GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 500,000 Max Cl/Cd: 112.85 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe803h-il-500000.txt Download as CSV file: xf-goe803h-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2464 0.10171 0.09949 -0.0259 1.0000 0.0177
-7.750 -0.2428 0.09934 0.09716 -0.0248 1.0000 0.0179
-7.500 -0.2440 0.09772 0.09558 -0.0230 1.0000 0.0180
-7.000 -0.2042 0.09115 0.08902 -0.0313 0.9932 0.0188
-6.750 -0.1794 0.08745 0.08533 -0.0367 0.9862 0.0193
-6.500 -0.1545 0.08379 0.08166 -0.0423 0.9764 0.0200
-6.250 -0.1232 0.08000 0.07785 -0.0507 0.9623 0.0210
-6.000 -0.0765 0.07562 0.07342 -0.0659 0.9492 0.0211
-5.750 -0.0501 0.07102 0.06880 -0.0697 0.9402 0.0213
-5.500 -0.0233 0.06742 0.06516 -0.0730 0.9298 0.0216
-5.250 0.0068 0.06433 0.06199 -0.0780 0.9152 0.0221
-5.000 0.0346 0.06148 0.05905 -0.0828 0.8991 0.0228
-4.750 0.0622 0.05865 0.05612 -0.0875 0.8839 0.0235
-4.500 0.1003 0.05541 0.05277 -0.0956 0.8694 0.0249
-4.250 0.1565 0.05070 0.04790 -0.1099 0.8557 0.0253
-4.000 0.1705 0.04828 0.04545 -0.1089 0.8425 0.0256
-3.750 0.1939 0.04606 0.04318 -0.1106 0.8296 0.0261
-3.500 0.2242 0.04372 0.04075 -0.1142 0.8171 0.0268
-2.750 0.3535 0.03416 0.03072 -0.1338 0.7817 0.0305
-2.500 0.3809 0.03239 0.02887 -0.1354 0.7701 0.0311
-2.250 0.4138 0.03052 0.02686 -0.1381 0.7579 0.0322
-2.000 0.4720 0.02770 0.02365 -0.1448 0.7463 0.0355
-1.750 0.5037 0.02466 0.02050 -0.1477 0.7355 0.0362
-1.500 0.5315 0.02348 0.01923 -0.1488 0.7255 0.0371
-1.250 0.5634 0.02220 0.01785 -0.1503 0.7159 0.0389
-1.000 0.6065 0.02092 0.01610 -0.1522 0.7074 0.0423
-0.750 0.6412 0.01799 0.01303 -0.1549 0.6985 0.0434
-0.500 0.6708 0.01704 0.01199 -0.1558 0.6899 0.0445
-0.250 0.7020 0.01610 0.01091 -0.1565 0.6805 0.0467
0.000 0.7344 0.01611 0.01056 -0.1563 0.6715 0.0506
0.250 0.7724 0.01265 0.00668 -0.1586 0.6626 0.0407
0.500 0.8039 0.01156 0.00533 -0.1591 0.6529 0.0401
0.750 0.8334 0.01099 0.00455 -0.1591 0.6428 0.0413
1.000 0.8625 0.01050 0.00395 -0.1592 0.6314 0.0436
1.250 0.8904 0.01039 0.00383 -0.1590 0.6193 0.0468
1.500 0.9184 0.01024 0.00359 -0.1588 0.6065 0.0499
1.750 0.9467 0.00995 0.00326 -0.1588 0.5919 0.0543
2.000 0.9739 0.00999 0.00324 -0.1585 0.5753 0.0599
2.250 1.0017 0.00982 0.00304 -0.1584 0.5571 0.0652
2.500 1.0286 0.00989 0.00304 -0.1581 0.5373 0.0707
2.750 1.0556 0.00993 0.00300 -0.1578 0.5151 0.0755
3.000 1.0818 0.01009 0.00304 -0.1574 0.4859 0.0802
3.250 1.1072 0.01036 0.00315 -0.1569 0.4472 0.0852
3.500 1.1318 0.01075 0.00331 -0.1562 0.4004 0.0932
3.750 1.1562 0.01117 0.00359 -0.1556 0.3574 0.1344
4.000 1.1782 0.01044 0.00404 -0.1549 0.3293 1.0000
4.250 1.2032 0.01083 0.00427 -0.1543 0.3096 1.0000
4.500 1.2284 0.01119 0.00451 -0.1538 0.2955 1.0000
