GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 100,000 Max Cl/Cd: 51.26 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe488-il-100000-n5.txt Download as CSV file: xf-goe488-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4208 0.10146 0.09643 -0.0287 1.0000 0.0562
-8.500 -0.4274 0.09898 0.09404 -0.0301 1.0000 0.0564
-8.250 -0.4348 0.09644 0.09159 -0.0312 1.0000 0.0566
-8.000 -0.4372 0.09328 0.08847 -0.0335 1.0000 0.0567
-7.750 -0.4385 0.08992 0.08513 -0.0355 1.0000 0.0568
-7.500 -0.4254 0.08550 0.08074 -0.0269 1.0000 0.0600
-7.250 -0.4258 0.08270 0.07798 -0.0268 1.0000 0.0609
-7.000 -0.4267 0.07987 0.07519 -0.0269 1.0000 0.0618
-6.750 -0.4277 0.07691 0.07226 -0.0271 1.0000 0.0626
-6.500 -0.4293 0.07221 0.06751 -0.0294 1.0000 0.0536
-6.250 -0.4271 0.06866 0.06391 -0.0305 1.0000 0.0542
-6.000 -0.4225 0.06495 0.06014 -0.0314 1.0000 0.0546
-5.750 -0.4168 0.06143 0.05655 -0.0314 1.0000 0.0539
-5.500 -0.4092 0.05778 0.05281 -0.0314 1.0000 0.0525
-5.250 -0.3988 0.05390 0.04877 -0.0319 1.0000 0.0513
-5.000 -0.3858 0.05003 0.04471 -0.0325 1.0000 0.0511
-4.750 -0.3669 0.04611 0.04051 -0.0338 0.9993 0.0532
-4.500 -0.3349 0.04138 0.03538 -0.0373 0.9953 0.0532
-4.250 -0.3035 0.03705 0.03059 -0.0400 0.9911 0.0526
-4.000 -0.2713 0.03329 0.02634 -0.0423 0.9872 0.0525
-3.750 -0.2405 0.03033 0.02288 -0.0438 0.9832 0.0531
-3.500 -0.2088 0.02819 0.02017 -0.0449 0.9793 0.0554
-3.250 -0.1770 0.02630 0.01784 -0.0461 0.9761 0.0557
-3.000 -0.1478 0.02471 0.01588 -0.0466 0.9719 0.0556
-2.750 -0.1155 0.02333 0.01417 -0.0476 0.9686 0.0556
-2.500 -0.0843 0.02220 0.01276 -0.0483 0.9644 0.0559
-2.250 -0.0508 0.02122 0.01155 -0.0494 0.9594 0.0563
-2.000 -0.0162 0.02031 0.01048 -0.0506 0.9541 0.0570
-1.750 0.0188 0.01930 0.00943 -0.0520 0.9478 0.0587
-1.500 0.0524 0.01860 0.00872 -0.0531 0.9407 0.0607
-1.250 0.0891 0.01800 0.00811 -0.0548 0.9348 0.0637
-1.000 0.1204 0.01756 0.00765 -0.0553 0.9270 0.0681
-0.750 0.1590 0.01702 0.00715 -0.0573 0.9212 0.0763
-0.500 0.1889 0.01664 0.00676 -0.0575 0.9124 0.0834
-0.250 0.2296 0.01605 0.00628 -0.0597 0.9067 0.1023
0.000 0.2602 0.01547 0.00607 -0.0600 0.8959 0.1898
0.250 0.2927 0.01495 0.00584 -0.0607 0.8856 0.2963
0.750 0.3952 0.01301 0.00554 -0.0694 0.8717 1.0000
1.000 0.4266 0.01292 0.00537 -0.0696 0.8606 1.0000
1.250 0.4568 0.01285 0.00523 -0.0697 0.8481 1.0000
1.500 0.4845 0.01280 0.00513 -0.0692 0.8333 1.0000
1.750 0.5108 0.01277 0.00508 -0.0684 0.8163 1.0000
2.000 0.5370 0.01275 0.00504 -0.0676 0.7965 1.0000
2.250 0.5640 0.01270 0.00496 -0.0669 0.7737 1.0000
