GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 797 AIRFOIL (goe797-il) Reynolds number: 500,000 Max Cl/Cd: 96.67 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe797-il-500000-n5.txt Download as CSV file: xf-goe797-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7790 0.07476 0.07124 -0.0886 1.0000 0.0319
-15.500 -0.8411 0.06248 0.05877 -0.0962 1.0000 0.0319
-15.000 -0.9087 0.04118 0.03696 -0.1164 0.9931 0.0319
-14.750 -0.9121 0.03566 0.03126 -0.1235 0.9849 0.0321
-14.500 -0.9094 0.03253 0.02798 -0.1264 0.9769 0.0324
-14.250 -0.9025 0.03043 0.02577 -0.1274 0.9699 0.0326
-14.000 -0.8970 0.02896 0.02420 -0.1263 0.9612 0.0328
-13.750 -0.8866 0.02776 0.02289 -0.1254 0.9541 0.0331
-13.500 -0.8730 0.02668 0.02172 -0.1245 0.9473 0.0333
-13.250 -0.8578 0.02572 0.02066 -0.1236 0.9409 0.0336
-13.000 -0.8413 0.02484 0.01968 -0.1228 0.9343 0.0340
-12.750 -0.8234 0.02400 0.01874 -0.1220 0.9288 0.0343
-12.500 -0.8049 0.02321 0.01785 -0.1212 0.9222 0.0347
-12.250 -0.7851 0.02247 0.01699 -0.1204 0.9160 0.0351
-12.000 -0.7645 0.02178 0.01619 -0.1198 0.9096 0.0355
-11.750 -0.7429 0.02114 0.01543 -0.1192 0.9029 0.0360
-11.500 -0.7206 0.02053 0.01470 -0.1186 0.8971 0.0364
-11.250 -0.6989 0.01984 0.01394 -0.1181 0.8900 0.0369
-11.000 -0.6765 0.01921 0.01324 -0.1175 0.8830 0.0374
-10.750 -0.6529 0.01867 0.01264 -0.1171 0.8754 0.0378
-10.500 -0.6288 0.01818 0.01207 -0.1167 0.8673 0.0384
-10.250 -0.6040 0.01772 0.01153 -0.1164 0.8595 0.0389
-10.000 -0.5791 0.01728 0.01100 -0.1161 0.8509 0.0396
-9.750 -0.5537 0.01685 0.01049 -0.1158 0.8422 0.0402
-9.500 -0.5282 0.01645 0.00998 -0.1155 0.8323 0.0409
-9.250 -0.5023 0.01608 0.00951 -0.1153 0.8219 0.0415
-9.000 -0.4770 0.01565 0.00900 -0.1150 0.8114 0.0423
-8.750 -0.4509 0.01528 0.00857 -0.1148 0.8008 0.0432
-8.500 -0.4244 0.01498 0.00819 -0.1147 0.7914 0.0442
-8.250 -0.3977 0.01469 0.00782 -0.1145 0.7819 0.0452
-8.000 -0.3708 0.01442 0.00746 -0.1144 0.7732 0.0462
-7.750 -0.3437 0.01417 0.00711 -0.1143 0.7646 0.0471
-7.500 -0.3168 0.01386 0.00674 -0.1142 0.7571 0.0483
-7.250 -0.2896 0.01359 0.00642 -0.1142 0.7499 0.0496
-7.000 -0.2621 0.01337 0.00614 -0.1142 0.7441 0.0510
-6.750 -0.2342 0.01315 0.00588 -0.1142 0.7384 0.0525
-6.500 -0.2062 0.01297 0.00563 -0.1143 0.7327 0.0540
-6.250 -0.1787 0.01274 0.00535 -0.1143 0.7275 0.0560
-6.000 -0.1505 0.01253 0.00513 -0.1144 0.7226 0.0581
-5.750 -0.1223 0.01235 0.00492 -0.1145 0.7177 0.0602
-5.500 -0.0939 0.01221 0.00472 -0.1146 0.7134 0.0620
-5.250 -0.0658 0.01202 0.00452 -0.1147 0.7095 0.0649