4.750 1.2538 0.01151 0.00475 -0.1533 0.2843 1.0000
5.000 1.2794 0.01179 0.00500 -0.1528 0.2757 1.0000
5.250 1.3045 0.01212 0.00526 -0.1523 0.2679 1.0000
5.500 1.3301 0.01238 0.00551 -0.1518 0.2616 1.0000
5.750 1.3553 0.01266 0.00577 -0.1513 0.2555 1.0000
6.000 1.3799 0.01301 0.00609 -0.1507 0.2500 1.0000
6.250 1.4056 0.01322 0.00634 -0.1502 0.2454 1.0000
6.500 1.4305 0.01351 0.00662 -0.1497 0.2399 1.0000
6.750 1.4545 0.01389 0.00697 -0.1490 0.2344 1.0000
7.000 1.4800 0.01408 0.00722 -0.1485 0.2293 1.0000
7.250 1.5043 0.01439 0.00753 -0.1479 0.2236 1.0000
7.500 1.5281 0.01474 0.00788 -0.1472 0.2183 1.0000
7.750 1.5531 0.01496 0.00817 -0.1467 0.2124 1.0000
8.000 1.5764 0.01533 0.00852 -0.1459 0.2055 1.0000
8.250 1.6009 0.01556 0.00881 -0.1454 0.1983 1.0000
8.500 1.6238 0.01594 0.00917 -0.1446 0.1888 1.0000
8.750 1.6469 0.01629 0.00950 -0.1438 0.1747 1.0000
9.000 1.6680 0.01682 0.00992 -0.1428 0.1492 1.0000
9.250 1.6837 0.01786 0.01071 -0.1410 0.1156 1.0000
9.500 1.6977 0.01903 0.01169 -0.1390 0.0867 1.0000
9.750 1.7098 0.02033 0.01278 -0.1366 0.0609 1.0000
10.000 1.7254 0.02122 0.01365 -0.1348 0.0541 1.0000
10.250 1.7413 0.02202 0.01449 -0.1329 0.0502 1.0000
10.500 1.7567 0.02280 0.01533 -0.1310 0.0477 1.0000
10.750 1.7695 0.02369 0.01627 -0.1288 0.0455 1.0000
11.000 1.7784 0.02467 0.01731 -0.1259 0.0435 1.0000
11.250 1.7852 0.02572 0.01844 -0.1227 0.0420 1.0000
11.500 1.7959 0.02655 0.01938 -0.1202 0.0410 1.0000
11.750 1.8049 0.02754 0.02047 -0.1177 0.0398 1.0000
12.000 1.8124 0.02869 0.02172 -0.1151 0.0385 1.0000
12.250 1.8177 0.03007 0.02319 -0.1126 0.0372 1.0000
12.500 1.8196 0.03182 0.02502 -0.1100 0.0358 1.0000
12.750 1.8159 0.03420 0.02750 -0.1073 0.0343 1.0000
13.000 1.8253 0.03552 0.02894 -0.1058 0.0334 1.0000
13.250 1.8347 0.03688 0.03041 -0.1045 0.0319 1.0000
13.500 1.8412 0.03858 0.03220 -0.1032 0.0303 1.0000
13.750 1.8418 0.04094 0.03463 -0.1017 0.0286 1.0000
14.000 1.8403 0.04365 0.03744 -0.1005 0.0270 1.0000
14.250 1.8559 0.04453 0.03841 -0.0998 0.0239 1.0000
14.500 1.8579 0.04695 0.04087 -0.0989 0.0213 1.0000
14.750 1.8610 0.04933 0.04328 -0.0982 0.0184 1.0000
15.000 1.8557 0.05280 0.04683 -0.0975 0.0166 1.0000
15.250 1.8494 0.05646 0.05061 -0.0970 0.0155 1.0000
15.500 1.8404 0.06061 0.05486 -0.0967 0.0147 1.0000
15.750 1.8270 0.06556 0.05992 -0.0969 0.0140 1.0000
16.000 1.8133 0.07075 0.06525 -0.0973 0.0137 1.0000
16.250 1.8008 0.07596 0.07062 -0.0981 0.0133 1.0000
16.500 1.7867 0.08162 0.07644 -0.0992 0.0130 1.0000
16.750 1.7711 0.08766 0.08263 -0.1006 0.0128 1.0000
17.000 1.7545 0.09405 0.08917 -0.1023 0.0126 1.0000
17.250 1.7369 0.10078 0.09605 -0.1044 0.0124 1.0000
17.500 1.7189 0.10773 0.10314 -0.1067 0.0123 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)