GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 500,000 Max Cl/Cd: 85.92 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe769-il-500000.txt Download as CSV file: xf-goe769-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2548 0.11023 0.10787 -0.0185 1.0000 0.0380
-10.000 -0.2485 0.10751 0.10518 -0.0193 1.0000 0.0388
-9.750 -0.2743 0.09997 0.09765 -0.0272 1.0000 0.0408
-9.500 -0.2636 0.09764 0.09535 -0.0263 1.0000 0.0410
-9.250 -0.2544 0.09539 0.09314 -0.0260 1.0000 0.0411
-9.000 -0.2441 0.09334 0.09113 -0.0256 1.0000 0.0414
-8.750 -0.1809 0.08776 0.08545 -0.0390 0.9277 0.0421
-8.500 -0.1725 0.07703 0.07439 -0.0583 0.8474 0.0454
-8.250 -0.1658 0.07487 0.07200 -0.0572 0.7944 0.0457
-8.000 -0.1562 0.07348 0.07047 -0.0560 0.7623 0.0459
-7.750 -0.3682 0.02662 0.02189 -0.0788 0.7628 0.0368
-7.500 -0.3536 0.02425 0.01911 -0.0776 0.7450 0.0368
-7.250 -0.3349 0.02255 0.01713 -0.0767 0.7294 0.0370
-7.000 -0.3138 0.02127 0.01562 -0.0758 0.7156 0.0372
-6.750 -0.2906 0.02028 0.01448 -0.0750 0.7035 0.0375
-6.500 -0.2661 0.01971 0.01380 -0.0743 0.6921 0.0379
-6.250 -0.2415 0.01895 0.01292 -0.0736 0.6810 0.0384
-6.000 -0.2172 0.01813 0.01189 -0.0728 0.6706 0.0389
-5.750 -0.1923 0.01725 0.01083 -0.0721 0.6602 0.0393
-5.500 -0.1670 0.01653 0.00989 -0.0714 0.6508 0.0396
-5.250 -0.1409 0.01587 0.00909 -0.0707 0.6413 0.0401
-5.000 -0.1148 0.01536 0.00839 -0.0700 0.6319 0.0405
-4.750 -0.0882 0.01477 0.00770 -0.0694 0.6223 0.0410
-4.500 -0.0624 0.01414 0.00701 -0.0688 0.6123 0.0416
-4.250 -0.0355 0.01373 0.00659 -0.0683 0.6024 0.0422
-4.000 -0.0087 0.01342 0.00620 -0.0677 0.5924 0.0430
-3.750 0.0184 0.01308 0.00582 -0.0671 0.5811 0.0439
-3.500 0.0453 0.01285 0.00547 -0.0665 0.5683 0.0450
-3.250 0.0720 0.01246 0.00503 -0.0659 0.5545 0.0462
-3.000 0.0989 0.01221 0.00477 -0.0653 0.5419 0.0474
-2.750 0.1259 0.01201 0.00451 -0.0647 0.5292 0.0489
-2.500 0.1533 0.01184 0.00425 -0.0642 0.5161 0.0505
-2.250 0.1799 0.01156 0.00398 -0.0636 0.5032 0.0526
-2.000 0.2069 0.01145 0.00379 -0.0631 0.4900 0.0553
-1.750 0.2339 0.01128 0.00361 -0.0625 0.4772 0.0587
-1.500 0.2611 0.01116 0.00347 -0.0620 0.4656 0.0637
-1.250 0.2879 0.01111 0.00338 -0.0615 0.4542 0.0710
-1.000 0.3154 0.01104 0.00332 -0.0610 0.4432 0.0803
-0.750 0.3426 0.01104 0.00330 -0.0605 0.4333 0.0898
-0.500 0.3701 0.01101 0.00327 -0.0601 0.4240 0.0987
-0.250 0.3972 0.01103 0.00325 -0.0596 0.4153 0.1072
0.000 0.4249 0.01105 0.00326 -0.0592 0.4065 0.1152
0.250 0.4516 0.01105 0.00324 -0.0587 0.3980 0.1245
0.500 0.4792 0.01101 0.00323 -0.0584 0.3904 0.1342
0.750 0.5062 0.01105 0.00323 -0.0579 0.3827 0.1448
1.000 0.5334 0.01101 0.00324 -0.0575 0.3757 0.1606
1.250 0.5601 0.01094 0.00326 -0.0570 0.3679 0.1889
1.500 0.5858 0.01081 0.00333 -0.0565 0.3606 0.2668
1.750 0.6098 0.01032 0.00341 -0.0557 0.3538 0.4614
2.000 0.6810 0.00929 0.00360 -0.0644 0.3428 1.0000
2.250 0.7066 0.00939 0.00365 -0.0636 0.3357 1.0000
2.500 0.7312 0.00958 0.00372 -0.0627 0.3278 1.0000
2.750 0.7567 0.00971 0.00380 -0.0620 0.3206 1.0000
3.000 0.7816 0.00988 0.00389 -0.0611 0.3129 1.0000
3.250 0.8065 0.01006 0.00400 -0.0603 0.3055 1.0000
3.500 0.8317 0.01022 0.00411 -0.0595 0.2975 1.0000
3.750 0.8562 0.01044 0.00424 -0.0587 0.2896 1.0000