-5.000 -0.0372 0.01185 0.00435 -0.1148 0.7054 0.0682
-4.750 -0.0086 0.01172 0.00420 -0.1150 0.7011 0.0713
-4.500 0.0198 0.01157 0.00405 -0.1151 0.6970 0.0758
-4.250 0.0483 0.01146 0.00392 -0.1153 0.6935 0.0803
-4.000 0.0771 0.01135 0.00380 -0.1154 0.6894 0.0850
-3.750 0.1057 0.01123 0.00371 -0.1156 0.6842 0.0911
-3.500 0.1343 0.01116 0.00361 -0.1157 0.6790 0.0962
-3.000 0.1917 0.01100 0.00346 -0.1161 0.6704 0.1082
-2.750 0.2206 0.01095 0.00339 -0.1162 0.6653 0.1123
-2.500 0.2491 0.01088 0.00332 -0.1164 0.6606 0.1182
-2.250 0.2777 0.01084 0.00326 -0.1165 0.6565 0.1236
-2.000 0.3068 0.01079 0.00321 -0.1167 0.6521 0.1278
-1.750 0.3355 0.01073 0.00316 -0.1169 0.6473 0.1326
-1.500 0.3640 0.01068 0.00311 -0.1170 0.6422 0.1379
-1.250 0.3925 0.01066 0.00306 -0.1171 0.6368 0.1425
-1.000 0.4211 0.01061 0.00302 -0.1173 0.6306 0.1471
-0.750 0.4494 0.01057 0.00299 -0.1174 0.6250 0.1537
-0.500 0.4779 0.01056 0.00296 -0.1175 0.6209 0.1598
-0.250 0.5066 0.01049 0.00294 -0.1177 0.6166 0.1671
0.000 0.5351 0.01046 0.00293 -0.1179 0.6118 0.1750
0.250 0.5633 0.01043 0.00292 -0.1180 0.6071 0.1849
0.500 0.5916 0.01039 0.00293 -0.1181 0.6024 0.1998
0.750 0.6198 0.01031 0.00295 -0.1183 0.5966 0.2287
1.000 0.6474 0.01023 0.00298 -0.1183 0.5904 0.2686
1.250 0.6751 0.01015 0.00301 -0.1184 0.5846 0.3110
1.500 0.7026 0.01004 0.00306 -0.1185 0.5780 0.3665
1.750 0.7290 0.00984 0.00312 -0.1184 0.5715 0.4674
2.000 0.7551 0.00952 0.00322 -0.1183 0.5647 0.6075
2.250 0.7792 0.00925 0.00334 -0.1175 0.5570 0.7386
2.500 0.8014 0.00909 0.00347 -0.1161 0.5494 0.8405
2.750 0.8236 0.00909 0.00359 -0.1145 0.5402 0.9153
3.000 0.8560 0.00918 0.00368 -0.1154 0.5299 0.9645
3.250 0.8955 0.00934 0.00378 -0.1181 0.5173 1.0000
3.500 0.9189 0.00952 0.00388 -0.1173 0.5037 1.0000
3.750 0.9416 0.00974 0.00401 -0.1163 0.4874 1.0000
4.000 0.9633 0.01002 0.00417 -0.1152 0.4671 1.0000
4.250 0.9836 0.01035 0.00438 -0.1139 0.4444 1.0000
4.500 1.0031 0.01073 0.00462 -0.1124 0.4231 1.0000
4.750 1.0227 0.01109 0.00487 -0.1109 0.4044 1.0000
5.000 1.0423 0.01146 0.00514 -0.1095 0.3883 1.0000
5.250 1.0630 0.01177 0.00539 -0.1083 0.3762 1.0000
5.500 1.0833 0.01208 0.00565 -0.1070 0.3667 1.0000
5.750 1.1020 0.01240 0.00592 -0.1054 0.3575 1.0000
6.000 1.1209 0.01270 0.00619 -0.1038 0.3506 1.0000
6.250 1.1405 0.01300 0.00647 -0.1024 0.3447 1.0000
6.500 1.1585 0.01337 0.00681 -0.1008 0.3386 1.0000
6.750 1.1789 0.01368 0.00712 -0.0996 0.3328 1.0000
7.000 1.1982 0.01404 0.00746 -0.0983 0.3268 1.0000
7.250 1.2163 0.01446 0.00786 -0.0968 0.3215 1.0000
