GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 63 AIRFOIL (goe63-il) Reynolds number: 500,000 Max Cl/Cd: 102.59 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe63-il-500000-n5.txt Download as CSV file: xf-goe63-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 63 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1749 0.09212 0.08896 -0.0351 0.7492 0.0200
-7.500 -0.1652 0.08951 0.08631 -0.0367 0.7404 0.0205
-7.250 -0.1560 0.08689 0.08367 -0.0386 0.7325 0.0211
-7.000 -0.1420 0.08392 0.08066 -0.0423 0.7246 0.0213
-6.750 -0.1255 0.08083 0.07754 -0.0467 0.7180 0.0214
-6.500 -0.1054 0.07757 0.07423 -0.0523 0.7111 0.0215
-6.250 -0.0829 0.07419 0.07078 -0.0584 0.7046 0.0215
-6.000 -0.0617 0.07086 0.06742 -0.0624 0.6985 0.0215
-5.750 -0.0464 0.06806 0.06460 -0.0630 0.6922 0.0217
-5.500 -0.0274 0.06546 0.06195 -0.0650 0.6867 0.0218
-5.250 -0.0055 0.06287 0.05933 -0.0678 0.6813 0.0220
-5.000 0.0186 0.06028 0.05669 -0.0712 0.6748 0.0223
-4.750 0.0445 0.05766 0.05400 -0.0748 0.6683 0.0228
-4.500 0.0725 0.05494 0.05123 -0.0787 0.6618 0.0234
-4.250 0.1094 0.05181 0.04798 -0.0848 0.6557 0.0247
-4.000 0.1499 0.04844 0.04445 -0.0915 0.6503 0.0249
-3.750 0.1859 0.04529 0.04119 -0.0963 0.6448 0.0249
-3.500 0.2199 0.04238 0.03816 -0.1000 0.6394 0.0249
-3.000 0.2733 0.03776 0.03341 -0.1037 0.6287 0.0253
-2.750 0.3018 0.03593 0.03152 -0.1054 0.6230 0.0256
-2.500 0.3322 0.03415 0.02963 -0.1074 0.6173 0.0260
-2.250 0.3642 0.03240 0.02780 -0.1094 0.6114 0.0270
-2.000 0.4071 0.02994 0.02509 -0.1126 0.6053 0.0287
-1.750 0.4425 0.02779 0.02273 -0.1146 0.6004 0.0288
-1.500 0.4768 0.02572 0.02048 -0.1162 0.5962 0.0289
-1.250 0.5097 0.02386 0.01846 -0.1176 0.5915 0.0289
-1.000 0.5417 0.02219 0.01663 -0.1187 0.5861 0.0289
-0.750 0.5688 0.02120 0.01563 -0.1198 0.5806 0.0280
-0.500 0.6014 0.01973 0.01400 -0.1208 0.5747 0.0272
-0.250 0.6343 0.01834 0.01241 -0.1216 0.5689 0.0278
0.000 0.6666 0.01698 0.01084 -0.1223 0.5633 0.0269
0.250 0.7002 0.01528 0.00885 -0.1230 0.5562 0.0262
0.500 0.7317 0.01403 0.00733 -0.1234 0.5484 0.0263
0.750 0.7623 0.01313 0.00624 -0.1237 0.5401 0.0267
1.000 0.7919 0.01250 0.00542 -0.1239 0.5309 0.0271
1.250 0.8212 0.01205 0.00484 -0.1240 0.5191 0.0278
1.500 0.8498 0.01181 0.00444 -0.1240 0.5044 0.0287
1.750 0.8780 0.01165 0.00414 -0.1240 0.4845 0.0289
2.000 0.9057 0.01149 0.00385 -0.1240 0.4575 0.0294
2.250 0.9329 0.01155 0.00377 -0.1239 0.4271 0.0299
2.500 0.9598 0.01170 0.00377 -0.1238 0.3986 0.0306
2.750 0.9868 0.01185 0.00381 -0.1237 0.3753 0.0314
3.000 1.0139 0.01201 0.00387 -0.1236 0.3566 0.0323
3.250 1.0411 0.01217 0.00396 -0.1235 0.3424 0.0336
3.500 1.0683 0.01231 0.00406 -0.1235 0.3299 0.0353
3.750 1.0954 0.01247 0.00418 -0.1234 0.3193 0.0368
4.000 1.1226 0.01262 0.00430 -0.1233 0.3107 0.0386
4.250 1.1496 0.01279 0.00445 -0.1232 0.3021 0.0418
