GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.85 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe493-il-1000000-n5.txt Download as CSV file: xf-goe493-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8436 0.08694 0.08389 -0.0737 1.0000 0.0074
-17.250 -0.8800 0.07791 0.07473 -0.0782 1.0000 0.0073
-17.000 -0.9182 0.06895 0.06562 -0.0827 1.0000 0.0073
-16.750 -0.9487 0.06151 0.05805 -0.0863 1.0000 0.0073
-16.500 -0.9707 0.05556 0.05199 -0.0891 1.0000 0.0074
-16.250 -0.9965 0.04943 0.04572 -0.0918 1.0000 0.0073
-16.000 -1.0156 0.04456 0.04074 -0.0936 1.0000 0.0073
-15.500 -1.0244 0.03628 0.03223 -0.0998 0.9986 0.0075
-15.250 -1.0148 0.03300 0.02883 -0.1038 0.9962 0.0076
-15.000 -1.0064 0.03010 0.02582 -0.1068 0.9916 0.0076
-14.750 -0.9937 0.02776 0.02339 -0.1096 0.9873 0.0078
-14.500 -0.9781 0.02576 0.02128 -0.1122 0.9836 0.0079
-14.250 -0.9645 0.02419 0.01962 -0.1134 0.9770 0.0080
-14.000 -0.9440 0.02271 0.01805 -0.1156 0.9731 0.0081
-13.750 -0.9271 0.02125 0.01649 -0.1170 0.9662 0.0084
-13.500 -0.9004 0.02011 0.01526 -0.1193 0.9624 0.0087
-13.250 -0.8728 0.01916 0.01425 -0.1212 0.9579 0.0090
-13.000 -0.8466 0.01837 0.01339 -0.1224 0.9514 0.0094
-12.750 -0.8192 0.01763 0.01257 -0.1238 0.9454 0.0097
-12.500 -0.7976 0.01707 0.01193 -0.1236 0.9366 0.0100
-12.250 -0.7743 0.01652 0.01129 -0.1237 0.9293 0.0103
-12.000 -0.7549 0.01605 0.01076 -0.1228 0.9208 0.0106
-11.750 -0.7359 0.01551 0.01013 -0.1219 0.9133 0.0111
-11.500 -0.7179 0.01505 0.00962 -0.1206 0.9056 0.0115
-11.000 -0.6782 0.01425 0.00869 -0.1186 0.8924 0.0125
-10.750 -0.6573 0.01390 0.00827 -0.1176 0.8861 0.0130
-10.500 -0.6358 0.01357 0.00788 -0.1168 0.8806 0.0135
-10.250 -0.6153 0.01318 0.00744 -0.1157 0.8746 0.0144
-10.000 -0.5936 0.01284 0.00705 -0.1149 0.8689 0.0154
-9.750 -0.5712 0.01253 0.00670 -0.1141 0.8638 0.0165
-9.500 -0.5490 0.01220 0.00634 -0.1133 0.8581 0.0181
-9.250 -0.5263 0.01190 0.00600 -0.1125 0.8527 0.0198
-9.000 -0.5032 0.01159 0.00567 -0.1119 0.8477 0.0222
-8.750 -0.4799 0.01131 0.00536 -0.1112 0.8420 0.0253
-8.500 -0.4567 0.01101 0.00505 -0.1105 0.8366 0.0292
-8.250 -0.4332 0.01072 0.00476 -0.1099 0.8314 0.0336
-8.000 -0.4093 0.01045 0.00448 -0.1093 0.8259 0.0386
-7.750 -0.3853 0.01021 0.00422 -0.1087 0.8205 0.0444
-7.500 -0.3609 0.00995 0.00397 -0.1082 0.8154 0.0513
-7.250 -0.3366 0.00970 0.00375 -0.1076 0.8097 0.0597
-7.000 -0.3121 0.00948 0.00353 -0.1071 0.8042 0.0681
-6.750 -0.2867 0.00929 0.00335 -0.1068 0.7989 0.0752
-6.500 -0.2612 0.00913 0.00318 -0.1064 0.7931 0.0821
-6.250 -0.2360 0.00897 0.00302 -0.1059 0.7874 0.0890
