GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 100,000 Max Cl/Cd: 37.57 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe766-il-100000.txt Download as CSV file: xf-goe766-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5361 0.09226 0.08697 -0.0047 1.0000 0.1784
-9.000 -0.5271 0.08921 0.08393 -0.0043 1.0000 0.1826
-8.750 -0.7353 0.06201 0.05580 -0.0211 1.0000 0.1127
-8.500 -0.7097 0.05809 0.05217 -0.0214 1.0000 0.1148
-8.250 -0.7458 0.04936 0.04227 -0.0172 1.0000 0.0997
-8.000 -0.7344 0.04550 0.03829 -0.0159 1.0000 0.0989
-7.750 -0.7247 0.04212 0.03467 -0.0140 1.0000 0.0982
-7.500 -0.7145 0.03911 0.03133 -0.0118 1.0000 0.0980
-7.250 -0.7036 0.03658 0.02838 -0.0094 1.0000 0.0989
-7.000 -0.6903 0.03445 0.02583 -0.0070 1.0000 0.0997
-6.750 -0.6735 0.03186 0.02308 -0.0054 1.0000 0.1008
-6.500 -0.6543 0.02997 0.02108 -0.0040 1.0000 0.1023
-6.250 -0.6340 0.02850 0.01953 -0.0026 1.0000 0.1043
-6.000 -0.6137 0.02725 0.01816 -0.0011 1.0000 0.1076
-5.750 -0.5933 0.02595 0.01661 0.0005 1.0000 0.1107
-5.500 -0.5718 0.02456 0.01501 0.0020 1.0000 0.1135
-5.250 -0.5495 0.02332 0.01389 0.0031 1.0000 0.1174
-5.000 -0.5281 0.02247 0.01299 0.0045 1.0000 0.1232
-4.750 -0.5062 0.02141 0.01191 0.0058 1.0000 0.1292
-4.500 -0.4850 0.02056 0.01115 0.0072 1.0000 0.1365
-4.250 -0.4644 0.01966 0.01031 0.0087 1.0000 0.1462
-4.000 -0.4448 0.01887 0.00959 0.0103 1.0000 0.1597
-3.750 -0.4270 0.01797 0.00891 0.0121 1.0000 0.1780
-3.500 -0.4111 0.01712 0.00830 0.0143 1.0000 0.2075
-3.250 -0.3981 0.01619 0.00780 0.0167 1.0000 0.2486
-3.000 -0.3866 0.01541 0.00750 0.0192 1.0000 0.3087
-2.750 -0.3799 0.01459 0.00746 0.0224 1.0000 0.4225
-2.500 -0.3339 0.01373 0.00794 0.0198 0.9821 0.6944
-2.250 -0.2722 0.01386 0.00841 0.0158 0.9614 0.8126
-2.000 -0.1937 0.01450 0.00904 0.0094 0.9430 0.8798
-1.750 -0.1121 0.01487 0.00923 0.0015 0.9134 0.9066
-1.500 -0.0217 0.01512 0.00921 -0.0083 0.8642 0.9197
-1.250 0.0469 0.01537 0.00907 -0.0143 0.7984 0.9342
-1.000 0.1094 0.01578 0.00906 -0.0195 0.7403 0.9559
-0.750 0.1762 0.01592 0.00878 -0.0262 0.6937 0.9747
-0.500 0.2324 0.01581 0.00836 -0.0317 0.6573 0.9907
-0.250 0.2752 0.01563 0.00795 -0.0351 0.6280 1.0000
0.000 0.2931 0.01566 0.00781 -0.0338 0.6073 1.0000
0.250 0.3112 0.01572 0.00771 -0.0325 0.5882 1.0000
0.500 0.3296 0.01579 0.00764 -0.0312 0.5703 1.0000
0.750 0.3483 0.01589 0.00763 -0.0298 0.5534 1.0000
1.000 0.3673 0.01601 0.00765 -0.0285 0.5374 1.0000
1.250 0.3866 0.01616 0.00770 -0.0272 0.5222 1.0000
1.500 0.4062 0.01634 0.00777 -0.0259 0.5077 1.0000
1.750 0.4264 0.01655 0.00784 -0.0246 0.4945 1.0000
