GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 100,000 Max Cl/Cd: 65.12 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe483-il-100000-n5.txt Download as CSV file: xf-goe483-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 483 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2838 0.10009 0.09576 -0.0268 1.0000 0.0314
-7.000 -0.2885 0.09887 0.09464 -0.0262 1.0000 0.0315
-6.750 -0.2951 0.09784 0.09370 -0.0255 1.0000 0.0316
-6.500 -0.2843 0.09530 0.09119 -0.0292 0.9964 0.0317
-6.250 -0.2575 0.09054 0.08643 -0.0361 0.9892 0.0319
-6.000 -0.2483 0.08471 0.08062 -0.0318 0.9862 0.0336
-5.750 -0.2214 0.08062 0.07650 -0.0373 0.9786 0.0355
-5.500 -0.1911 0.07645 0.07230 -0.0442 0.9696 0.0368
-5.250 -0.1580 0.07234 0.06813 -0.0517 0.9607 0.0384
-5.000 -0.1002 0.06856 0.06415 -0.0677 0.9529 0.0414
-4.750 -0.0627 0.06452 0.06000 -0.0751 0.9444 0.0416
-4.250 -0.0188 0.05482 0.05023 -0.0790 0.9310 0.0284
-4.000 0.0197 0.05042 0.04571 -0.0855 0.9249 0.0261
-3.750 0.0564 0.04659 0.04172 -0.0909 0.9167 0.0267
-3.500 0.0971 0.04253 0.03747 -0.0966 0.9102 0.0278
-3.250 0.1356 0.03846 0.03316 -0.1013 0.9026 0.0272
-3.000 0.1766 0.03416 0.02855 -0.1058 0.8961 0.0269
-2.750 0.2162 0.02958 0.02356 -0.1095 0.8887 0.0273
-2.500 0.2587 0.02389 0.01705 -0.1132 0.8830 0.0301
-2.250 0.2919 0.02067 0.01306 -0.1143 0.8750 0.0331
-2.000 0.3232 0.01910 0.01108 -0.1147 0.8674 0.0387
-1.750 0.3533 0.01794 0.00963 -0.1149 0.8592 0.0484
-1.500 0.3817 0.01723 0.00868 -0.1147 0.8498 0.0629
-1.250 0.4111 0.01648 0.00771 -0.1145 0.8412 0.0764
-1.000 0.4392 0.01612 0.00714 -0.1142 0.8314 0.0956
-0.750 0.4665 0.01564 0.00659 -0.1137 0.8206 0.1118
-0.500 0.4933 0.01535 0.00627 -0.1132 0.8097 0.1313
-0.250 0.5203 0.01526 0.00611 -0.1126 0.7986 0.1557
0.000 0.5473 0.01519 0.00593 -0.1121 0.7871 0.1790
0.250 0.5737 0.01509 0.00577 -0.1115 0.7741 0.1979
0.500 0.6000 0.01497 0.00558 -0.1108 0.7610 0.2166
0.750 0.6263 0.01486 0.00540 -0.1102 0.7477 0.2359
1.000 0.6523 0.01474 0.00524 -0.1096 0.7339 0.2548
1.250 0.6784 0.01465 0.00511 -0.1091 0.7197 0.2779
1.500 0.7045 0.01454 0.00501 -0.1085 0.7051 0.3020
1.750 0.7305 0.01443 0.00494 -0.1081 0.6901 0.3357
2.250 0.7839 0.01339 0.00484 -0.1071 0.6591 1.0000
2.500 0.8095 0.01355 0.00490 -0.1065 0.6428 1.0000
2.750 0.8351 0.01372 0.00497 -0.1059 0.6264 1.0000
3.000 0.8606 0.01391 0.00507 -0.1052 0.6101 1.0000
3.250 0.8861 0.01412 0.00520 -0.1046 0.5943 1.0000
3.500 0.9114 0.01436 0.00541 -0.1040 0.5789 1.0000
3.750 0.9367 0.01463 0.00562 -0.1034 0.5640 1.0000
4.000 0.9618 0.01492 0.00588 -0.1028 0.5493 1.0000
4.250 0.9868 0.01524 0.00622 -0.1022 0.5348 1.0000
4.500 1.0116 0.01558 0.00657 -0.1016 0.5202 1.0000
4.750 1.0362 0.01593 0.00695 -0.1009 0.5056 1.0000
5.000 1.0608 0.01629 0.00738 -0.1003 0.4911 1.0000
5.250 1.0852 0.01667 0.00788 -0.0996 0.4767 1.0000
5.500 1.1095 0.01705 0.00838 -0.0990 0.4625 1.0000
5.750 1.1325 0.01744 0.00883 -0.0980 0.4430 1.0000
6.000 1.1510 0.01782 0.00916 -0.0963 0.3961 1.0000
6.250 1.1679 0.01848 0.00960 -0.0945 0.3378 1.0000
6.500 1.1804 0.01977 0.01040 -0.0924 0.2418 1.0000
6.750 1.1762 0.02346 0.01247 -0.0889 0.0388 1.0000
7.000 1.1898 0.02514 0.01415 -0.0869 0.0257 1.0000
7.250 1.2053 0.02647 0.01570 -0.0850 0.0211 1.0000
7.500 1.2192 0.02792 0.01739 -0.0831 0.0189 1.0000
7.750 1.2291 0.02962 0.01935 -0.0807 0.0177 1.0000
8.000 1.2327 0.03171 0.02169 -0.0777 0.0167 1.0000
8.250 1.2404 0.03325 0.02340 -0.0752 0.0158 1.0000
8.500 1.2450 0.03485 0.02518 -0.0723 0.0149 1.0000
8.750 1.2483 0.03669 0.02716 -0.0695 0.0142 1.0000
9.000 1.2528 0.03871 0.02930 -0.0669 0.0138 1.0000
9.250 1.2612 0.04083 0.03162 -0.0647 0.0135 1.0000
9.500 1.2755 0.04312 0.03403 -0.0630 0.0131 1.0000
9.750 1.2944 0.04561 0.03669 -0.0617 0.0129 1.0000
10.000 1.3128 0.04840 0.03972 -0.0605 0.0126 1.0000
10.250 1.3253 0.05122 0.04279 -0.0590 0.0121 1.0000
10.500 1.3321 0.05410 0.04592 -0.0574 0.0114 1.0000
10.750 1.3352 0.05714 0.04920 -0.0558 0.0109 1.0000
11.000 1.3346 0.06041 0.05275 -0.0541 0.0106 1.0000
11.250 1.3309 0.06392 0.05654 -0.0526 0.0105 1.0000
11.500 1.3246 0.06764 0.06057 -0.0513 0.0106 1.0000
11.750 1.3159 0.07161 0.06483 -0.0505 0.0106 1.0000
12.000 1.3045 0.07595 0.06947 -0.0503 0.0107 1.0000
12.250 1.2908 0.08065 0.07445 -0.0507 0.0108 1.0000
12.500 1.2759 0.08580 0.07987 -0.0518 0.0109 1.0000
12.750 1.2603 0.09137 0.08570 -0.0537 0.0110 1.0000
13.000 1.2440 0.09746 0.09204 -0.0563 0.0111 1.0000
13.250 1.2274 0.10399 0.09879 -0.0596 0.0112 1.0000
13.500 1.2107 0.11104 0.10605 -0.0637 0.0113 1.0000
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Polar data table (+)
Polar graphs
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