-6.000 -0.2099 0.00883 0.00287 -0.1057 0.7819 0.0960
-5.750 -0.1845 0.00867 0.00272 -0.1053 0.7756 0.1039
-5.500 -0.1584 0.00856 0.00259 -0.1049 0.7697 0.1091
-5.250 -0.1323 0.00844 0.00246 -0.1046 0.7633 0.1153
-5.000 -0.1066 0.00833 0.00234 -0.1043 0.7572 0.1221
-4.750 -0.0805 0.00820 0.00222 -0.1040 0.7511 0.1315
-4.250 -0.0289 0.00798 0.00200 -0.1032 0.7375 0.1518
-4.000 -0.0029 0.00787 0.00190 -0.1029 0.7303 0.1633
-3.750 0.0229 0.00778 0.00182 -0.1025 0.7238 0.1742
-3.500 0.0490 0.00767 0.00174 -0.1022 0.7167 0.1887
-3.000 0.1005 0.00749 0.00159 -0.1015 0.7017 0.2192
-2.750 0.1259 0.00742 0.00153 -0.1010 0.6941 0.2356
-2.500 0.1518 0.00731 0.00147 -0.1006 0.6866 0.2554
-2.000 0.2019 0.00716 0.00138 -0.0996 0.6673 0.3019
-1.750 0.2268 0.00711 0.00135 -0.0990 0.6572 0.3227
-1.500 0.2519 0.00707 0.00134 -0.0985 0.6477 0.3431
-1.250 0.2774 0.00703 0.00132 -0.0980 0.6386 0.3651
-1.000 0.3021 0.00701 0.00133 -0.0974 0.6295 0.3857
-0.750 0.3281 0.00699 0.00133 -0.0971 0.6211 0.4026
-0.500 0.3530 0.00700 0.00134 -0.0965 0.6115 0.4191
-0.250 0.3781 0.00701 0.00136 -0.0960 0.6011 0.4365
0.000 0.4032 0.00701 0.00139 -0.0954 0.5918 0.4574
0.250 0.4282 0.00702 0.00142 -0.0949 0.5838 0.4766
0.500 0.4541 0.00703 0.00146 -0.0945 0.5778 0.4913
0.750 0.4799 0.00705 0.00149 -0.0941 0.5711 0.5037
1.000 0.5051 0.00708 0.00154 -0.0935 0.5649 0.5162
1.250 0.5311 0.00711 0.00158 -0.0932 0.5584 0.5286
1.500 0.5556 0.00715 0.00164 -0.0925 0.5507 0.5426
1.750 0.5811 0.00717 0.00169 -0.0920 0.5442 0.5583
2.000 0.6058 0.00721 0.00176 -0.0914 0.5370 0.5727
2.250 0.6306 0.00725 0.00182 -0.0908 0.5306 0.5859
2.500 0.6554 0.00729 0.00189 -0.0902 0.5232 0.5987
2.750 0.6776 0.00741 0.00198 -0.0891 0.5075 0.6119
3.000 0.7007 0.00748 0.00207 -0.0882 0.4978 0.6274
3.250 0.7233 0.00755 0.00217 -0.0871 0.4875 0.6439
3.750 0.7651 0.00774 0.00240 -0.0844 0.4583 0.6869
4.000 0.7799 0.00795 0.00255 -0.0818 0.4300 0.7110
4.250 0.7947 0.00815 0.00272 -0.0792 0.4049 0.7389
4.750 0.8247 0.00863 0.00315 -0.0741 0.3582 0.7911
5.000 0.8404 0.00883 0.00337 -0.0717 0.3404 0.8195
5.250 0.8554 0.00900 0.00359 -0.0692 0.3245 0.8576
5.500 0.8979 0.00928 0.00398 -0.0728 0.3003 0.9419
5.750 0.9542 0.00981 0.00439 -0.0798 0.2721 1.0000
6.000 0.9682 0.01017 0.00465 -0.0772 0.2513 1.0000
6.250 0.9800 0.01065 0.00497 -0.0743 0.2198 1.0000
6.500 0.9798 0.01163 0.00562 -0.0695 0.1583 1.0000
6.750 0.9898 0.01226 0.00611 -0.0665 0.1296 1.0000
7.000 0.9967 0.01307 0.00671 -0.0631 0.0906 1.0000
7.250 1.0103 0.01362 0.00717 -0.0609 0.0735 1.0000
7.500 1.0243 0.01418 0.00765 -0.0589 0.0589 1.0000