2.000 0.4465 0.01675 0.00801 -0.0234 0.4807 1.0000
2.250 0.4668 0.01703 0.00825 -0.0221 0.4682 1.0000
2.500 0.4876 0.01734 0.00846 -0.0209 0.4574 1.0000
2.750 0.5082 0.01762 0.00872 -0.0196 0.4457 1.0000
3.000 0.5289 0.01798 0.00908 -0.0184 0.4354 1.0000
3.250 0.5504 0.01833 0.00934 -0.0172 0.4263 1.0000
3.500 0.5710 0.01874 0.00981 -0.0159 0.4162 1.0000
3.750 0.5929 0.01910 0.01006 -0.0147 0.4080 1.0000
4.000 0.6134 0.01955 0.01063 -0.0135 0.3984 1.0000
4.250 0.6356 0.01991 0.01087 -0.0123 0.3905 1.0000
4.500 0.6558 0.02037 0.01146 -0.0110 0.3809 1.0000
4.750 0.6784 0.02072 0.01169 -0.0099 0.3731 1.0000
5.000 0.6984 0.02120 0.01233 -0.0085 0.3636 1.0000
5.250 0.7214 0.02153 0.01252 -0.0074 0.3559 1.0000
5.500 0.7410 0.02201 0.01318 -0.0060 0.3460 1.0000
5.750 0.7642 0.02230 0.01332 -0.0049 0.3379 1.0000
6.000 0.7837 0.02267 0.01385 -0.0034 0.3271 1.0000
6.250 0.8051 0.02301 0.01417 -0.0021 0.3175 1.0000
6.500 0.8271 0.02319 0.01432 -0.0009 0.3073 1.0000
6.750 0.8466 0.02362 0.01486 0.0006 0.2962 1.0000
7.000 0.8685 0.02389 0.01506 0.0018 0.2859 1.0000
7.250 0.8896 0.02413 0.01529 0.0032 0.2745 1.0000
7.500 0.9081 0.02458 0.01584 0.0048 0.2620 1.0000
7.750 0.9275 0.02499 0.01627 0.0063 0.2494 1.0000
8.000 0.9472 0.02537 0.01660 0.0077 0.2365 1.0000
8.250 0.9670 0.02577 0.01690 0.0092 0.2234 1.0000
8.500 0.9848 0.02621 0.01732 0.0109 0.2095 1.0000
8.750 1.0005 0.02679 0.01799 0.0128 0.1958 1.0000
9.000 1.0161 0.02752 0.01881 0.0146 0.1830 1.0000
9.250 1.0317 0.02833 0.01966 0.0164 0.1718 1.0000
9.500 1.0493 0.02912 0.02035 0.0179 0.1625 1.0000
9.750 1.0646 0.03000 0.02130 0.0197 0.1535 1.0000
10.000 1.0791 0.03124 0.02263 0.0214 0.1462 1.0000
10.250 1.0960 0.03224 0.02360 0.0228 0.1396 1.0000
10.500 1.1100 0.03378 0.02523 0.0243 0.1342 1.0000
10.750 1.1221 0.03517 0.02677 0.0261 0.1290 1.0000
11.000 1.1450 0.03659 0.02795 0.0265 0.1242 1.0000
11.250 1.1482 0.03856 0.03033 0.0290 0.1210 1.0000
11.500 1.1539 0.04047 0.03248 0.0311 0.1176 1.0000
11.750 1.1671 0.04198 0.03401 0.0324 0.1142 1.0000
12.000 1.1823 0.04418 0.03618 0.0332 0.1111 1.0000
12.250 1.1717 0.04672 0.03911 0.0362 0.1096 1.0000
12.500 1.1557 0.04942 0.04210 0.0395 0.1084 1.0000
12.750 1.1349 0.05254 0.04547 0.0421 0.1076 1.0000
13.000 1.1071 0.05666 0.04985 0.0431 0.1072 1.0000
13.250 1.0644 0.06306 0.05653 0.0412 0.1076 1.0000
13.500 0.9895 0.07563 0.06939 0.0334 0.1096 1.0000
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Polar data table (+)
Polar graphs
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