GOE 683 AIRFOIL (goe683-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 683 AIRFOIL (goe683-il) Reynolds number: 100,000 Max Cl/Cd: 31.25 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe683-il-100000.txt Download as CSV file: xf-goe683-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 683 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5488 0.07618 0.07053 -0.0736 1.0000 0.1234
-12.250 -0.5941 0.06879 0.06308 -0.0750 1.0000 0.1226
-12.000 -0.6448 0.06318 0.05739 -0.0734 1.0000 0.1218
-11.750 -0.6920 0.05955 0.05369 -0.0688 1.0000 0.1212
-11.500 -0.7393 0.05797 0.05211 -0.0613 1.0000 0.1206
-11.250 -0.7898 0.05778 0.05194 -0.0519 1.0000 0.1200
-11.000 -0.8370 0.05722 0.05133 -0.0433 0.9992 0.1196
-10.750 -0.8518 0.05303 0.04669 -0.0419 0.9855 0.1202
-10.500 -0.8575 0.04926 0.04241 -0.0403 0.9723 0.1216
-10.250 -0.8583 0.04607 0.03864 -0.0384 0.9596 0.1231
-10.000 -0.8247 0.04385 0.03639 -0.0409 0.9513 0.1257
-9.750 -0.7936 0.04231 0.03478 -0.0425 0.9421 0.1283
-9.500 -0.7654 0.04041 0.03262 -0.0437 0.9336 0.1317
-9.250 -0.7527 0.03869 0.03049 -0.0419 0.9221 0.1345
-9.000 -0.7122 0.03674 0.02843 -0.0450 0.9161 0.1383
-8.750 -0.6726 0.03543 0.02706 -0.0476 0.9092 0.1426
-8.500 -0.6450 0.03412 0.02545 -0.0479 0.8997 0.1475
-8.250 -0.5919 0.03234 0.02366 -0.0529 0.8954 0.1534
-8.000 -0.5693 0.03161 0.02284 -0.0521 0.8837 0.1584
-7.750 -0.5271 0.03015 0.02120 -0.0549 0.8774 0.1659
-7.500 -0.4991 0.02947 0.02058 -0.0550 0.8668 0.1727
-7.250 -0.4633 0.02834 0.01933 -0.0565 0.8586 0.1821
-7.000 -0.4402 0.02783 0.01883 -0.0556 0.8483 0.1917
-6.750 -0.4103 0.02701 0.01806 -0.0559 0.8390 0.2044
-6.500 -0.3917 0.02653 0.01758 -0.0541 0.8290 0.2188
-6.250 -0.3727 0.02608 0.01713 -0.0522 0.8191 0.2357
-6.000 -0.3584 0.02585 0.01687 -0.0495 0.8094 0.2520
-5.750 -0.3436 0.02570 0.01665 -0.0467 0.7993 0.2672
-5.500 -0.3201 0.02536 0.01638 -0.0457 0.7910 0.2820
-5.250 -0.3037 0.02515 0.01617 -0.0435 0.7804 0.2944
-5.000 -0.2737 0.02469 0.01558 -0.0434 0.7740 0.3097
-4.750 -0.2621 0.02467 0.01567 -0.0405 0.7619 0.3204
-4.500 -0.2304 0.02415 0.01512 -0.0409 0.7551 0.3355
-4.250 -0.2199 0.02423 0.01515 -0.0376 0.7445 0.3481
-4.000 -0.1905 0.02375 0.01475 -0.0376 0.7367 0.3654
-3.750 -0.1675 0.02349 0.01458 -0.0366 0.7281 0.3823
-3.500 -0.1449 0.02321 0.01439 -0.0354 0.7189 0.4009
-3.250 -0.1128 0.02268 0.01389 -0.0358 0.7131 0.4281
-3.000 -0.1028 0.02275 0.01414 -0.0325 0.7023 0.4522
-2.750 -0.0733 0.02219 0.01375 -0.0324 0.6955 0.4919
-2.500 -0.0488 0.02186 0.01376 -0.0316 0.6870 0.5403
-2.250 -0.0055 0.02127 0.01364 -0.0342 0.6784 0.6235
