GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 797 AIRFOIL (goe797-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.55 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe797-il-1000000-n5.txt Download as CSV file: xf-goe797-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 797 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7973 0.09378 0.09110 -0.0765 1.0000 0.0269
-17.000 -0.8665 0.07999 0.07714 -0.0852 1.0000 0.0270
-16.750 -1.0933 0.04117 0.03770 -0.1135 1.0000 0.0265
-16.500 -1.1080 0.03317 0.02944 -0.1236 0.9907 0.0266
-16.250 -1.1045 0.03009 0.02621 -0.1265 0.9815 0.0267
-16.000 -1.0999 0.02811 0.02410 -0.1269 0.9714 0.0269
-15.750 -1.0957 0.02667 0.02255 -0.1256 0.9614 0.0270
-15.500 -1.0908 0.02558 0.02135 -0.1236 0.9527 0.0272
-15.250 -1.0793 0.02462 0.02029 -0.1222 0.9458 0.0274
-15.000 -1.0645 0.02375 0.01932 -0.1212 0.9397 0.0275
-14.750 -1.0480 0.02298 0.01845 -0.1202 0.9333 0.0277
-14.500 -1.0297 0.02228 0.01766 -0.1194 0.9278 0.0278
-14.250 -1.0125 0.02142 0.01672 -0.1185 0.9217 0.0282
-14.000 -0.9941 0.02065 0.01586 -0.1177 0.9162 0.0285
-13.750 -0.9735 0.01997 0.01511 -0.1171 0.9111 0.0288
-13.500 -0.9520 0.01935 0.01443 -0.1165 0.9053 0.0291
-13.250 -0.9299 0.01879 0.01380 -0.1160 0.8994 0.0294
-13.000 -0.9067 0.01826 0.01321 -0.1156 0.8939 0.0297
-12.750 -0.8831 0.01777 0.01265 -0.1152 0.8877 0.0300
-12.500 -0.8592 0.01731 0.01211 -0.1148 0.8818 0.0303
-12.250 -0.8345 0.01686 0.01160 -0.1146 0.8756 0.0306
-12.000 -0.8097 0.01644 0.01110 -0.1143 0.8680 0.0309
-11.750 -0.7845 0.01604 0.01063 -0.1140 0.8607 0.0313
-11.500 -0.7590 0.01567 0.01018 -0.1138 0.8518 0.0316
-11.250 -0.7331 0.01533 0.00976 -0.1136 0.8436 0.0319
-11.000 -0.7076 0.01493 0.00928 -0.1133 0.8335 0.0323
-10.750 -0.6820 0.01454 0.00883 -0.1131 0.8229 0.0329
-10.500 -0.6560 0.01421 0.00842 -0.1129 0.8105 0.0334
-10.000 -0.6031 0.01365 0.00770 -0.1126 0.7840 0.0344
-9.750 -0.5762 0.01340 0.00738 -0.1125 0.7731 0.0350
-9.250 -0.5217 0.01294 0.00676 -0.1124 0.7541 0.0360
-8.750 -0.4669 0.01246 0.00616 -0.1123 0.7383 0.0373
-8.500 -0.4393 0.01223 0.00588 -0.1124 0.7311 0.0381
-8.250 -0.4114 0.01202 0.00564 -0.1124 0.7255 0.0390
-8.000 -0.3831 0.01182 0.00540 -0.1125 0.7204 0.0400
-7.750 -0.3549 0.01164 0.00519 -0.1126 0.7153 0.0409
-7.250 -0.2982 0.01126 0.00473 -0.1128 0.7062 0.0429
-7.000 -0.2697 0.01107 0.00453 -0.1130 0.7016 0.0442
-6.750 -0.2412 0.01091 0.00435 -0.1131 0.6972 0.0455
-6.500 -0.2126 0.01078 0.00417 -0.1133 0.6932 0.0467
-6.250 -0.1836 0.01063 0.00400 -0.1135 0.6900 0.0478
