WORTMANN FX 057-816 (fx057816-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 057-816 (fx057816-il) Reynolds number: 200,000 Max Cl/Cd: 27.11 at α=11.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx057816-il-200000-n5.txt Download as CSV file: xf-fx057816-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 057-816
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2751 0.10601 0.10074 -0.0526 0.6040 0.0192
-11.500 -0.2872 0.09872 0.09350 -0.0561 0.6038 0.0197
-11.250 -0.2942 0.09325 0.08808 -0.0589 0.6034 0.0201
-11.000 -0.2904 0.09037 0.08520 -0.0606 0.6029 0.0205
-10.750 -0.2913 0.08645 0.08132 -0.0628 0.6024 0.0209
-10.500 -0.4623 0.05175 0.04658 -0.0839 0.6033 0.0197
-10.250 -0.5089 0.04562 0.04015 -0.0812 0.6029 0.0196
-10.000 -0.5356 0.03987 0.03389 -0.0786 0.6025 0.0199
-9.750 -0.5290 0.03814 0.03199 -0.0773 0.6019 0.0205
-9.500 -0.5114 0.03772 0.03149 -0.0767 0.6013 0.0211
-9.250 -0.4957 0.03676 0.03039 -0.0759 0.6007 0.0217
-9.000 -0.4826 0.03504 0.02843 -0.0749 0.6002 0.0225
-8.750 -0.4687 0.03308 0.02618 -0.0739 0.5997 0.0235
-8.500 -0.4535 0.03099 0.02373 -0.0729 0.5992 0.0248
-8.250 -0.4357 0.02897 0.02133 -0.0721 0.5985 0.0264
-8.000 -0.4149 0.02808 0.02036 -0.0716 0.5975 0.0282
-7.750 -0.3906 0.02801 0.02027 -0.0714 0.5964 0.0297
-7.500 -0.3664 0.02769 0.01985 -0.0712 0.5953 0.0315
-7.250 -0.3423 0.02711 0.01911 -0.0709 0.5944 0.0342
-7.000 -0.3184 0.02595 0.01765 -0.0705 0.5936 0.0377
-6.750 -0.2939 0.02546 0.01706 -0.0703 0.5928 0.0399
-6.500 -0.2682 0.02567 0.01726 -0.0702 0.5920 0.0420
-6.250 -0.2425 0.02567 0.01716 -0.0701 0.5912 0.0451
-6.000 -0.2167 0.02524 0.01653 -0.0699 0.5904 0.0492
-5.750 -0.1904 0.02511 0.01616 -0.0697 0.5897 0.0519
-5.500 -0.1652 0.02451 0.01555 -0.0697 0.5890 0.0546
-5.250 -0.1392 0.02435 0.01533 -0.0697 0.5884 0.0573
-5.000 -0.1130 0.02410 0.01495 -0.0697 0.5877 0.0604
-4.750 -0.0864 0.02379 0.01449 -0.0696 0.5871 0.0635
-4.500 -0.0595 0.02356 0.01408 -0.0695 0.5864 0.0658
-4.250 -0.0330 0.02303 0.01347 -0.0694 0.5858 0.0675
-4.000 -0.0066 0.02261 0.01305 -0.0694 0.5852 0.0697
-3.750 0.0200 0.02233 0.01272 -0.0694 0.5847 0.0718
-3.500 0.0458 0.02215 0.01255 -0.0693 0.5837 0.0735
-3.250 0.0714 0.02204 0.01244 -0.0692 0.5826 0.0750
-3.000 0.0969 0.02197 0.01237 -0.0692 0.5815 0.0763
-2.750 0.1225 0.02195 0.01233 -0.0691 0.5804 0.0773
-2.500 0.1475 0.02182 0.01225 -0.0690 0.5794 0.0785
-2.250 0.1725 0.02172 0.01220 -0.0689 0.5784 0.0797
-2.000 0.1978 0.02165 0.01217 -0.0688 0.5774 0.0811
-1.750 0.2235 0.02160 0.01213 -0.0687 0.5764 0.0831
-1.500 0.2495 0.02157 0.01210 -0.0687 0.5754 0.0858
-1.250 0.2755 0.02159 0.01210 -0.0687 0.5746 0.0877
-1.000 0.3013 0.02155 0.01208 -0.0687 0.5739 0.0897
-0.750 0.3275 0.02158 0.01210 -0.0688 0.5733 0.0921
-0.500 0.3540 0.02164 0.01214 -0.0688 0.5727 0.0950
-0.250 0.3805 0.02170 0.01220 -0.0689 0.5721 0.0983
0.000 0.4071 0.02176 0.01227 -0.0690 0.5716 0.1034
0.250 0.4337 0.02182 0.01235 -0.0691 0.5711 0.1125