-2.000 0.1395 0.02114 0.01390 -0.0548 0.6706 0.7555
-1.750 0.1985 0.02223 0.01499 -0.0591 0.6599 0.7964
-1.500 0.2487 0.02293 0.01548 -0.0616 0.6533 0.8242
-1.250 0.2868 0.02407 0.01658 -0.0625 0.6437 0.8449
-1.000 0.3353 0.02478 0.01713 -0.0651 0.6361 0.8640
-0.750 0.3823 0.02551 0.01771 -0.0679 0.6287 0.8824
-0.500 0.4265 0.02619 0.01833 -0.0705 0.6196 0.9003
-0.250 0.4844 0.02655 0.01847 -0.0754 0.6133 0.9175
0.000 0.5290 0.02714 0.01906 -0.0786 0.6044 0.9358
0.250 0.5800 0.02724 0.01905 -0.0830 0.5969 0.9528
0.500 0.6357 0.02711 0.01874 -0.0885 0.5905 0.9677
0.750 0.6863 0.02693 0.01860 -0.0937 0.5815 0.9828
1.000 0.7528 0.02596 0.01746 -0.1015 0.5748 0.9985
1.250 0.7700 0.02609 0.01756 -0.1006 0.5691 1.0000
1.500 0.7781 0.02645 0.01797 -0.0980 0.5625 1.0000
1.750 0.7938 0.02655 0.01800 -0.0964 0.5574 1.0000
2.000 0.8147 0.02656 0.01786 -0.0954 0.5533 1.0000
2.250 0.8189 0.02723 0.01866 -0.0922 0.5466 1.0000
2.500 0.8313 0.02760 0.01903 -0.0900 0.5409 1.0000
2.750 0.8514 0.02767 0.01901 -0.0888 0.5364 1.0000
3.000 0.8715 0.02789 0.01914 -0.0877 0.5325 1.0000
3.250 0.8719 0.02891 0.02032 -0.0838 0.5258 1.0000
3.500 0.8869 0.02927 0.02068 -0.0819 0.5206 1.0000
3.750 0.9105 0.02929 0.02059 -0.0811 0.5166 1.0000
4.000 0.9245 0.02988 0.02119 -0.0791 0.5121 1.0000
4.250 0.9224 0.03118 0.02264 -0.0749 0.5059 1.0000
4.500 0.9374 0.03165 0.02312 -0.0730 0.5013 1.0000
4.750 0.9627 0.03167 0.02305 -0.0725 0.4977 1.0000
5.000 0.9765 0.03234 0.02372 -0.0704 0.4933 1.0000
5.250 0.9611 0.03431 0.02589 -0.0645 0.4867 1.0000
5.500 0.9753 0.03489 0.02648 -0.0625 0.4824 1.0000
5.750 1.0004 0.03499 0.02653 -0.0619 0.4792 1.0000
6.000 1.0348 0.03488 0.02631 -0.0627 0.4765 1.0000
6.250 0.9387 0.04073 0.03257 -0.0468 0.4674 1.0000
6.500 0.9494 0.04144 0.03328 -0.0443 0.4633 1.0000
6.750 1.0038 0.04006 0.03181 -0.0472 0.4606 1.0000
7.000 1.0616 0.03871 0.03032 -0.0507 0.4579 1.0000
7.250 0.5036 0.08154 0.07363 -0.0126 0.4285 1.0000
7.500 0.4881 0.08595 0.07807 -0.0117 0.4281 1.0000
7.750 0.4692 0.09129 0.08345 -0.0114 0.4335 1.0000
8.000 0.4871 0.09410 0.08628 -0.0117 0.4407 1.0000
8.250 0.5025 0.09634 0.08853 -0.0113 0.4398 1.0000
8.500 0.5162 0.09891 0.09110 -0.0109 0.4393 1.0000
8.750 0.5391 0.09688 0.08903 -0.0084 0.4200 1.0000
9.000 0.5437 0.10012 0.09229 -0.0081 0.4203 1.0000
9.250 0.4302 0.11206 0.10435 -0.0088 0.4472 1.0000
9.500 0.4767 0.11300 0.10530 -0.0088 0.4406 1.0000
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Polar data table (+)
Polar graphs
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