FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 50,000 Max Cl/Cd: 1.41 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w270-il-50000.txt Download as CSV file: xf-fx77w270-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6109 0.08627 0.07938 -0.0599 0.7272 0.1484
-11.750 -0.6375 0.08115 0.07408 -0.0601 0.7251 0.1475
-11.500 -0.6670 0.07711 0.06980 -0.0589 0.7233 0.1466
-11.250 -0.6858 0.07322 0.06558 -0.0580 0.7211 0.1461
-11.000 -0.6951 0.06972 0.06170 -0.0572 0.7186 0.1461
-10.750 -0.6964 0.06657 0.05815 -0.0566 0.7159 0.1466
-10.500 -0.6909 0.06376 0.05491 -0.0561 0.7132 0.1475
-10.250 -0.6814 0.06125 0.05191 -0.0556 0.7107 0.1488
-10.000 -0.6528 0.05940 0.05008 -0.0569 0.7077 0.1516
-9.750 -0.6253 0.05778 0.04838 -0.0584 0.7049 0.1552
-9.500 -0.6027 0.05613 0.04639 -0.0595 0.7024 0.1592
-9.250 -0.5704 0.05503 0.04543 -0.0610 0.6997 0.1648
-9.000 -0.5452 0.05400 0.04416 -0.0617 0.6970 0.1718
-8.750 -0.5158 0.05335 0.04365 -0.0624 0.6938 0.1816
-8.500 -0.4898 0.05273 0.04310 -0.0625 0.6909 0.1943
-8.250 -0.4632 0.05223 0.04268 -0.0621 0.6884 0.2097
-8.000 -0.4331 0.05203 0.04274 -0.0629 0.6866 0.2292
-7.750 -0.4041 0.05188 0.04294 -0.0637 0.6856 0.2555
-7.500 -0.3846 0.05158 0.04313 -0.0634 0.6852 0.2923
-7.250 -0.3775 0.05104 0.04347 -0.0616 0.6852 0.3548
-7.000 -0.3233 0.05841 0.05219 -0.0558 0.6834 0.4858
-6.750 -0.2738 0.06575 0.05934 -0.0538 0.6814 0.5283
-6.500 -0.2639 0.06909 0.06256 -0.0514 0.6817 0.5619
-6.250 -0.2191 0.07487 0.06818 -0.0507 0.6817 0.5851
-6.000 -0.1740 0.08009 0.07324 -0.0509 0.6815 0.6097
-5.750 -0.2910 0.07910 0.07259 -0.0421 0.6984 0.6186
-5.500 -0.2897 0.08235 0.07577 -0.0385 0.7061 0.6391
-5.250 -0.7013 0.06458 0.05663 -0.0186 0.9822 0.2764
-5.000 -0.6816 0.06413 0.05844 -0.0174 0.9774 0.4230
-4.750 -0.6576 0.07268 0.06757 -0.0069 0.9599 0.5844
-4.500 -0.6256 0.07758 0.07206 -0.0055 0.9425 0.6390
-4.250 -0.6022 0.08177 0.07608 -0.0004 0.9253 0.6631
-4.000 -0.5803 0.08504 0.07917 0.0040 0.9085 0.6866
-3.750 -0.5584 0.08794 0.08189 0.0080 0.8940 0.7100
-3.500 -0.5236 0.09168 0.08543 0.0101 0.8838 0.7396
-3.250 -0.5090 0.09294 0.08655 0.0141 0.8684 0.7639
-3.000 -0.4418 0.09839 0.09177 0.0110 0.8621 0.7991
-2.750 -0.3970 0.10037 0.09358 0.0092 0.8456 0.8275
-2.500 -0.2770 0.10641 0.09936 -0.0066 0.8314 0.8680
-2.250 -0.2182 0.10881 0.10153 -0.0136 0.8222 0.8961
-2.000 -0.1778 0.10994 0.10251 -0.0181 0.8065 0.9155
-1.750 -0.0733 0.11411 0.10642 -0.0344 0.7988 0.9440
-1.500 -0.0761 0.11329 0.10552 -0.0319 0.7830 0.9522
-1.250 -0.0047 0.11637 0.10840 -0.0428 0.7770 0.9680
-1.000 -0.0193 0.11530 0.10727 -0.0383 0.7617 0.9714
-0.750 0.0505 0.11833 0.11011 -0.0490 0.7551 0.9828
-0.500 0.0374 0.11749 0.10923 -0.0450 0.7404 0.9854
-0.250 0.0832 0.11968 0.11127 -0.0511 0.7341 0.9922
0.000 0.0682 0.11940 0.11094 -0.0469 0.7238 0.9924
0.250 0.0904 0.12036 0.11179 -0.0487 0.7149 0.9952
0.500 0.1357 0.12337 0.11466 -0.0543 0.7107 0.9999
0.750 0.1093 0.12210 0.11338 -0.0485 0.6976 0.9999
1.000 0.1261 0.12318 0.11435 -0.0486 0.6913 0.9999
1.250 0.1542 0.12590 0.11693 -0.0504 0.6882 0.9999
1.500 0.1207 0.12384 0.11489 -0.0438 0.6748 0.9999
1.750 0.1366 0.12505 0.11600 -0.0437 0.6695 0.9999
2.000 0.1618 0.12770 0.11853 -0.0450 0.6666 0.9999
2.250 0.1280 0.12575 0.11659 -0.0387 0.6552 0.9999
2.500 0.1395 0.12670 0.11745 -0.0380 0.6494 0.9999
2.750 0.1605 0.12884 0.11949 -0.0385 0.6460 0.9999
3.000 0.1382 0.12809 0.11874 -0.0340 0.6387 0.9999
3.250 0.1401 0.12837 0.11896 -0.0321 0.6310 0.9999
3.500 0.1554 0.12980 0.12030 -0.0317 0.6265 0.9999
3.750 0.1798 0.13280 0.12321 -0.0325 0.6239 0.9999
4.000 0.1440 0.13021 0.12064 -0.0266 0.6138 0.9999
4.250 0.1524 0.13098 0.12135 -0.0254 0.6079 0.9999
4.500 0.1691 0.13283 0.12312 -0.0251 0.6046 0.9999
4.750 0.1926 0.13629 0.12650 -0.0257 0.6027 0.9999
5.000 0.1494 0.13234 0.12259 -0.0192 0.5930 0.9999
5.250 0.1559 0.13295 0.12315 -0.0178 0.5876 0.9999
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