GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 100,000 Max Cl/Cd: 47.25 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe255-il-100000-n5.txt Download as CSV file: xf-goe255-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3611 0.11667 0.11171 -0.0642 1.0000 0.0293
-13.750 -0.4742 0.08947 0.08421 -0.0770 1.0000 0.0276
-13.500 -0.5125 0.08101 0.07559 -0.0806 1.0000 0.0273
-13.250 -0.5403 0.07530 0.06976 -0.0823 1.0000 0.0272
-13.000 -0.5648 0.07085 0.06524 -0.0829 1.0000 0.0271
-12.750 -0.5795 0.06638 0.06066 -0.0850 0.9975 0.0273
-12.500 -0.5763 0.06118 0.05528 -0.0908 0.9909 0.0277
-12.250 -0.5689 0.05645 0.05035 -0.0967 0.9841 0.0284
-12.000 -0.5599 0.05211 0.04580 -0.1021 0.9754 0.0293
-11.750 -0.5482 0.04817 0.04159 -0.1071 0.9664 0.0304
-11.500 -0.5345 0.04487 0.03813 -0.1112 0.9565 0.0314
-11.250 -0.5210 0.04200 0.03519 -0.1147 0.9453 0.0325
-11.000 -0.5145 0.03957 0.03263 -0.1162 0.9292 0.0336
-10.750 -0.5117 0.03762 0.03055 -0.1158 0.9120 0.0346
-10.500 -0.5037 0.03586 0.02862 -0.1153 0.8987 0.0359
-10.250 -0.4933 0.03420 0.02680 -0.1149 0.8873 0.0375
-10.000 -0.4830 0.03270 0.02523 -0.1143 0.8762 0.0396
-9.750 -0.4674 0.03130 0.02368 -0.1141 0.8676 0.0428
-9.500 -0.4517 0.02989 0.02218 -0.1138 0.8592 0.0465
-9.250 -0.4344 0.02866 0.02081 -0.1133 0.8511 0.0516
-9.000 -0.4158 0.02739 0.01948 -0.1131 0.8439 0.0588
-8.750 -0.3966 0.02627 0.01828 -0.1128 0.8366 0.0698
-8.500 -0.3759 0.02523 0.01715 -0.1125 0.8294 0.0833
-8.250 -0.3532 0.02431 0.01618 -0.1125 0.8230 0.0985
-8.000 -0.3310 0.02360 0.01543 -0.1122 0.8154 0.1146
-7.750 -0.3052 0.02292 0.01472 -0.1125 0.8098 0.1344
-7.500 -0.2820 0.02251 0.01423 -0.1123 0.8019 0.1570
-7.250 -0.2565 0.02203 0.01373 -0.1124 0.7957 0.1783
-7.000 -0.2314 0.02160 0.01321 -0.1123 0.7894 0.1960
-6.750 -0.2067 0.02121 0.01275 -0.1120 0.7825 0.2117
-6.500 -0.1795 0.02080 0.01225 -0.1121 0.7771 0.2278
-6.250 -0.1551 0.02052 0.01194 -0.1118 0.7702 0.2433
-6.000 -0.1289 0.02027 0.01164 -0.1116 0.7639 0.2595
-5.750 -0.1010 0.02007 0.01139 -0.1117 0.7587 0.2773
-5.500 -0.0763 0.02002 0.01134 -0.1113 0.7512 0.2948
-5.250 -0.0483 0.01996 0.01119 -0.1113 0.7453 0.3135
-5.000 -0.0213 0.01999 0.01109 -0.1112 0.7391 0.3327
-4.750 0.0050 0.02007 0.01110 -0.1109 0.7323 0.3509
-4.500 0.0337 0.02012 0.01100 -0.1110 0.7271 0.3682
-4.250 0.0596 0.02018 0.01094 -0.1107 0.7206 0.3822
-4.000 0.0866 0.02019 0.01081 -0.1106 0.7146 0.3947
-3.750 0.1154 0.02013 0.01067 -0.1107 0.7100 0.4050
-3.500 0.1410 0.02016 0.01060 -0.1105 0.7037 0.4151
-3.250 0.1679 0.02015 0.01052 -0.1104 0.6981 0.4245
-3.000 0.1968 0.02009 0.01034 -0.1106 0.6938 0.4337
-2.750 0.2227 0.02012 0.01032 -0.1104 0.6882 0.4423
-2.500 0.2491 0.02013 0.01028 -0.1102 0.6826 0.4502
-2.250 0.2776 0.02008 0.01015 -0.1104 0.6783 0.4585
-2.000 0.3048 0.02010 0.01010 -0.1104 0.6736 0.4663
-1.750 0.3300 0.02015 0.01016 -0.1101 0.6678 0.4736
-1.500 0.3582 0.02015 0.01005 -0.1102 0.6634 0.4817
-1.250 0.3870 0.02008 0.00995 -0.1104 0.6596 0.4891
-1.000 0.4107 0.02023 0.01010 -0.1099 0.6533 0.4989
-0.750 0.4373 0.02021 0.01010 -0.1097 0.6482 0.5088
-0.500 0.4667 0.02014 0.00996 -0.1100 0.6444 0.5191
-0.250 0.4901 0.02028 0.01016 -0.1094 0.6386 0.5267
0.000 0.5166 0.02034 0.01020 -0.1094 0.6340 0.5341
0.250 0.5449 0.02032 0.01018 -0.1095 0.6305 0.5412
0.500 0.5721 0.02039 0.01021 -0.1096 0.6267 0.5493
0.750 0.5952 0.02053 0.01044 -0.1090 0.6212 0.5569
1.250 0.6512 0.02050 0.01041 -0.1092 0.6133 0.5785
1.500 0.6744 0.02072 0.01071 -0.1086 0.6088 0.5910
