GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 50,000 Max Cl/Cd: 29.42 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe629-il-50000.txt Download as CSV file: xf-goe629-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 629 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3738 0.11868 0.11067 -0.0258 1.0000 0.3253
-9.750 -0.3323 0.11225 0.10413 -0.0249 1.0000 0.3345
-9.500 -0.3668 0.11312 0.10518 -0.0238 1.0000 0.3435
-9.250 -0.3285 0.10741 0.09937 -0.0231 1.0000 0.3525
-9.000 -0.3526 0.10695 0.09906 -0.0216 1.0000 0.3623
-8.750 -0.3300 0.10332 0.09539 -0.0204 1.0000 0.3750
-8.500 -0.3299 0.10080 0.09293 -0.0190 1.0000 0.3839
-8.250 -0.3531 0.10079 0.09305 -0.0163 1.0000 0.3965
-8.000 -0.3249 0.09630 0.08851 -0.0157 1.0000 0.4049
-7.750 -0.3434 0.09530 0.08764 -0.0129 1.0000 0.4172
-7.500 -0.3489 0.09405 0.08646 -0.0100 1.0000 0.4321
-7.250 -0.3265 0.09048 0.08287 -0.0090 1.0000 0.4445
-7.000 -0.3316 0.08862 0.08109 -0.0063 1.0000 0.4567
-6.750 -0.3540 0.08799 0.08060 -0.0021 1.0000 0.4708
-6.500 -0.3536 0.08628 0.07893 0.0007 1.0000 0.4860
-6.250 -0.3376 0.08336 0.07601 0.0022 1.0000 0.5003
-6.000 -0.5758 0.06449 0.05715 -0.0149 1.0000 0.2736
-5.750 -0.5731 0.06068 0.05322 -0.0146 1.0000 0.2678
-5.500 -0.5739 0.05609 0.04841 -0.0151 1.0000 0.2622
-5.250 -0.5709 0.05213 0.04415 -0.0154 1.0000 0.2612
-5.000 -0.5629 0.04901 0.04075 -0.0152 1.0000 0.2622
-4.750 -0.5524 0.04621 0.03766 -0.0149 1.0000 0.2637
-4.500 -0.5399 0.04363 0.03474 -0.0146 1.0000 0.2654
-4.250 -0.5263 0.04137 0.03206 -0.0142 1.0000 0.2696
-4.000 -0.5114 0.03963 0.03008 -0.0134 1.0000 0.2744
-3.750 -0.4954 0.03848 0.02886 -0.0123 1.0000 0.2793
-3.500 -0.4790 0.03711 0.02721 -0.0116 1.0000 0.2849
-3.250 -0.4624 0.03587 0.02568 -0.0109 1.0000 0.2918
-3.000 -0.4461 0.03517 0.02500 -0.0097 1.0000 0.2998
-2.750 -0.4287 0.03424 0.02373 -0.0091 1.0000 0.3086
-2.500 -0.4120 0.03360 0.02315 -0.0080 1.0000 0.3169
-2.250 -0.3948 0.03301 0.02238 -0.0073 1.0000 0.3280
-2.000 -0.3778 0.03261 0.02192 -0.0064 1.0000 0.3402
-1.750 -0.3607 0.03221 0.02154 -0.0055 1.0000 0.3518
-1.500 -0.3427 0.03192 0.02120 -0.0049 1.0000 0.3661
-1.250 -0.3247 0.03173 0.02098 -0.0043 1.0000 0.3820
-1.000 -0.2957 0.03191 0.02123 -0.0056 0.9951 0.4034
-0.750 -0.2520 0.03248 0.02182 -0.0094 0.9837 0.4348
-0.500 -0.2101 0.03284 0.02233 -0.0129 0.9722 0.4722
-0.250 -0.1718 0.03300 0.02277 -0.0156 0.9612 0.5239
0.000 -0.0616 0.03202 0.02383 -0.0299 0.9500 1.0000
0.250 -0.0174 0.03306 0.02425 -0.0345 0.9375 1.0000
0.500 0.0180 0.03392 0.02480 -0.0370 0.9242 1.0000
0.750 0.0484 0.03467 0.02533 -0.0386 0.9103 1.0000
1.000 0.0805 0.03547 0.02593 -0.0403 0.8961 1.0000
1.250 0.1135 0.03628 0.02659 -0.0420 0.8821 1.0000
1.500 0.1491 0.03710 0.02727 -0.0440 0.8684 1.0000