7.750 1.0379 0.01478 0.00817 -0.0568 0.0441 1.0000
8.000 1.0531 0.01532 0.00868 -0.0550 0.0372 1.0000
8.250 1.0702 0.01579 0.00914 -0.0536 0.0344 1.0000
8.500 1.0876 0.01625 0.00961 -0.0522 0.0329 1.0000
8.750 1.1047 0.01674 0.01011 -0.0509 0.0315 1.0000
9.000 1.1210 0.01729 0.01067 -0.0494 0.0303 1.0000
9.250 1.1372 0.01786 0.01126 -0.0480 0.0292 1.0000
9.500 1.1533 0.01846 0.01187 -0.0467 0.0282 1.0000
9.750 1.1703 0.01902 0.01246 -0.0455 0.0276 1.0000
10.000 1.1866 0.01962 0.01310 -0.0443 0.0270 1.0000
10.250 1.2025 0.02027 0.01377 -0.0431 0.0263 1.0000
10.500 1.2177 0.02098 0.01451 -0.0418 0.0256 1.0000
10.750 1.2323 0.02173 0.01528 -0.0406 0.0249 1.0000
11.000 1.2458 0.02257 0.01615 -0.0393 0.0241 1.0000
11.250 1.2584 0.02350 0.01711 -0.0379 0.0234 1.0000
11.500 1.2718 0.02439 0.01804 -0.0367 0.0229 1.0000
11.750 1.2867 0.02520 0.01888 -0.0357 0.0224 1.0000
12.000 1.3012 0.02604 0.01976 -0.0347 0.0217 1.0000
12.250 1.3138 0.02704 0.02080 -0.0336 0.0213 1.0000
12.500 1.3269 0.02802 0.02181 -0.0326 0.0205 1.0000
12.750 1.3388 0.02912 0.02295 -0.0315 0.0199 1.0000
13.000 1.3500 0.03028 0.02415 -0.0305 0.0194 1.0000
13.250 1.3594 0.03162 0.02551 -0.0294 0.0188 1.0000
13.500 1.3707 0.03283 0.02677 -0.0285 0.0182 1.0000
13.750 1.3823 0.03404 0.02803 -0.0277 0.0177 1.0000
14.000 1.3923 0.03543 0.02948 -0.0268 0.0172 1.0000
14.250 1.4019 0.03686 0.03095 -0.0260 0.0165 1.0000
14.500 1.4111 0.03835 0.03248 -0.0252 0.0160 1.0000
14.750 1.4192 0.03997 0.03412 -0.0245 0.0151 1.0000
15.000 1.4268 0.04168 0.03588 -0.0238 0.0146 1.0000
15.250 1.4342 0.04343 0.03769 -0.0232 0.0141 1.0000
15.500 1.4411 0.04526 0.03958 -0.0226 0.0136 1.0000
15.750 1.4472 0.04720 0.04157 -0.0220 0.0130 1.0000
16.000 1.4524 0.04926 0.04366 -0.0216 0.0124 1.0000
16.250 1.4569 0.05142 0.04587 -0.0211 0.0118 1.0000
16.500 1.4611 0.05367 0.04818 -0.0208 0.0114 1.0000
16.750 1.4643 0.05606 0.05064 -0.0205 0.0110 1.0000
17.000 1.4671 0.05850 0.05314 -0.0202 0.0107 1.0000
17.250 1.4691 0.06106 0.05576 -0.0201 0.0102 1.0000
17.500 1.4700 0.06379 0.05855 -0.0200 0.0098 1.0000
17.750 1.4700 0.06668 0.06150 -0.0200 0.0094 1.0000
18.000 1.4696 0.06965 0.06454 -0.0200 0.0091 1.0000
18.250 1.4692 0.07263 0.06760 -0.0202 0.0089 1.0000
18.500 1.4682 0.07573 0.07078 -0.0204 0.0087 1.0000
18.750 1.4662 0.07900 0.07412 -0.0207 0.0084 1.0000
19.000 1.4633 0.08242 0.07763 -0.0211 0.0082 1.0000
19.250 1.4598 0.08596 0.08125 -0.0217 0.0080 1.0000
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Polar data table (+)
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