0.500 0.4572 0.02118 0.01248 -0.0692 0.5706 0.3359
0.750 0.4610 0.02121 0.01410 -0.0662 0.5671 0.7132
1.000 0.4788 0.02206 0.01510 -0.0648 0.5650 0.7983
1.250 0.4992 0.02273 0.01579 -0.0638 0.5634 0.8204
1.500 0.5181 0.02332 0.01642 -0.0623 0.5622 0.8412
1.750 0.5372 0.02380 0.01692 -0.0608 0.5611 0.8556
2.000 0.5559 0.02422 0.01736 -0.0592 0.5602 0.8687
2.250 0.5778 0.02452 0.01765 -0.0582 0.5593 0.8794
2.500 0.5975 0.02472 0.01786 -0.0567 0.5586 0.8868
2.750 0.6214 0.02493 0.01806 -0.0561 0.5579 0.8945
3.000 0.6439 0.02512 0.01824 -0.0552 0.5573 0.8986
3.250 0.6663 0.02536 0.01849 -0.0544 0.5568 0.9042
4.750 0.6636 0.03575 0.02938 -0.0425 0.5311 0.9481
5.000 0.6891 0.03604 0.02968 -0.0426 0.5304 0.9522
5.250 0.7190 0.03600 0.02966 -0.0430 0.5298 0.9541
5.500 0.7498 0.03583 0.02950 -0.0435 0.5290 0.9561
6.000 0.7671 0.03923 0.03300 -0.0443 0.5169 0.9737
6.250 0.8010 0.03900 0.03281 -0.0453 0.5162 0.9800
6.750 0.8178 0.04180 0.03569 -0.0450 0.5041 1.0000
7.000 0.8488 0.04150 0.03542 -0.0454 0.5031 1.0000
7.250 0.8806 0.04112 0.03508 -0.0459 0.5023 1.0000
7.750 0.8955 0.04414 0.03820 -0.0452 0.4900 1.0000
8.000 0.9271 0.04370 0.03781 -0.0456 0.4890 1.0000
8.500 0.9520 0.04564 0.03986 -0.0450 0.4762 1.0000
8.750 0.9864 0.04475 0.03904 -0.0454 0.4748 1.0000
9.000 0.9796 0.04746 0.04180 -0.0445 0.4635 1.0000
9.250 1.0092 0.04700 0.04141 -0.0447 0.4615 1.0000
9.500 1.0087 0.04918 0.04366 -0.0440 0.4505 1.0000
9.750 1.0371 0.04871 0.04327 -0.0442 0.4473 1.0000
10.750 1.0939 0.05227 0.04708 -0.0431 0.4043 1.0000
11.000 1.1242 0.05149 0.04633 -0.0432 0.3896 1.0000
11.250 1.2064 0.04464 0.03909 -0.0439 0.3431 1.0000
11.500 1.2198 0.04499 0.03906 -0.0428 0.3037 1.0000
11.750 1.2208 0.04697 0.04083 -0.0418 0.2788 1.0000
12.000 1.2201 0.04930 0.04303 -0.0409 0.2559 1.0000
12.250 1.2199 0.05170 0.04530 -0.0402 0.2340 1.0000
12.500 1.2196 0.05423 0.04771 -0.0397 0.2074 1.0000
12.750 1.2177 0.05700 0.05033 -0.0392 0.1791 1.0000
13.000 1.2145 0.05995 0.05309 -0.0387 0.1493 1.0000
13.250 1.2124 0.06288 0.05585 -0.0384 0.1259 1.0000
13.500 1.2131 0.06557 0.05844 -0.0381 0.1100 1.0000
13.750 1.2160 0.06809 0.06089 -0.0380 0.0966 1.0000
14.000 1.2192 0.07063 0.06339 -0.0380 0.0861 1.0000
14.250 1.2244 0.07301 0.06578 -0.0380 0.0763 1.0000
14.500 1.2300 0.07539 0.06815 -0.0381 0.0652 1.0000
14.750 1.2338 0.07799 0.07074 -0.0382 0.0487 1.0000
15.000 1.2332 0.08116 0.07379 -0.0384 0.0350 1.0000
15.250 1.2353 0.08408 0.07669 -0.0387 0.0298 1.0000
15.500 1.2376 0.08704 0.07968 -0.0390 0.0264 1.0000
15.750 1.2386 0.09023 0.08291 -0.0394 0.0236 1.0000
16.000 1.2436 0.09293 0.08573 -0.0398 0.0223 1.0000
16.250 1.2469 0.09589 0.08881 -0.0403 0.0212 1.0000
16.500 1.2499 0.09894 0.09196 -0.0409 0.0201 1.0000
16.750 1.2518 0.10217 0.09530 -0.0416 0.0192 1.0000
17.000 1.2521 0.10567 0.09887 -0.0424 0.0183 1.0000
17.250 1.2503 0.10950 0.10280 -0.0434 0.0175 1.0000
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