2.500 0.5893 0.01270 0.00492 -0.0659 0.7444 1.0000
2.750 0.6157 0.01269 0.00485 -0.0649 0.7049 1.0000
3.000 0.6443 0.01273 0.00467 -0.0643 0.6499 1.0000
3.250 0.6690 0.01305 0.00460 -0.0630 0.5835 1.0000
3.500 0.6897 0.01352 0.00476 -0.0612 0.5162 1.0000
3.750 0.7099 0.01405 0.00498 -0.0596 0.4650 1.0000
4.000 0.7312 0.01453 0.00527 -0.0582 0.4323 1.0000
4.250 0.7531 0.01500 0.00560 -0.0570 0.4076 1.0000
4.500 0.7754 0.01545 0.00598 -0.0559 0.3864 1.0000
4.750 0.7978 0.01590 0.00637 -0.0549 0.3670 1.0000
5.000 0.8202 0.01635 0.00679 -0.0539 0.3497 1.0000
5.250 0.8428 0.01678 0.00722 -0.0529 0.3337 1.0000
5.500 0.8660 0.01719 0.00771 -0.0520 0.3206 1.0000
5.750 0.8891 0.01761 0.00821 -0.0511 0.3076 1.0000
6.000 0.9101 0.01803 0.00862 -0.0499 0.2838 1.0000
6.250 0.9303 0.01841 0.00896 -0.0486 0.2464 1.0000
6.500 0.9516 0.01884 0.00943 -0.0475 0.2169 1.0000
6.750 0.9716 0.01943 0.00990 -0.0463 0.1825 1.0000
7.000 0.9905 0.02024 0.01054 -0.0450 0.1458 1.0000
7.250 1.0087 0.02125 0.01138 -0.0436 0.1028 1.0000
7.500 1.0231 0.02281 0.01255 -0.0419 0.0541 1.0000
7.750 1.0392 0.02414 0.01389 -0.0401 0.0363 1.0000
8.250 1.0717 0.02647 0.01646 -0.0365 0.0270 1.0000
8.500 1.0862 0.02769 0.01785 -0.0346 0.0249 1.0000
8.750 1.0981 0.02909 0.01935 -0.0325 0.0231 1.0000
9.000 1.1085 0.03055 0.02097 -0.0301 0.0216 1.0000
9.250 1.1188 0.03196 0.02258 -0.0277 0.0207 1.0000
9.500 1.1272 0.03354 0.02435 -0.0252 0.0200 1.0000
9.750 1.1342 0.03521 0.02618 -0.0225 0.0194 1.0000
10.000 1.1413 0.03696 0.02816 -0.0199 0.0190 1.0000
10.250 1.1484 0.03891 0.03029 -0.0174 0.0186 1.0000
10.500 1.1555 0.04104 0.03261 -0.0152 0.0183 1.0000
10.750 1.1614 0.04328 0.03507 -0.0131 0.0179 1.0000
11.000 1.1649 0.04567 0.03768 -0.0109 0.0174 1.0000
11.250 1.1656 0.04811 0.04033 -0.0089 0.0169 1.0000
11.500 1.1633 0.05083 0.04326 -0.0071 0.0164 1.0000
11.750 1.1587 0.05386 0.04649 -0.0056 0.0160 1.0000
12.000 1.1515 0.05723 0.05009 -0.0044 0.0157 1.0000
12.250 1.1404 0.06122 0.05431 -0.0039 0.0154 1.0000
12.500 1.1295 0.06534 0.05866 -0.0040 0.0154 1.0000
12.750 1.1179 0.06975 0.06332 -0.0048 0.0154 1.0000
13.000 1.1032 0.07498 0.06878 -0.0067 0.0154 1.0000
13.250 1.0869 0.08099 0.07501 -0.0097 0.0154 1.0000
13.500 1.0696 0.08780 0.08203 -0.0137 0.0155 1.0000
13.750 1.0521 0.09539 0.08985 -0.0187 0.0157 1.0000
14.000 1.0301 0.10485 0.09953 -0.0251 0.0160 1.0000
14.250 0.9980 0.11803 0.11294 -0.0338 0.0168 1.0000
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Polar data table (+)
Polar graphs
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