1.750 0.1910 0.03794 0.02800 -0.0468 0.8557 1.0000
2.000 0.2119 0.03863 0.02861 -0.0465 0.8415 1.0000
2.250 0.2364 0.03938 0.02929 -0.0466 0.8274 1.0000
2.500 0.2636 0.04017 0.03002 -0.0471 0.8138 1.0000
2.750 0.2962 0.04091 0.03072 -0.0483 0.8002 1.0000
3.000 0.3402 0.04150 0.03129 -0.0508 0.7876 1.0000
3.250 0.3582 0.04232 0.03209 -0.0499 0.7725 1.0000
3.500 0.3793 0.04315 0.03291 -0.0493 0.7575 1.0000
3.750 0.4009 0.04404 0.03380 -0.0489 0.7430 1.0000
4.000 0.4256 0.04488 0.03465 -0.0487 0.7287 1.0000
4.250 0.4554 0.04559 0.03537 -0.0491 0.7149 1.0000
4.500 0.4988 0.04584 0.03568 -0.0507 0.7028 1.0000
4.750 0.5112 0.04703 0.03689 -0.0491 0.6876 1.0000
5.000 0.5243 0.04831 0.03819 -0.0478 0.6729 1.0000
5.250 0.5399 0.04957 0.03948 -0.0467 0.6589 1.0000
5.500 0.5632 0.05048 0.04045 -0.0462 0.6454 1.0000
5.750 0.6078 0.05025 0.04030 -0.0469 0.6331 1.0000
6.000 0.6343 0.05071 0.04085 -0.0462 0.6186 1.0000
6.250 0.6485 0.05182 0.04200 -0.0445 0.6029 1.0000
6.500 0.6622 0.05303 0.04326 -0.0430 0.5876 1.0000
6.750 0.6787 0.05407 0.04438 -0.0415 0.5724 1.0000
7.000 0.6998 0.05477 0.04516 -0.0402 0.5573 1.0000
7.250 0.7287 0.05477 0.04527 -0.0390 0.5423 1.0000
7.500 0.8259 0.04890 0.03967 -0.0397 0.5291 1.0000
7.750 0.8885 0.04613 0.03709 -0.0402 0.5107 1.0000
8.000 0.9368 0.04436 0.03545 -0.0399 0.4897 1.0000
8.250 1.0384 0.03954 0.03068 -0.0443 0.4621 1.0000
8.500 1.0464 0.04032 0.03155 -0.0408 0.4412 1.0000
8.750 1.1017 0.03860 0.02969 -0.0418 0.4131 1.0000
9.000 1.1051 0.03968 0.03085 -0.0378 0.3920 1.0000
9.250 1.1444 0.03900 0.02993 -0.0375 0.3634 1.0000
9.500 1.1473 0.03998 0.03095 -0.0334 0.3412 1.0000
9.750 1.1702 0.03978 0.03041 -0.0314 0.3127 1.0000
10.000 1.1706 0.04079 0.03143 -0.0273 0.2914 1.0000
10.250 1.1784 0.04174 0.03229 -0.0242 0.2703 1.0000
10.500 1.1944 0.04266 0.03296 -0.0221 0.2485 1.0000
10.750 1.1951 0.04413 0.03445 -0.0184 0.2316 1.0000
11.000 1.1967 0.04569 0.03598 -0.0148 0.2155 1.0000
11.250 1.2011 0.04745 0.03769 -0.0118 0.2003 1.0000
11.500 1.2101 0.04942 0.03958 -0.0096 0.1861 1.0000
11.750 1.2030 0.05187 0.04226 -0.0059 0.1774 1.0000
12.000 1.2083 0.05466 0.04513 -0.0039 0.1691 1.0000
12.250 1.2014 0.05756 0.04823 -0.0010 0.1634 1.0000
12.500 1.2138 0.06037 0.05103 0.0000 0.1565 1.0000
12.750 1.1872 0.06414 0.05513 0.0035 0.1550 1.0000
13.000 1.1574 0.06861 0.05990 0.0059 0.1542 1.0000
13.250 1.1209 0.07418 0.06573 0.0072 0.1543 1.0000
13.500 1.0773 0.08135 0.07313 0.0067 0.1555 1.0000
13.750 1.0306 0.09039 0.08232 0.0042 0.1571 1.0000
14.000 0.8034 0.13959 0.13136 -0.0251 0.1868 1.0000
14.250 0.7962 0.14662 0.13838 -0.0279 0.1871 1.0000
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Polar data table (+)
Polar graphs
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