-6.000 -0.1548 0.01045 0.00382 -0.1137 0.6864 0.0495
-5.750 -0.1260 0.01030 0.00366 -0.1139 0.6824 0.0514
-5.500 -0.0971 0.01018 0.00352 -0.1140 0.6785 0.0532
-5.000 -0.0393 0.00991 0.00324 -0.1145 0.6712 0.0576
-4.750 -0.0102 0.00979 0.00311 -0.1147 0.6661 0.0601
-4.500 0.0187 0.00970 0.00299 -0.1149 0.6610 0.0622
-4.250 0.0474 0.00959 0.00288 -0.1150 0.6566 0.0660
-4.000 0.0767 0.00948 0.00278 -0.1153 0.6531 0.0700
-3.750 0.1058 0.00937 0.00268 -0.1156 0.6483 0.0749
-3.500 0.1347 0.00928 0.00260 -0.1158 0.6433 0.0803
-3.250 0.1637 0.00922 0.00253 -0.1160 0.6395 0.0854
-3.000 0.1930 0.00912 0.00247 -0.1163 0.6360 0.0922
-2.750 0.2223 0.00906 0.00241 -0.1165 0.6311 0.0966
-2.500 0.2513 0.00900 0.00236 -0.1167 0.6257 0.1032
-2.250 0.2802 0.00897 0.00232 -0.1169 0.6208 0.1086
-2.000 0.3096 0.00893 0.00228 -0.1172 0.6155 0.1121
-1.750 0.3386 0.00889 0.00225 -0.1174 0.6095 0.1174
-1.500 0.3673 0.00888 0.00222 -0.1176 0.6039 0.1224
-1.250 0.3967 0.00885 0.00220 -0.1179 0.5993 0.1264
-1.000 0.4259 0.00884 0.00218 -0.1181 0.5946 0.1294
-0.750 0.4546 0.00882 0.00216 -0.1183 0.5895 0.1347
-0.500 0.4836 0.00880 0.00215 -0.1186 0.5846 0.1394
-0.250 0.5126 0.00880 0.00215 -0.1188 0.5784 0.1439
0.000 0.5411 0.00881 0.00215 -0.1189 0.5721 0.1504
0.250 0.5700 0.00879 0.00215 -0.1192 0.5668 0.1566
0.750 0.6269 0.00882 0.00218 -0.1194 0.5536 0.1697
1.000 0.6556 0.00882 0.00220 -0.1196 0.5465 0.1789
1.250 0.6833 0.00883 0.00224 -0.1197 0.5381 0.1982
1.500 0.7114 0.00879 0.00228 -0.1198 0.5294 0.2322
1.750 0.7387 0.00880 0.00235 -0.1198 0.5193 0.2687
2.250 0.7927 0.00883 0.00250 -0.1197 0.4934 0.3466
2.500 0.8183 0.00881 0.00262 -0.1195 0.4763 0.4307
2.750 0.8431 0.00878 0.00278 -0.1192 0.4571 0.5335
3.000 0.8668 0.00883 0.00297 -0.1186 0.4340 0.6281
3.250 0.8896 0.00893 0.00318 -0.1178 0.4097 0.7181
3.500 0.9107 0.00901 0.00343 -0.1165 0.3879 0.8165
3.750 0.9280 0.00904 0.00367 -0.1141 0.3723 0.9207
4.000 0.9576 0.00923 0.00385 -0.1145 0.3589 0.9880
4.250 0.9866 0.00945 0.00401 -0.1150 0.3490 1.0000
4.500 1.0103 0.00968 0.00418 -0.1143 0.3399 1.0000
4.750 1.0348 0.00987 0.00434 -0.1138 0.3334 1.0000
5.000 1.0592 0.01006 0.00450 -0.1132 0.3276 1.0000
5.250 1.0831 0.01027 0.00468 -0.1126 0.3227 1.0000
5.500 1.1074 0.01045 0.00484 -0.1120 0.3190 1.0000
5.750 1.1316 0.01062 0.00501 -0.1114 0.3150 1.0000
6.000 1.1542 0.01085 0.00521 -0.1106 0.3092 1.0000
6.250 1.1753 0.01111 0.00543 -0.1094 0.3033 1.0000
6.500 1.1976 0.01129 0.00562 -0.1084 0.3006 1.0000
6.750 1.2192 0.01149 0.00583 -0.1074 0.2975 1.0000
7.000 1.2405 0.01172 0.00606 -0.1063 0.2941 1.0000