4.500 1.1767 0.01294 0.00461 -0.1231 0.2950 0.0510
4.750 1.2038 0.01307 0.00483 -0.1230 0.2878 0.1032
5.250 1.2504 0.01220 0.00534 -0.1215 0.2740 1.0000
5.750 1.3029 0.01270 0.00577 -0.1211 0.2604 1.0000
6.000 1.3287 0.01299 0.00600 -0.1208 0.2527 1.0000
6.250 1.3545 0.01325 0.00624 -0.1205 0.2451 1.0000
6.500 1.3797 0.01357 0.00652 -0.1202 0.2360 1.0000
6.750 1.4051 0.01386 0.00678 -0.1198 0.2282 1.0000
7.000 1.4296 0.01421 0.00709 -0.1194 0.2196 1.0000
7.250 1.4544 0.01453 0.00739 -0.1190 0.2115 1.0000
7.500 1.4782 0.01491 0.00774 -0.1185 0.2029 1.0000
7.750 1.5020 0.01529 0.00809 -0.1179 0.1941 1.0000
8.000 1.5250 0.01571 0.00849 -0.1173 0.1853 1.0000
8.250 1.5466 0.01623 0.00894 -0.1165 0.1745 1.0000
8.500 1.5686 0.01670 0.00937 -0.1157 0.1650 1.0000
8.750 1.5898 0.01720 0.00986 -0.1148 0.1574 1.0000
9.000 1.6108 0.01768 0.01033 -0.1139 0.1506 1.0000
9.250 1.6308 0.01822 0.01085 -0.1128 0.1441 1.0000
9.500 1.6505 0.01873 0.01137 -0.1117 0.1375 1.0000
9.750 1.6685 0.01934 0.01196 -0.1104 0.1318 1.0000
10.000 1.6871 0.01984 0.01250 -0.1091 0.1269 1.0000
10.250 1.7030 0.02048 0.01313 -0.1075 0.1212 1.0000
10.500 1.7179 0.02111 0.01378 -0.1057 0.1166 1.0000
10.750 1.7307 0.02175 0.01446 -0.1035 0.1126 1.0000
11.000 1.7421 0.02253 0.01526 -0.1012 0.1085 1.0000
11.250 1.7536 0.02337 0.01614 -0.0992 0.1046 1.0000
11.500 1.7652 0.02426 0.01706 -0.0973 0.0997 1.0000
11.750 1.7744 0.02537 0.01818 -0.0953 0.0949 1.0000
12.000 1.7853 0.02643 0.01929 -0.0937 0.0909 1.0000
12.250 1.7942 0.02770 0.02060 -0.0921 0.0857 1.0000
12.500 1.8022 0.02913 0.02205 -0.0905 0.0808 1.0000
12.750 1.8086 0.03076 0.02370 -0.0891 0.0742 1.0000
13.000 1.8123 0.03273 0.02567 -0.0876 0.0655 1.0000
13.250 1.8089 0.03544 0.02832 -0.0860 0.0522 1.0000
13.500 1.7868 0.04016 0.03289 -0.0839 0.0284 1.0000
13.750 1.7760 0.04393 0.03668 -0.0825 0.0206 1.0000
14.000 1.7724 0.04703 0.03985 -0.0816 0.0182 1.0000
14.250 1.7704 0.04998 0.04290 -0.0809 0.0170 1.0000
14.500 1.7682 0.05303 0.04604 -0.0803 0.0161 1.0000
14.750 1.7648 0.05628 0.04940 -0.0798 0.0154 1.0000
15.000 1.7600 0.05978 0.05301 -0.0795 0.0148 1.0000
15.250 1.7556 0.06334 0.05669 -0.0793 0.0144 1.0000
15.500 1.7519 0.06692 0.06038 -0.0793 0.0140 1.0000
15.750 1.7469 0.07076 0.06435 -0.0794 0.0137 1.0000
16.000 1.7405 0.07487 0.06857 -0.0797 0.0134 1.0000
16.250 1.7326 0.07930 0.07314 -0.0802 0.0131 1.0000
16.500 1.7233 0.08406 0.07802 -0.0810 0.0129 1.0000
16.750 1.7125 0.08914 0.08323 -0.0819 0.0127 1.0000
17.000 1.7002 0.09455 0.08877 -0.0831 0.0125 1.0000
17.250 1.6868 0.10028 0.09463 -0.0846 0.0123 1.0000
17.500 1.6721 0.10635 0.10084 -0.0863 0.0122 1.0000
17.750 1.6562 0.11270 0.10733 -0.0883 0.0120 1.0000
18.000 1.6396 0.11931 0.11408 -0.0906 0.0119 1.0000
18.250 1.6227 0.12610 0.12101 -0.0932 0.0118 1.0000
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