GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.65 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe803h-il-1000000.txt Download as CSV file: xf-goe803h-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 803 (HACKLINGER) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2533 0.10504 0.10342 -0.0244 1.0000 0.0133
-8.250 -0.2491 0.10268 0.10108 -0.0244 1.0000 0.0139
-8.000 -0.2454 0.10031 0.09873 -0.0247 0.9999 0.0143
-7.750 -0.1047 0.07682 0.07528 -0.0497 0.9582 0.0145
-7.500 -0.0812 0.07215 0.07058 -0.0536 0.9413 0.0147
-7.250 -0.0645 0.06879 0.06709 -0.0563 0.9134 0.0148
-7.000 -0.0554 0.06629 0.06450 -0.0571 0.8922 0.0150
-6.750 -0.0467 0.06382 0.06197 -0.0579 0.8760 0.0153
-6.500 -0.0378 0.06128 0.05939 -0.0588 0.8614 0.0156
-6.250 -0.0270 0.05854 0.05660 -0.0604 0.8475 0.0162
-6.000 -0.0137 0.05552 0.05353 -0.0629 0.8328 0.0169
-5.750 0.0056 0.05193 0.04987 -0.0685 0.8186 0.0175
-5.500 0.0265 0.04831 0.04619 -0.0742 0.8057 0.0175
-5.250 0.0491 0.04469 0.04251 -0.0796 0.7923 0.0176
-5.000 0.0681 0.04062 0.03837 -0.0832 0.7796 0.0177
-4.750 0.0842 0.03806 0.03576 -0.0840 0.7675 0.0179
-4.500 0.1057 0.03551 0.03314 -0.0867 0.7567 0.0181
-4.250 0.1308 0.03281 0.03040 -0.0905 0.7471 0.0184
-4.000 0.1579 0.03014 0.02767 -0.0947 0.7376 0.0190
-3.750 0.2038 0.02618 0.02359 -0.1049 0.7295 0.0210
-3.500 0.2456 0.02259 0.01988 -0.1128 0.7209 0.0211
-3.250 0.2776 0.01898 0.01617 -0.1180 0.7117 0.0214
-3.000 0.3035 0.01735 0.01448 -0.1198 0.7014 0.0217
-2.750 0.3330 0.01579 0.01284 -0.1225 0.6915 0.0222
-2.500 0.3677 0.01395 0.01091 -0.1264 0.6832 0.0231
-2.250 0.4227 0.01110 0.00780 -0.1344 0.6773 0.0252
-2.000 0.4583 0.00882 0.00538 -0.1386 0.6709 0.0259
-1.750 0.4877 0.00804 0.00453 -0.1401 0.6629 0.0265
-1.500 0.5207 0.00715 0.00352 -0.1422 0.6556 0.0276
-1.250 0.5651 0.00588 0.00190 -0.1456 0.6487 0.0300
-1.000 0.6407 0.00972 0.00436 -0.1605 0.6539 0.0257
-0.500 0.6993 0.00887 0.00327 -0.1609 0.6349 0.0269
-0.250 0.7278 0.00874 0.00307 -0.1609 0.6249 0.0280
0.000 0.7564 0.00854 0.00277 -0.1609 0.6135 0.0292
0.250 0.7850 0.00839 0.00255 -0.1608 0.6017 0.0300
0.500 0.8138 0.00814 0.00223 -0.1609 0.5892 0.0318
0.750 0.8418 0.00815 0.00220 -0.1607 0.5749 0.0334
1.000 0.8696 0.00818 0.00215 -0.1605 0.5588 0.0353
1.250 0.8974 0.00819 0.00212 -0.1604 0.5415 0.0384
1.500 0.9247 0.00832 0.00219 -0.1601 0.5235 0.0417
1.750 0.9522 0.00837 0.00216 -0.1600 0.5029 0.0457
2.000 0.9789 0.00856 0.00224 -0.1596 0.4741 0.0493
2.250 1.0054 0.00876 0.00227 -0.1593 0.4380 0.0528
2.500 1.0313 0.00905 0.00239 -0.1590 0.3960 0.0564
2.750 1.0568 0.00942 0.00255 -0.1585 0.3546 0.0593
3.000 1.0826 0.00972 0.00269 -0.1581 0.3224 0.0620
3.250 1.1090 0.00995 0.00280 -0.1578 0.2995 0.0658
3.500 1.1354 0.01016 0.00293 -0.1575 0.2832 0.0694
3.750 1.1620 0.01033 0.00306 -0.1572 0.2714 0.0724
4.000 1.1888 0.01049 0.00320 -0.1569 0.2616 0.0829
4.250 1.2141 0.00950 0.00365 -0.1569 0.2528 1.0000
