S8064 (s8064-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 200,000 Max Cl/Cd: 68.86 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8064-il-200000.txt Download as CSV file: xf-s8064-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4149 0.08868 0.08559 -0.0469 1.0000 0.0602
-10.500 -0.4262 0.08553 0.08247 -0.0459 1.0000 0.0617
-10.250 -0.4479 0.08000 0.07700 -0.0468 1.0000 0.0609
-10.000 -0.4701 0.07437 0.07142 -0.0480 1.0000 0.0613
-9.750 -0.5059 0.06693 0.06398 -0.0513 1.0000 0.0613
-9.500 -0.5437 0.06184 0.05886 -0.0519 1.0000 0.0611
-9.250 -0.5809 0.05836 0.05533 -0.0501 1.0000 0.0608
-9.000 -0.6169 0.05602 0.05294 -0.0464 1.0000 0.0607
-8.750 -0.6512 0.05430 0.05116 -0.0411 0.9997 0.0605
-8.500 -0.6609 0.04971 0.04640 -0.0411 0.9957 0.0614
-8.250 -0.7819 0.04214 0.03665 -0.0284 0.9929 0.0255
-8.000 -0.7739 0.03767 0.03181 -0.0270 0.9897 0.0249
-7.750 -0.7587 0.03416 0.02787 -0.0262 0.9868 0.0245
-7.500 -0.7364 0.03138 0.02462 -0.0260 0.9844 0.0248
-7.250 -0.7152 0.02970 0.02256 -0.0253 0.9815 0.0254
-7.000 -0.6952 0.02730 0.01984 -0.0244 0.9786 0.0265
-6.750 -0.6702 0.02541 0.01786 -0.0244 0.9761 0.0282
-6.500 -0.6414 0.02400 0.01632 -0.0249 0.9737 0.0295
-6.250 -0.6103 0.02280 0.01501 -0.0258 0.9717 0.0315
-6.000 -0.5889 0.02197 0.01404 -0.0247 0.9682 0.0342
-5.750 -0.5702 0.02064 0.01276 -0.0235 0.9642 0.0406
-5.500 -0.5441 0.01970 0.01181 -0.0236 0.9610 0.0540
-5.250 -0.5146 0.01878 0.01098 -0.0245 0.9584 0.0789
-5.000 -0.4987 0.01819 0.01051 -0.0228 0.9535 0.1047
-4.750 -0.4763 0.01748 0.01004 -0.0224 0.9492 0.1497
-4.500 -0.4509 0.01651 0.00957 -0.0228 0.9459 0.2436
-4.250 -0.4350 0.01558 0.00931 -0.0214 0.9414 0.3829
-4.000 -0.4203 0.01497 0.00922 -0.0191 0.9359 0.5042
-3.750 -0.3935 0.01467 0.00930 -0.0189 0.9324 0.6013
-3.500 -0.3600 0.01473 0.00957 -0.0196 0.9300 0.6738
-3.250 -0.3488 0.01484 0.00970 -0.0161 0.9226 0.7093
-3.000 -0.3177 0.01503 0.00986 -0.0164 0.9189 0.7421
-2.750 -0.2820 0.01527 0.01003 -0.0176 0.9164 0.7685
-2.500 -0.2690 0.01545 0.01019 -0.0144 0.9089 0.7874
-2.250 -0.2387 0.01562 0.01032 -0.0145 0.9051 0.8070
-2.000 -0.2025 0.01581 0.01046 -0.0157 0.9026 0.8248
-1.750 -0.1900 0.01598 0.01061 -0.0124 0.8948 0.8402
-1.500 -0.1589 0.01613 0.01074 -0.0125 0.8910 0.8555
-1.250 -0.1224 0.01630 0.01088 -0.0136 0.8886 0.8701
-1.000 -0.1098 0.01644 0.01101 -0.0103 0.8806 0.8843
-0.750 -0.0755 0.01656 0.01110 -0.0112 0.8770 0.8953
-0.500 -0.0325 0.01665 0.01116 -0.0139 0.8750 0.9028
-0.250 -0.0114 0.01675 0.01124 -0.0125 0.8682 0.9135
0.000 0.0293 0.01687 0.01133 -0.0150 0.8644 0.9194
0.250 0.0678 0.01684 0.01127 -0.0170 0.8615 0.9270
0.500 0.1191 0.01685 0.01127 -0.0215 0.8601 0.9295
