GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 100,000 Max Cl/Cd: 46.53 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe533-il-100000.txt Download as CSV file: xf-goe533-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2722 0.09785 0.09339 -0.0372 1.0000 0.1277
-8.250 -0.3107 0.09856 0.09435 -0.0342 1.0000 0.1287
-8.000 -0.3459 0.09692 0.09289 -0.0449 0.9863 0.1300
-7.750 -0.2942 0.09224 0.08815 -0.0361 0.9901 0.1332
-7.500 -0.2603 0.08820 0.08408 -0.0419 0.9816 0.1411
-7.250 -0.2495 0.08275 0.07865 -0.0537 0.9628 0.1484
-7.000 -0.2096 0.07926 0.07511 -0.0561 0.9569 0.1566
-6.750 -0.1884 0.07347 0.06930 -0.0676 0.9420 0.1661
-6.500 -0.1675 0.06751 0.06325 -0.0820 0.9266 0.1809
-6.250 -0.1256 0.06517 0.06093 -0.0793 0.9232 0.1865
-6.000 -0.1201 0.06055 0.05597 -0.0954 0.9010 0.2137
-5.750 -0.0869 0.05733 0.05294 -0.0912 0.8942 0.2172
-5.500 -0.0648 0.05480 0.05036 -0.0927 0.8824 0.2348
-5.250 -0.0384 0.05241 0.04792 -0.0936 0.8731 0.2534
-5.000 -0.0147 0.03417 0.02738 -0.1145 0.8578 0.1103
-4.750 0.0117 0.03114 0.02344 -0.1147 0.8467 0.1003
-4.500 0.0444 0.02930 0.02126 -0.1153 0.8387 0.0987
-4.250 0.0691 0.02801 0.01967 -0.1147 0.8271 0.0990
-4.000 0.0990 0.02640 0.01776 -0.1148 0.8188 0.1000
-3.750 0.1250 0.02512 0.01630 -0.1143 0.8082 0.1005
-3.500 0.1528 0.02395 0.01499 -0.1139 0.7990 0.1015
-3.250 0.1804 0.02298 0.01394 -0.1134 0.7895 0.1033
-3.000 0.2066 0.02231 0.01321 -0.1128 0.7798 0.1062
-2.750 0.2350 0.02169 0.01249 -0.1123 0.7711 0.1115
-2.500 0.2596 0.02109 0.01190 -0.1114 0.7611 0.1164
-2.250 0.2869 0.02043 0.01129 -0.1107 0.7530 0.1237
-2.000 0.3102 0.02002 0.01094 -0.1097 0.7427 0.1341
-1.750 0.3379 0.01932 0.01033 -0.1093 0.7350 0.1654
-1.500 0.3518 0.01786 0.01067 -0.1067 0.7251 0.5812
-1.250 0.3748 0.01805 0.01087 -0.1043 0.7177 0.6639
-1.000 0.3933 0.01831 0.01119 -0.1018 0.7073 0.7112
-0.750 0.4146 0.01829 0.01115 -0.0991 0.7002 0.7588
-0.500 0.4282 0.01837 0.01135 -0.0953 0.6900 0.8068
-0.250 0.4450 0.01814 0.01115 -0.0914 0.6831 0.8596
0.000 0.4667 0.01811 0.01122 -0.0893 0.6732 0.9118
0.250 0.5269 0.01795 0.01085 -0.0948 0.6650 0.9690
0.500 0.5618 0.01824 0.01104 -0.0977 0.6538 1.0000
0.750 0.5926 0.01842 0.01094 -0.0988 0.6468 1.0000
1.000 0.6170 0.01888 0.01133 -0.0991 0.6362 1.0000
1.250 0.6488 0.01910 0.01130 -0.0999 0.6296 1.0000
1.500 0.6724 0.01961 0.01177 -0.0997 0.6192 1.0000
1.750 0.7033 0.01982 0.01176 -0.1000 0.6125 1.0000
2.000 0.7262 0.02035 0.01229 -0.0996 0.6025 1.0000
2.250 0.7558 0.02060 0.01237 -0.0997 0.5959 1.0000
2.500 0.7789 0.02119 0.01296 -0.0993 0.5872 1.0000
2.750 0.8066 0.02150 0.01317 -0.0992 0.5801 1.0000
3.000 0.8320 0.02197 0.01358 -0.0989 0.5728 1.0000
3.250 0.8569 0.02238 0.01396 -0.0984 0.5646 1.0000
3.500 0.8876 0.02254 0.01397 -0.0986 0.5591 1.0000