4.500 1.2407 0.00969 0.00379 -0.1565 0.2463 1.0000
4.750 1.2671 0.00989 0.00394 -0.1562 0.2399 1.0000
5.000 1.2933 0.01012 0.00413 -0.1558 0.2341 1.0000
5.250 1.3199 0.01027 0.00428 -0.1555 0.2305 1.0000
5.500 1.3460 0.01047 0.00446 -0.1551 0.2257 1.0000
5.750 1.3717 0.01073 0.00468 -0.1547 0.2198 1.0000
6.000 1.3981 0.01088 0.00485 -0.1544 0.2166 1.0000
6.250 1.4242 0.01107 0.00503 -0.1540 0.2125 1.0000
6.500 1.4497 0.01130 0.00525 -0.1536 0.2074 1.0000
6.750 1.4753 0.01152 0.00547 -0.1531 0.2023 1.0000
7.000 1.5010 0.01172 0.00566 -0.1527 0.1961 1.0000
7.250 1.5258 0.01200 0.00591 -0.1522 0.1885 1.0000
7.500 1.5511 0.01223 0.00613 -0.1517 0.1801 1.0000
7.750 1.5749 0.01259 0.00642 -0.1511 0.1639 1.0000
8.000 1.5943 0.01344 0.00699 -0.1498 0.1253 1.0000
8.250 1.6134 0.01429 0.00765 -0.1484 0.0989 1.0000
8.500 1.6292 0.01547 0.00855 -0.1466 0.0597 1.0000
8.750 1.6485 0.01624 0.00923 -0.1452 0.0468 1.0000
9.000 1.6696 0.01680 0.00978 -0.1441 0.0422 1.0000
9.250 1.6916 0.01722 0.01023 -0.1432 0.0410 1.0000
9.500 1.7129 0.01769 0.01074 -0.1421 0.0398 1.0000
9.750 1.7333 0.01822 0.01130 -0.1409 0.0384 1.0000
10.000 1.7527 0.01882 0.01192 -0.1396 0.0366 1.0000
10.250 1.7713 0.01945 0.01260 -0.1382 0.0350 1.0000
10.500 1.7899 0.02004 0.01325 -0.1367 0.0340 1.0000
10.750 1.8095 0.02048 0.01375 -0.1355 0.0334 1.0000
11.000 1.8282 0.02097 0.01429 -0.1341 0.0324 1.0000
11.250 1.8457 0.02152 0.01488 -0.1325 0.0313 1.0000
11.500 1.8607 0.02216 0.01556 -0.1306 0.0299 1.0000
11.750 1.8721 0.02292 0.01636 -0.1280 0.0285 1.0000
12.000 1.8812 0.02373 0.01723 -0.1251 0.0273 1.0000
12.250 1.8971 0.02414 0.01769 -0.1233 0.0265 1.0000
12.500 1.9111 0.02469 0.01828 -0.1214 0.0248 1.0000
12.750 1.9213 0.02552 0.01911 -0.1190 0.0222 1.0000
13.000 1.9313 0.02641 0.02000 -0.1167 0.0186 1.0000
13.250 1.9346 0.02785 0.02140 -0.1138 0.0137 1.0000
13.750 1.9399 0.03117 0.02483 -0.1088 0.0098 1.0000
14.000 1.9415 0.03308 0.02681 -0.1066 0.0090 1.0000
14.250 1.9417 0.03525 0.02907 -0.1045 0.0084 1.0000
14.500 1.9440 0.03731 0.03123 -0.1029 0.0081 1.0000
14.750 1.9445 0.03964 0.03367 -0.1014 0.0078 1.0000
15.000 1.9435 0.04226 0.03639 -0.1001 0.0075 1.0000
15.250 1.9405 0.04519 0.03943 -0.0989 0.0073 1.0000
15.500 1.9359 0.04842 0.04276 -0.0980 0.0072 1.0000
15.750 1.9288 0.05206 0.04653 -0.0973 0.0070 1.0000
16.000 1.9203 0.05599 0.05057 -0.0968 0.0068 1.0000
16.250 1.9087 0.06048 0.05519 -0.0966 0.0067 1.0000
16.500 1.8953 0.06542 0.06027 -0.0968 0.0066 1.0000
16.750 1.8795 0.07092 0.06592 -0.0973 0.0065 1.0000
17.000 1.8625 0.07681 0.07196 -0.0983 0.0064 1.0000
17.250 1.8456 0.08293 0.07821 -0.0995 0.0064 1.0000
17.500 1.8286 0.08918 0.08461 -0.1011 0.0064 1.0000
17.750 1.8103 0.09582 0.09139 -0.1029 0.0063 1.0000
18.000 1.7910 0.10281 0.09853 -0.1051 0.0063 1.0000
18.250 1.7699 0.11026 0.10611 -0.1076 0.0063 1.0000
18.500 1.7492 0.11773 0.11373 -0.1104 0.0063 1.0000
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