1.750 0.6987 0.02089 0.01097 -0.1082 0.6048 0.6063
2.000 0.7250 0.02094 0.01110 -0.1081 0.6012 0.6262
2.250 0.7534 0.02086 0.01109 -0.1081 0.5979 0.6542
2.500 0.7736 0.02101 0.01145 -0.1069 0.5928 0.6912
2.750 0.7942 0.02104 0.01171 -0.1055 0.5880 0.7466
3.000 0.8201 0.02081 0.01175 -0.1046 0.5840 0.8479
3.250 0.8586 0.02081 0.01179 -0.1068 0.5794 1.0000
3.500 0.8785 0.02117 0.01215 -0.1058 0.5735 1.0000
3.750 0.9051 0.02130 0.01221 -0.1058 0.5689 1.0000
4.000 0.9349 0.02138 0.01220 -0.1063 0.5653 1.0000
4.250 0.9511 0.02191 0.01279 -0.1047 0.5597 1.0000
4.500 0.9746 0.02218 0.01306 -0.1042 0.5548 1.0000
4.750 1.0038 0.02225 0.01307 -0.1046 0.5506 1.0000
5.000 1.0217 0.02269 0.01356 -0.1032 0.5447 1.0000
5.250 1.0426 0.02301 0.01390 -0.1023 0.5387 1.0000
5.500 1.0724 0.02304 0.01387 -0.1027 0.5338 1.0000
5.750 1.0858 0.02360 0.01451 -0.1006 0.5269 1.0000
6.000 1.1075 0.02388 0.01481 -0.0998 0.5207 1.0000
6.250 1.1345 0.02401 0.01492 -0.0998 0.5153 1.0000
6.500 1.1435 0.02466 0.01568 -0.0971 0.5074 1.0000
6.750 1.1695 0.02478 0.01578 -0.0968 0.5011 1.0000
7.000 1.1745 0.02545 0.01656 -0.0934 0.4925 1.0000
7.250 1.1951 0.02564 0.01673 -0.0924 0.4843 1.0000
7.500 1.1955 0.02653 0.01773 -0.0885 0.4735 1.0000
7.750 1.2072 0.02707 0.01830 -0.0864 0.4634 1.0000
8.000 1.2153 0.02780 0.01910 -0.0839 0.4525 1.0000
8.250 1.2164 0.02900 0.02039 -0.0809 0.4401 1.0000
8.500 1.2211 0.03013 0.02158 -0.0785 0.4279 1.0000
8.750 1.2279 0.03122 0.02271 -0.0765 0.4158 1.0000
9.000 1.2367 0.03225 0.02374 -0.0748 0.4037 1.0000
9.250 1.2465 0.03326 0.02473 -0.0732 0.3921 1.0000
9.500 1.2560 0.03440 0.02588 -0.0717 0.3816 1.0000
9.750 1.2691 0.03529 0.02674 -0.0705 0.3729 1.0000
10.000 1.2821 0.03624 0.02767 -0.0694 0.3649 1.0000
10.250 1.2956 0.03720 0.02862 -0.0683 0.3579 1.0000
10.500 1.3083 0.03826 0.02969 -0.0672 0.3512 1.0000
10.750 1.3240 0.03905 0.03045 -0.0663 0.3445 1.0000
11.000 1.3318 0.04052 0.03197 -0.0650 0.3363 1.0000
11.250 1.3433 0.04160 0.03299 -0.0638 0.3272 1.0000
11.500 1.3488 0.04323 0.03461 -0.0624 0.3172 1.0000
11.750 1.3539 0.04492 0.03633 -0.0611 0.3078 1.0000
12.000 1.3616 0.04638 0.03777 -0.0599 0.2986 1.0000
12.250 1.3637 0.04848 0.03998 -0.0588 0.2908 1.0000
12.500 1.3687 0.05030 0.04186 -0.0577 0.2830 1.0000
12.750 1.3691 0.05264 0.04431 -0.0567 0.2748 1.0000
13.000 1.3685 0.05508 0.04681 -0.0558 0.2656 1.0000
13.250 1.3639 0.05816 0.05003 -0.0550 0.2563 1.0000
13.500 1.3622 0.06091 0.05284 -0.0544 0.2471 1.0000
13.750 1.3567 0.06432 0.05641 -0.0540 0.2371 1.0000
14.000 1.3519 0.06775 0.05997 -0.0537 0.2268 1.0000
14.250 1.3468 0.07127 0.06357 -0.0535 0.2156 1.0000
14.500 1.3416 0.07489 0.06725 -0.0534 0.2037 1.0000
14.750 1.3353 0.07870 0.07107 -0.0534 0.1910 1.0000
15.250 1.3208 0.08668 0.07901 -0.0537 0.1683 1.0000
15.500 1.3140 0.09071 0.08305 -0.0540 0.1594 1.0000
15.750 1.3058 0.09500 0.08735 -0.0544 0.1512 1.0000
16.000 1.2991 0.09922 0.09165 -0.0549 0.1429 1.0000
16.250 1.2894 0.10390 0.09638 -0.0557 0.1348 1.0000
16.500 1.2795 0.10877 0.10133 -0.0567 0.1242 1.0000
16.750 1.2700 0.11369 0.10633 -0.0579 0.1130 1.0000
17.000 1.2607 0.11866 0.11135 -0.0592 0.1019 1.0000
17.250 1.2496 0.12395 0.11668 -0.0608 0.0907 1.0000
17.500 1.2384 0.12937 0.12209 -0.0626 0.0810 1.0000
17.750 1.2272 0.13490 0.12761 -0.0646 0.0699 1.0000
18.000 1.2120 0.14120 0.13382 -0.0672 0.0430 1.0000
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Polar data table (+)
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