0.750 0.1703 0.01681 0.01122 -0.0260 0.8589 0.9322
1.000 0.1881 0.01692 0.01135 -0.0243 0.8489 0.9418
1.250 0.2399 0.01679 0.01124 -0.0289 0.8469 0.9433
1.500 0.2922 0.01656 0.01103 -0.0335 0.8452 0.9447
1.750 0.3306 0.01656 0.01109 -0.0359 0.8373 0.9486
2.000 0.3744 0.01621 0.01077 -0.0387 0.8332 0.9519
2.250 0.4128 0.01573 0.01032 -0.0401 0.8299 0.9562
2.500 0.4533 0.01546 0.01014 -0.0427 0.8201 0.9591
2.750 0.4988 0.01478 0.00950 -0.0453 0.8157 0.9613
3.000 0.5325 0.01435 0.00915 -0.0462 0.8043 0.9662
3.250 0.5649 0.01382 0.00870 -0.0466 0.7931 0.9713
3.500 0.6047 0.01315 0.00809 -0.0484 0.7796 0.9746
3.750 0.6401 0.01260 0.00762 -0.0494 0.7637 0.9793
4.000 0.6737 0.01214 0.00722 -0.0501 0.7458 0.9841
4.250 0.7113 0.01172 0.00684 -0.0518 0.7194 0.9879
4.500 0.7455 0.01146 0.00653 -0.0528 0.6838 0.9925
4.750 0.7786 0.01141 0.00634 -0.0537 0.6321 0.9966
5.000 0.8043 0.01168 0.00632 -0.0534 0.5592 1.0000
5.250 0.8109 0.01221 0.00649 -0.0497 0.4829 1.0000
5.500 0.8100 0.01297 0.00680 -0.0448 0.3942 1.0000
5.750 0.8044 0.01379 0.00719 -0.0393 0.3143 1.0000
6.000 0.7960 0.01453 0.00757 -0.0333 0.2491 1.0000
6.250 0.7882 0.01528 0.00798 -0.0272 0.1953 1.0000
6.500 0.7862 0.01611 0.00851 -0.0223 0.1532 1.0000
6.750 0.7892 0.01694 0.00913 -0.0182 0.1255 1.0000
7.000 0.7965 0.01773 0.00981 -0.0148 0.1075 1.0000
7.250 0.8036 0.01855 0.01055 -0.0114 0.0956 1.0000
7.500 0.8139 0.01933 0.01130 -0.0086 0.0855 1.0000
7.750 0.8273 0.02006 0.01205 -0.0064 0.0762 1.0000
8.000 0.8401 0.02095 0.01292 -0.0043 0.0680 1.0000
8.250 0.8543 0.02174 0.01372 -0.0024 0.0605 1.0000
8.500 0.8702 0.02280 0.01485 -0.0007 0.0541 1.0000
8.750 0.8856 0.02406 0.01603 0.0008 0.0475 1.0000
9.000 0.9029 0.02502 0.01714 0.0022 0.0419 1.0000
9.250 0.9207 0.02642 0.01849 0.0033 0.0373 1.0000
9.500 0.9473 0.02838 0.02065 0.0034 0.0342 1.0000
9.750 0.9696 0.02996 0.02242 0.0041 0.0319 1.0000
10.000 0.9844 0.03111 0.02364 0.0056 0.0297 1.0000
10.250 1.0115 0.03471 0.02741 0.0046 0.0274 1.0000
10.500 1.0219 0.03654 0.02954 0.0069 0.0268 1.0000
10.750 1.0300 0.03891 0.03224 0.0092 0.0264 1.0000
11.000 1.0319 0.04142 0.03509 0.0122 0.0259 1.0000
11.250 1.0288 0.04433 0.03834 0.0154 0.0257 1.0000
11.500 1.0204 0.04742 0.04175 0.0188 0.0256 1.0000
11.750 1.0099 0.05065 0.04526 0.0218 0.0257 1.0000
12.000 0.9945 0.05420 0.04909 0.0247 0.0258 1.0000
12.250 0.9775 0.05802 0.05315 0.0268 0.0260 1.0000
12.500 0.9586 0.06201 0.05736 0.0283 0.0262 1.0000
12.750 0.9362 0.06661 0.06218 0.0290 0.0263 1.0000
13.000 0.9153 0.07158 0.06733 0.0286 0.0266 1.0000
13.250 0.8933 0.07713 0.07302 0.0272 0.0269 1.0000
13.500 0.8681 0.08371 0.07976 0.0246 0.0270 1.0000
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