4.000 0.8815 0.01061 0.00436 -0.0580 0.2818 1.0000
4.250 0.9056 0.01087 0.00452 -0.0571 0.2742 1.0000
4.500 0.9310 0.01104 0.00467 -0.0564 0.2674 1.0000
4.750 0.9551 0.01131 0.00485 -0.0556 0.2603 1.0000
5.000 0.9801 0.01151 0.00503 -0.0548 0.2543 1.0000
5.250 1.0047 0.01175 0.00522 -0.0541 0.2484 1.0000
5.500 1.0280 0.01209 0.00546 -0.0532 0.2427 1.0000
5.750 1.0532 0.01228 0.00566 -0.0525 0.2383 1.0000
6.000 1.0774 0.01254 0.00588 -0.0518 0.2335 1.0000
6.250 1.1004 0.01289 0.00616 -0.0508 0.2287 1.0000
6.500 1.1246 0.01315 0.00642 -0.0501 0.2251 1.0000
6.750 1.1489 0.01339 0.00667 -0.0494 0.2215 1.0000
7.000 1.1722 0.01370 0.00694 -0.0485 0.2178 1.0000
7.250 1.1942 0.01409 0.00728 -0.0475 0.2140 1.0000
7.500 1.2171 0.01441 0.00760 -0.0466 0.2108 1.0000
7.750 1.2409 0.01466 0.00788 -0.0459 0.2079 1.0000
8.000 1.2637 0.01496 0.00818 -0.0450 0.2048 1.0000
8.250 1.2853 0.01533 0.00852 -0.0440 0.2019 1.0000
8.500 1.3049 0.01582 0.00897 -0.0427 0.1986 1.0000
8.750 1.3267 0.01615 0.00933 -0.0418 0.1963 1.0000
9.000 1.3488 0.01643 0.00965 -0.0408 0.1938 1.0000
9.250 1.3699 0.01675 0.01000 -0.0398 0.1912 1.0000
9.500 1.3895 0.01714 0.01038 -0.0385 0.1886 1.0000
9.750 1.4071 0.01762 0.01083 -0.0370 0.1861 1.0000
10.000 1.4221 0.01822 0.01142 -0.0352 0.1834 1.0000
10.250 1.4397 0.01853 0.01180 -0.0336 0.1818 1.0000
10.500 1.4560 0.01891 0.01222 -0.0318 0.1799 1.0000
10.750 1.4713 0.01934 0.01269 -0.0301 0.1778 1.0000
11.000 1.4858 0.01982 0.01320 -0.0283 0.1757 1.0000
11.250 1.4984 0.02043 0.01380 -0.0264 0.1735 1.0000
11.500 1.5088 0.02123 0.01458 -0.0244 0.1711 1.0000
11.750 1.5219 0.02193 0.01533 -0.0229 0.1694 1.0000
12.000 1.5360 0.02255 0.01604 -0.0215 0.1679 1.0000
12.250 1.5491 0.02328 0.01682 -0.0202 0.1662 1.0000
12.500 1.5615 0.02409 0.01768 -0.0190 0.1644 1.0000
12.750 1.5728 0.02502 0.01865 -0.0178 0.1627 1.0000
13.000 1.5829 0.02608 0.01973 -0.0167 0.1609 1.0000
13.250 1.5910 0.02736 0.02101 -0.0156 0.1588 1.0000
13.500 1.6004 0.02861 0.02230 -0.0147 0.1571 1.0000
13.750 1.6109 0.02980 0.02359 -0.0140 0.1558 1.0000
14.000 1.6208 0.03109 0.02496 -0.0134 0.1543 1.0000
14.250 1.6299 0.03248 0.02642 -0.0129 0.1528 1.0000
14.500 1.6383 0.03397 0.02797 -0.0125 0.1513 1.0000
14.750 1.6456 0.03558 0.02962 -0.0121 0.1499 1.0000
15.000 1.6519 0.03729 0.03136 -0.0117 0.1484 1.0000
15.250 1.6577 0.03904 0.03311 -0.0112 0.1467 1.0000
15.500 1.6639 0.04078 0.03489 -0.0107 0.1452 1.0000
15.750 1.6685 0.04277 0.03701 -0.0107 0.1441 1.0000
16.000 1.6717 0.04497 0.03931 -0.0108 0.1425 1.0000
16.250 1.6750 0.04717 0.04159 -0.0109 0.1410 1.0000
16.500 1.6776 0.04949 0.04398 -0.0111 0.1394 1.0000
16.750 1.6798 0.05188 0.04641 -0.0114 0.1380 1.0000
17.000 1.6814 0.05434 0.04890 -0.0116 0.1364 1.0000
17.250 1.6864 0.05629 0.05084 -0.0115 0.1348 1.0000
17.500 1.6872 0.05895 0.05360 -0.0119 0.1336 1.0000
17.750 1.6859 0.06202 0.05679 -0.0127 0.1326 1.0000
18.000 1.6837 0.06526 0.06015 -0.0136 0.1311 1.0000
18.250 1.6816 0.06853 0.06351 -0.0146 0.1296 1.0000
18.500 1.6800 0.07176 0.06681 -0.0155 0.1282 1.0000
18.750 1.6795 0.07484 0.06995 -0.0164 0.1270 1.0000
19.000 1.6795 0.07781 0.07295 -0.0173 0.1257 1.0000
19.250 1.6849 0.07989 0.07502 -0.0176 0.1242 1.0000
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