7.250 1.2607 0.01202 0.00634 -0.1050 0.2895 1.0000
7.500 1.2817 0.01229 0.00661 -0.1040 0.2851 1.0000
7.750 1.3034 0.01255 0.00687 -0.1030 0.2806 1.0000
8.000 1.3241 0.01285 0.00717 -0.1020 0.2761 1.0000
8.250 1.3437 0.01321 0.00752 -0.1007 0.2716 1.0000
8.500 1.3649 0.01351 0.00783 -0.0998 0.2672 1.0000
8.750 1.3848 0.01388 0.00819 -0.0987 0.2609 1.0000
9.000 1.4030 0.01433 0.00862 -0.0974 0.2542 1.0000
9.250 1.4218 0.01476 0.00904 -0.0962 0.2454 1.0000
9.500 1.4375 0.01536 0.00958 -0.0946 0.2328 1.0000
9.750 1.4480 0.01625 0.01035 -0.0923 0.2116 1.0000
10.000 1.4533 0.01744 0.01139 -0.0893 0.1860 1.0000
10.500 1.4722 0.01953 0.01334 -0.0849 0.1592 1.0000
10.750 1.4847 0.02043 0.01422 -0.0833 0.1519 1.0000
11.000 1.4982 0.02131 0.01509 -0.0818 0.1458 1.0000
11.250 1.5112 0.02224 0.01602 -0.0803 0.1404 1.0000
11.500 1.5263 0.02305 0.01685 -0.0792 0.1367 1.0000
11.750 1.5396 0.02399 0.01780 -0.0778 0.1320 1.0000
12.000 1.5506 0.02511 0.01891 -0.0764 0.1265 1.0000
12.250 1.5644 0.02606 0.01988 -0.0752 0.1223 1.0000
12.500 1.5756 0.02722 0.02103 -0.0739 0.1170 1.0000
12.750 1.5859 0.02847 0.02228 -0.0726 0.1121 1.0000
13.000 1.5989 0.02955 0.02339 -0.0715 0.1090 1.0000
13.250 1.6094 0.03084 0.02470 -0.0704 0.1044 1.0000
13.500 1.6173 0.03238 0.02623 -0.0690 0.0988 1.0000
13.750 1.6271 0.03379 0.02765 -0.0679 0.0940 1.0000
14.000 1.6331 0.03555 0.02939 -0.0666 0.0877 1.0000
14.250 1.6401 0.03725 0.03111 -0.0655 0.0828 1.0000
14.500 1.6469 0.03899 0.03286 -0.0644 0.0782 1.0000
14.750 1.6508 0.04103 0.03489 -0.0632 0.0731 1.0000
15.000 1.6565 0.04296 0.03685 -0.0622 0.0688 1.0000
15.250 1.6574 0.04534 0.03921 -0.0610 0.0634 1.0000
15.500 1.6596 0.04763 0.04152 -0.0600 0.0582 1.0000
15.750 1.6594 0.05023 0.04412 -0.0589 0.0535 1.0000
16.000 1.6589 0.05290 0.04681 -0.0580 0.0489 1.0000
16.250 1.6590 0.05554 0.04947 -0.0571 0.0444 1.0000
16.500 1.6561 0.05855 0.05249 -0.0563 0.0398 1.0000
16.750 1.6514 0.06183 0.05579 -0.0555 0.0346 1.0000
17.000 1.6442 0.06545 0.05942 -0.0549 0.0288 1.0000
17.250 1.6356 0.06933 0.06332 -0.0543 0.0236 1.0000
17.500 1.6288 0.07303 0.06706 -0.0539 0.0204 1.0000
17.750 1.6240 0.07659 0.07067 -0.0537 0.0184 1.0000
18.000 1.6196 0.08017 0.07432 -0.0536 0.0172 1.0000
18.250 1.6158 0.08374 0.07796 -0.0536 0.0163 1.0000
18.500 1.6110 0.08745 0.08173 -0.0537 0.0155 1.0000
18.750 1.6068 0.09110 0.08545 -0.0539 0.0148 1.0000
19.000 1.6027 0.09481 0.08924 -0.0543 0.0144 1.0000
19.250 1.5977 0.09870 0.09320 -0.0548 0.0139 1.0000
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