7.500 1.2371 0.01478 0.00820 -0.0958 0.3174 1.0000
7.750 1.2574 0.01514 0.00857 -0.0947 0.3130 1.0000
8.000 1.2762 0.01557 0.00900 -0.0935 0.3083 1.0000
8.250 1.2936 0.01607 0.00948 -0.0920 0.3036 1.0000
8.500 1.3145 0.01642 0.00988 -0.0912 0.2995 1.0000
8.750 1.3338 0.01686 0.01033 -0.0901 0.2945 1.0000
9.000 1.3514 0.01739 0.01086 -0.0888 0.2900 1.0000
9.250 1.3692 0.01792 0.01141 -0.0876 0.2859 1.0000
9.500 1.3887 0.01837 0.01190 -0.0866 0.2808 1.0000
9.750 1.4058 0.01896 0.01250 -0.0854 0.2746 1.0000
10.000 1.4219 0.01962 0.01316 -0.0841 0.2687 1.0000
10.250 1.4392 0.02022 0.01379 -0.0830 0.2610 1.0000
10.500 1.4532 0.02103 0.01458 -0.0815 0.2522 1.0000
10.750 1.4669 0.02188 0.01542 -0.0801 0.2409 1.0000
11.000 1.4783 0.02291 0.01640 -0.0784 0.2265 1.0000
11.250 1.4847 0.02429 0.01769 -0.0763 0.2061 1.0000
11.500 1.4876 0.02595 0.01924 -0.0740 0.1863 1.0000
11.750 1.4924 0.02755 0.02078 -0.0720 0.1733 1.0000
12.000 1.4989 0.02908 0.02227 -0.0703 0.1643 1.0000
12.250 1.5056 0.03062 0.02381 -0.0687 0.1569 1.0000
12.500 1.5150 0.03201 0.02522 -0.0674 0.1514 1.0000
12.750 1.5237 0.03350 0.02673 -0.0662 0.1459 1.0000
13.000 1.5306 0.03518 0.02841 -0.0648 0.1410 1.0000
13.250 1.5415 0.03652 0.02980 -0.0639 0.1367 1.0000
13.500 1.5498 0.03813 0.03144 -0.0628 0.1318 1.0000
13.750 1.5557 0.03997 0.03329 -0.0617 0.1271 1.0000
14.000 1.5656 0.04149 0.03487 -0.0609 0.1234 1.0000
14.250 1.5736 0.04320 0.03661 -0.0600 0.1189 1.0000
14.500 1.5790 0.04516 0.03859 -0.0590 0.1143 1.0000
14.750 1.5851 0.04709 0.04056 -0.0581 0.1103 1.0000
15.000 1.5923 0.04894 0.04246 -0.0574 0.1061 1.0000
15.250 1.5962 0.05114 0.04469 -0.0566 0.1013 1.0000
15.500 1.5991 0.05349 0.04706 -0.0558 0.0970 1.0000
15.750 1.6040 0.05565 0.04928 -0.0551 0.0925 1.0000
16.000 1.6048 0.05827 0.05191 -0.0544 0.0874 1.0000
16.250 1.6056 0.06095 0.05462 -0.0538 0.0829 1.0000
16.500 1.6067 0.06362 0.05733 -0.0533 0.0783 1.0000
16.750 1.6037 0.06683 0.06056 -0.0528 0.0735 1.0000
17.000 1.6035 0.06974 0.06351 -0.0524 0.0695 1.0000
17.250 1.6006 0.07301 0.06682 -0.0521 0.0654 1.0000
17.500 1.5973 0.07639 0.07025 -0.0519 0.0618 1.0000
17.750 1.5933 0.07991 0.07382 -0.0519 0.0578 1.0000
18.000 1.5872 0.08375 0.07771 -0.0519 0.0543 1.0000
18.250 1.5817 0.08754 0.08155 -0.0520 0.0504 1.0000
18.500 1.5742 0.09164 0.08570 -0.0523 0.0466 1.0000
18.750 1.5660 0.09592 0.09003 -0.0527 0.0426 1.0000
19.000 1.5567 0.10042 0.09458 -0.0534 0.0382 1.0000
19.250 1.5462 0.10514 0.09934 -0.0542 0.0337 1.0000
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