 1.2135 0.06690 0.06385 0.0152 0.0032 1.0000
16.750 1.2064 0.07194 0.06902 0.0126 0.0032 1.0000
17.000 1.1929 0.07842 0.07563 0.0090 0.0032 1.0000
17.250 1.1527 0.09069 0.08811 0.0019 0.0033 1.0000
17.500 1.1329 0.09953 0.09710 -0.0032 0.0032 1.0000
17.750 1.0882 0.11408 0.11183 -0.0114 0.0033 1.0000
18.000 1.0307 0.13204 0.12998 -0.0213 0.0034 1.0000
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Polar data table (+)
Polar graphs
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