3.750 0.9070 0.02325 0.01478 -0.0976 0.5498 1.0000
4.000 0.9374 0.02331 0.01470 -0.0977 0.5438 1.0000
4.250 0.9580 0.02389 0.01536 -0.0967 0.5347 1.0000
4.500 0.9873 0.02392 0.01528 -0.0966 0.5280 1.0000
4.750 1.0095 0.02447 0.01588 -0.0959 0.5204 1.0000
5.000 1.0359 0.02465 0.01603 -0.0955 0.5130 1.0000
5.250 1.0623 0.02488 0.01622 -0.0951 0.5062 1.0000
5.500 1.0848 0.02529 0.01669 -0.0943 0.4981 1.0000
5.750 1.1165 0.02529 0.01657 -0.0945 0.4932 1.0000
6.000 1.1325 0.02622 0.01768 -0.0932 0.4851 1.0000
6.250 1.1606 0.02641 0.01784 -0.0930 0.4793 1.0000
6.500 1.1840 0.02694 0.01842 -0.0924 0.4731 1.0000
6.750 1.2050 0.02752 0.01909 -0.0915 0.4657 1.0000
7.000 1.2381 0.02744 0.01891 -0.0919 0.4605 1.0000
7.250 1.2509 0.02847 0.02015 -0.0901 0.4520 1.0000
7.500 1.2814 0.02847 0.02009 -0.0902 0.4457 1.0000
7.750 1.2982 0.02930 0.02106 -0.0888 0.4378 1.0000
8.000 1.3247 0.02951 0.02128 -0.0884 0.4307 1.0000
8.250 1.3457 0.03014 0.02199 -0.0875 0.4234 1.0000
8.500 1.3678 0.03055 0.02246 -0.0866 0.4152 1.0000
8.750 1.3901 0.03099 0.02295 -0.0858 0.4071 1.0000
9.000 1.4142 0.03110 0.02307 -0.0850 0.3978 1.0000
9.250 1.4303 0.03172 0.02379 -0.0834 0.3882 1.0000
9.500 1.4634 0.03145 0.02339 -0.0837 0.3795 1.0000
9.750 1.4700 0.03248 0.02466 -0.0810 0.3696 1.0000
10.000 1.5005 0.03248 0.02455 -0.0811 0.3613 1.0000
10.250 1.5078 0.03336 0.02563 -0.0785 0.3517 1.0000
10.500 1.5294 0.03375 0.02604 -0.0776 0.3433 1.0000
10.750 1.5418 0.03447 0.02687 -0.0756 0.3348 1.0000
11.000 1.5597 0.03510 0.02755 -0.0743 0.3272 1.0000
11.250 1.5694 0.03585 0.02842 -0.0721 0.3190 1.0000
11.500 1.5855 0.03644 0.02907 -0.0706 0.3116 1.0000
11.750 1.5876 0.03747 0.03025 -0.0675 0.3044 1.0000
12.000 1.6059 0.03778 0.03056 -0.0662 0.2969 1.0000
12.250 1.5950 0.03915 0.03213 -0.0618 0.2901 1.0000
12.500 1.6162 0.03927 0.03220 -0.0608 0.2823 1.0000
12.750 1.5982 0.04132 0.03451 -0.0565 0.2763 1.0000
13.000 1.6189 0.04129 0.03440 -0.0556 0.2678 1.0000
13.250 1.5951 0.04408 0.03748 -0.0519 0.2619 1.0000
13.500 1.6075 0.04442 0.03775 -0.0505 0.2527 1.0000
13.750 1.5834 0.04783 0.04143 -0.0481 0.2461 1.0000
14.000 1.5831 0.04931 0.04290 -0.0467 0.2364 1.0000
14.250 1.5677 0.05245 0.04616 -0.0456 0.2273 1.0000
14.500 1.5515 0.05606 0.04989 -0.0450 0.2177 1.0000
14.750 1.5410 0.05920 0.05301 -0.0446 0.2063 1.0000
15.000 1.5302 0.06256 0.05630 -0.0445 0.1940 1.0000
15.250 1.5199 0.06614 0.05977 -0.0444 0.1811 1.0000
15.500 1.4987 0.07153 0.06527 -0.0453 0.1704 1.0000
15.750 1.4844 0.07626 0.07001 -0.0460 0.1594 1.0000
16.000 1.4757 0.08038 0.07409 -0.0466 0.1493 1.0000
16.250 1.4696 0.08422 0.07788 -0.0473 0.1402 1.0000
16.500 1.4522 0.09021 0.08406 -0.0492 0.1334 1.0000
16.750 1.4503 0.09361 0.08737 -0.0500 0.1260 1.0000
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